JP2012240667A - V/stol aircraft of turboshaft engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a tilt rotor aircraft and a tilt fan aircraft which take off and land vertically and in a short distance, and take off and land from an aircraft carrier, and a V/STOL aircraft of a turboshaft engine.SOLUTION: Right and left engines are engaged with a variable ducted rotor provided in right and left main wings of a barycenter part by shaft interlock, and are configured to perform vertical, forward, and backward inclined rise from tilt control of duct equipment, and make adjustment control which can circle right and left from hovering, and in switching from a ring rotor upon cruise flight and fan flight to jet flight, a jet blowout amount increases gradually, a drive shaft to the ring rotor and a fan is stopped rotating by a clutch and a brake, and a ducted ring rotor and fan equipment are airtightly performed by slide doors of an upper and lower face of the main wings.

Description

It is about takeoff and launch of fixed wing, fixed engine airplane and V / STOL aircraft.

The fixed wing and fixed engine aircraft other than the V / STOL aircraft are launched with the propulsion power of the fluid (steam) catapult and the means to achieve full power.

Japanese Patent Application 57-48155 Combined engine with convertible output Actual Application Sho 61-94406 Patent No. 2700734 Vertical take-off and landing aircraft Patent No. 3677748 Aircraft created by fixing the rapid air volume generating wind direction changing device directly on the side or side wall of the aircraft Patent No. 3753266 Traction device and catapult Patent No. 4111903 Flying object launching device and flying object launching method Patent No. 4653255 Trim hydrofoil device Patent No. 4480051 Hybrid generators connected to a gravity power generator using a balance having a pressure load device are operated by about 100 various aircraft carriers around the world, and the maintenance cost is enormous. In the case of stormy weather, the launch and landing of a small aircraft carrier is impossible, and the V / STOL carrier-based aircraft with inferior performance is adopted, and the small hull's ascent, trim, speed up and vertical and horizontal vibration reduction The fins, hydrofoil, and tank cylinder vibration reducer were combined to provide auxiliary equipment for the arrival and departure of small ships.

The catapult equipment is an air cushion levitation propulsion float table that switches between turboshaft engine fan levitation output and jet propulsion, and the aircraft is mounted on the float plate to provide a short-range launch system from the outputs of both engines. Magnetic levitation and linear motor catapult traction were appropriately applied.

The existing VTOL turbofan engine was made an auxiliary equipment for vertical levitation by applying the wind power of the fixed and portable prime mover ducted fan to the fuselage volume surface. The VTOL tilt rotor machine and fan machine of this application are fixed to the upper part of the fuselage main wing part with a turbo shaft engine, and it is equipped with a small caliber ducted rotor and fan that is stored in the main wing separated from the engine. A combination of jet flight and rotary flight, with vertical take-off with two fixed turboshaft engines on the left and right, and a free turbine chamber with an open slide door structure and a turbofan engine with an open / closed fan door for the bypass ratio engine. Selected flight configuration.

The composite engine capable of converting the output of Patent Document 1 uses a free turbine with variable blade control, and unlike a helicopter rotor hub mechanism that is variable at the center, links multiple turbine blades that rotate at high speed. At the same time, the control method for making all wings variable is for a rotating machine with low rotation and low safety, and is an unreasonable technique that cannot be used in the center of an airplane engine. In the present application, an annular cover portion is used as a slide door, and the structure has no problem in safety.

The ship anti-vibration device of Patent Document 2 uses a reciprocating motion of the amount of water in the bow, stern, and left and right bottom ballast tanks as a vertical anti-vibration device, but the inclination of the hull and the flow velocity in the communication pipe do not match. The present application is a hydraulic cylinder tank cylinder agitator on the left and right sides of the bow and stern, and has intake cylinders on the left and right sides and the bottom of the ship, etc. The air pressure in the air tank is changed from the compression to the exhaust pressure adjustment check valve and the suction check valve, and the safety valve structure is filled with high-pressure air to speed up the buoyancy, and the air tank draft is moved back and forth. The vibration reduction device mainly communicates the vertical vibration of the shock absorber structure in communication with the left and right and interlocking with the compression of the air section. The same bottom ballast tank as in Document 2 is provided with a remote control intake valve at the bottom of the ship, filled with high-pressure air to form a buoyancy tank for levitation of the hull and trim. The bottom ballast tank was designed to be able to take water.

The trim hydrofoil device disclosed in Patent Document 7 has a structure in which a hydrofoil plate is folded from a hinge fixed to an appropriate position of a large ship, and a deck ship of a small ship is used as a rotation axis of the prop plate, and the support post and the hinge. The trim hydrofoil device of this application is a hindrance for quay mooring and waves. This is a trim hydrofoil device that is configured to slide up and down the hydrofoil wing equipment that folds on the support plate without any gaps from the storage part on the deck to the appropriate position between the bottom side ridges of the deck, mainly reducing the hull speed up and rolling. It was a rocking device.
Patent Document 8 is a device that takes the pressure of the water flow of the cruising into the hydraulic cylinder and inputs a large force to the prime mover, and uses the same pipe as the communication pipe for the shock absorber under the draft of the present application.

The launch of a 20 to 30 ton aircraft from an existing large aircraft carrier takes a few minutes at a speed of 250 km / h or more with a steam catapult length of 50 to 70 m, a steam piston propulsion force of 100 t, and a total power. The ships are set at intervals.
Aircraft carriers without catapults include those of ski jump V / STOL jet fighters and helicopter mother ships, and helicopters have been dispatched to the rear deck of all small ships. Devised a fixed wing launcher with air cushion / float levitation propulsion that can be launched from a small ship, and will also be a land take-off device.

If a new short-range launching device that can launch with a small hull such as a diesel engine is available for the launch of fixed wing and fixed engine ship-borne aircraft (fighter aircraft), the number of personnel will be reduced and all merits will be achieved.
In this application, it is also possible to launch larger shipboards from existing aircraft carriers, making the catapult the air cushion levitation, jet, magnetic levitation, and linear motor catapult, equipped with the optimal prime mover (turbo shaft engine) fan From the above, the machine weight was lifted by air pressure and air volume equipped with an air cushion float base to eliminate mechanical friction.
In addition, the bow and stern trims and stabilizers to reduce the hull swaying, the hydrofoil equipment to speed up, the damping from the compression of the atmospheric pressure of the hydraulic pipe tank cylinder attenuator, and the single and combined air pressure enclosure floating The equipment was designed to help the arrival and departure of the ship to speed up. Ship and land-specific VTOL machines are equipped with a ring rotor machine that tilts separately from the engine and a variable ducted rotor with a small diameter of the ring fan machine and a fan, and a sliding plate sealing structure that is housed in the left and right main wings. In combination with a turboshaft engine fixed on the left and right main wings and geared together, combined with vertical and horizontal takeoff and landing, and gradually flying from the flight as a rotor aircraft and fan aircraft, jet flight from the ejection of the open slide door in the free turbine room , The ducted rotor was stored in the main wing so that it could be used for jet flight speeding up, and horizontal takeoff and landing from jet flight would be possible.
In addition, it is equipped with a portable fan that helps to lift the burden of the V / STOL turbofan engine and assists the engine output of landing, and can take off from the small hull and take off and landing from the inside. .

Then, avoid the fuel tank and the equipment on the lower part of the fuselage fuselage of the VTOL aircraft mounted on the turbofan engine, and make the lower part of the full fuselage the structure of the deployment door, the structure of the fan levitation and jet propulsion, and the linear motor catapult With the combined use of towing, the launch of wind power, air cushion float and airframe engine output from the front of the ship speed is very small, the launch distance without the burden of the engine is very small, the landing deck distance plane is marginal The ship's speed can be set at normal speed, or it can be launched in a stopped or moored state, and the above-mentioned hydrofoil and tank cylinder anti-vibration devices are capable of launching in waves. Easier and faster speeds will result in higher lift from strong winds and easier launch. And the portable fan equipment that assists the levitation output to reduce the burden on the VTOL aircraft makes it easy to take off and land from any location.

For the landing and takeoff of fixed wings and fixed engine aircraft on land, the magnetic levitation linear motor or the weight is levitated with an air cushion float base equipped with a fan and installed under the road surface at the start position of the runway. This is a take-off device that can reduce the weight of the fuselage in a section of about 50m, doubling the speed from all power, and inevitably shortening the running distance. For landing, a launching device similar to the aircraft carrier, a plurality of landing wires, and a landing gear provided with a spring equipment (steel spring, fluid) to alleviate the impact load on the fuselage at the bottom of the road surface, and the fuselage And the wheels are equipped with cushioning materials that reduce shocks, and are equipped with short-range landing gear.

Trim hydrofoil equipment, fin equipment, tank cylinder vibration reduction equipment and ballast tank levitation equipment are installed on large and small aircraft carriers, hydrofoil blades with a large area of the bow, stern and center of gravity, or fin stabilizers, main wing plates and flaps Trimming from the angle control of the plate and the stabilizer running, the reduction of the pitching and rolling at the time of departure from the ship, and the speed-up, the high pressure air is encapsulated in the air tank of the tank cylinder vibration reduction device, The levitation trim of the ballast tank and the trim hydrofoil unit are aimed at 50 knots at full speed, and the wind speed from the front is more than 30m / s. The ascent of the equipped aircraft and jet propulsion, with the help of wind power from the front, will result in the output of both propulsion engines with the shipboard engine, and will be discussed later. Both hydrofoil facilities and tank facilities are the best equipment for air cushion levitation, magnetic levitation, and launching a small aircraft carrier from a linear motor catapult.
If combined with the current traction catapult equipment ship, the fluid (steam) pressure drops, and the linear motor is not a superconducting linear motor, but it is a low-power system that uses a primary ground system of about 10 mm and a spare tire. It is a small device, and it can be selected from one of the magnetic levitation and air cushion levitation equipments, and it can be used in combination with the engine propulsion power of the float. The combined use and combination with the anti-vibration device makes it possible to launch at the time of a wave, increasing the launch capability, and the normal hydrofoil trim and stabilizer on a sunny day increase the average speed for long-term navigation And fuel savings. In the current situation, there is no precise equipment that supports pitching, and the bow and stern movements of the bow and stern due to the waves of the inventions of Reference 4 and 5 and 6 of this application are mainly used, and it is also possible to move left and right simultaneously. With a compatible tank as an air chamber, air compression suppresses the hull's shaking, and high pressure air sealed buoyancy and trim configuration make the sunny trim hydrofoil speed up, Pitching tank cylinder attenuating sailing in stormy weather is a vibration reducing device that reduces the decrease in speed.

The invention of Reference 1
The fixed-wing, fixed-engine ship-borne fan linear launch system is equipped with a turbo-shaft engine equipped with airframe engine output and catapult float levitation propulsion equipment, and a magnetic levitation equipment integrated with a linear motor and catapult traction equipment. It was surfaced and used as a combined equipment, and it was a take-off launch device that was short-distance from gliding.
The fan connected to the 2-shaft shaft of the free turbine of the turbo-shaft engine, which generates almost 100% of the output as the rotational force, is blown forward in the reverse jet duct and connected to the catapult traction air cushion / float base, and the engine is centered. The front and rear are equipped with float bases, and the structure of the launching lifts the weight of the front wheel of the fuselage, and the weight of the rear of the fuselage on the left and right main wing deck surfaces sandwiching the float A straight opening width of about 3 to 10 cm for a towing catapult that receives the weight of the body of the front wheel catapult and the supporting rear wheel on the float center for the purpose of reducing the tow catapult opening width on the deck surface. The board surface of the width and length on which the airframe is placed is connected to the float, and the float board surface is integrated with the float on which the large and small airframes are placed. Provided small wheels on the deck upper surface, and that of stable flies, the full complement is a float base floating.
In addition, the lower part of the fuselage at the rear of the fuselage is used as a deployment door, and the method of reducing the load on the left and right rear wheels from the volume floating structure that receives the air volume from the open / close duct on the float base, and this turbo shaft engine An annular control sliding door structure is used, a free turbine is used as a circular plate, and a width for jetting is provided. The sliding door uses a hydraulic, electric, or pre-mechanical fan rotation and jet propulsion output with a variable ratio and full opening. In the fully closed configuration, a turbojet afterburner engine, which is composed of various airframes and large aircraft launch floats as appropriate, is used as the airflow of the air cushion and the launch jet propulsion.
The one or more turboshaft engines shall have separate and combined engine configurations for air cushion air volume and launch propulsion. In conjunction with maximum power and aircraft engine propulsion, the mooring lock on the float base and the float plate surface is released to catapult wheel traction, and the wheel brake is configured to be automatic and manual release, and it should be launched in about 2 seconds. The sudden stop of the catapult / float table was made by connecting the float between the left and right cushion tires by reversely jetting the compressed air in the float from the automatic control valve at the tip of the float.
Then, the airframe weight and air cushion / float base equipment are changed to the ground primary type linear motor catapult traction and air cushion levitation propulsion equipment, and the structure of appropriate magnetic levitation is adopted, and the equipment weight eliminates mechanical resistance and increases speed. The engine that is connected to the aircraft engine output and uses the turbo-shaft engine's free turbine chamber as an annular slide opening door control to make jet propulsion is used for the configuration of various jet engine aircraft. Become.
Even if the launch equipment is improved, the launch and departure are affected by the weather, and the ocean wave sway is natural. To be.
The front wheel catapult tow hook uses a device that automatically releases, and at the time of launch, it has various safety control equipment, and it is equipped with air cushion equipment, magnetic levitation and linear motor as appropriate for short takeoff and launch. It was a combination ship launcher.
In other words, the present invention is a device capable of launching a fighter with a small diesel engine aircraft carrier, and this fan body levitation control device is a primary ground type linear motor used for high-speed trains and a magnetic levitation equipment. It becomes a small light aircraft carrier, a ship that can be used for ships, and is equipped with a trim hydrofoil device and a tank shaker that reduce vibrations from speeding up.

Short-range landing and landing equipment for fixed wings, fixed-engine passenger aircraft, and military aircraft on the ground, the air cushion / float platform pulling equipment with a large prime mover of the same structure as the above is located under the fuselage below the fuselage. For the front and rear wheel levitation and jet shaft engine propulsion or magnetic levitation linear motor, the levitation start of the aircraft becomes a STOL aircraft, and the landing runway space is equipped with a shock absorber (fluid spring, rigid body) With the cushioning properties of springs, shock-absorbing elastic materials), military aircraft use a plurality of landing wire hook devices together, the shock load of the aircraft is equipped with shock-absorbing material for shock reduction aircraft and wheel connection, It was equipped with short-range landing equipment such as a moving brake section runway, fuselage wheels, and air brakes.
That is, the present invention is adopted for an airport with a short runway and a simple new airport.

The invention of Reference 2
Aircraft carriers such as small aircraft carriers and helicopter light aircraft carriers adopt V / STOL turbofan engine aircraft, and the total weight of vertical levitation is the burden of the turbofan engine. The fan wind power from the motorized ducted fan equipment installed under the deck and under the road surface with the pressure receiving surface and volume part receiving wind force as the deployment door is used to assist the floating force at the time of takeoff departure of the vertical levitation turbofan engine In addition, the upper opening / closing duct of the air cushion float launching equipment is used as the launching equipment, and an appropriate opening / closing capacity door is also used in the later-described tilt rotor and tilt fan machines. It also consists of a primed ducted fan equipment (R) that reduces the impact load on the aircraft during vertical landing. Then, a fan linear take-off launching device that facilitates the launch of V / STOL aircraft has been achieved since the hull shaking device has been installed on a smaller aircraft carrier, reducing the vertical and horizontal shaking.
In other words, according to the present invention, a turbofan engine-borne aircraft of a VTOL aircraft is composed of a variable bypass injection port that raises the aircraft weight and equipment weight, and a plurality of small-caliber nozzles for fine adjustment, and has a total weight. The thrust that lifts vertically from the state of stoppage is a burden on the engine, a large amount of fuel consumption, and skill in maneuvering. Therefore, the lower part of the fuselage has a volume expansion door that receives wind pressure and wind power, and this motorized ducted fan equipment is fixed and portable, and the efficiency of the VTOL turbofan engine machine that assists levitation with fan wind power A good takeoff launcher.

The invention of Reference 3
The trim hydrofoil device that reduces vertical and horizontal swings of the aircraft carrier and various hulls in good weather is provided with a slide groove of the column between the right and left deck surfaces of the bow and stern and the side wall anchors from the appropriate position under the draft, It is equipped with hydrofoil for large ships that are drastically changed in drafting position, and the strut plate is slid up and down to the underwater part from the male and female engagement of the deck slide groove, and the hydrofoil plate is hinged to the lower part of the strut plate The control unit is folded from the hydraulic unit and is equipped with a slide up / down storage and deployment with a hydraulic actuator, and the middle part of the strut plate and hydrofoil blade is hinged with a four-bar link support fixing plate, and the strut plate and hydrofoil The intermediate support fixing plate is connected with a double-acting hydraulic cylinder or trunnion type hydraulic cylinder via a slide connecting plate, or is engaged with a hydraulic motor gear, a slide groove spur gear, and a male shaft slide, Branch The slide groove of the plate and the slide connection plate are of a male and female slide structure, and the expansion and contraction of the slide connection plate by the cylinder and the motor is expanded from the folding of the hydrofoil blade, and the storage of the support plate on the deck is a remote operation slide The spur gear in the groove is engaged with the hydraulic motor gear of the strut plate, and the mounting part of the deck and heel is a rotating structure on the deck with the motor gear and male shaft of the strut plate as fulcrums, and the strut plate is set at the top of the heel The male surface of the hydrofoil hinge portion of the strut plate, the male surface of the strut intermediate link portion, and the male surface of the appropriate number of strut central portions are separated from the groove portion at the position, and from the rotation of the hydraulic motor gear of the strut plate It was configured to slide on the deck. Each hydraulic motor has a drum brake band closed structure with a hydraulic cylinder.
The props are lowered into the draft, and the vertical and horizontal fluctuations of the hull in the wave cycle are reduced by the optimal course and speed of the hydrofoil surface under the draft from the ship speed and underwater remotely controlled. Angle adjustment hydrofoil surface, vertical and horizontal shaking, change wave period and hull inclination underwater main wing angle of bow left and right side and stern left and right side, manual fixing of main wing front and rear edge flaps and angle change of automatic hydraulic control The mechanism is a trim and stabilizer that is a device that reduces the fluctuation of the vertical and horizontal periods of the wave, and the underwater main wing plate that has a wide area and length with a four-bar link is designed to speed up from the rising of the hull. The trim hydrofoil device features a sliding storage from the draft to the deck.
In other words, the present invention and the speed of a configuration in which the hydrofoil plate is hinged to the dredger of a large steel ship described in claim 3 of the trim hydrofoil device of Patent Document 7 and folded and deployed. The swing control by the vertical control of the flap and the main wing surface, and the speed from ascent are common, and the present application lowers the strut plate from the ridge above the water to an arbitrary position under the draft. It was designed to fold inside the board, and it could be stored on the deck.
And, the hydrofoil plate having an area and strength structure that reduces shaking is a trim hydrofoil device that is housed on the water except when necessary, with the bow part having an appropriate hull shape larger than the stern part.

The invention of Reference 4
Currently, rolling (rolling) is bilge keel, fin stabilizer, onboard anti-vibration tank equipment, and onboard gyro-stabilizer equipment, pitching is basically reduced in the center of the hull center of gravity. The above-mentioned trim hydrofoil equipment installed outside the ship cannot withstand a large moment load, and is provided with a hydraulic plate that is fixed to the upper part of the bow. There is a patent etc. that suppresses vertical movement by providing a float part outside, but the ship originally has this shape, and in high waves, it is the opposite effect of submergence. Various anti-vibration devices have been devised, but complete and reliable equipment is not possible, and there are small floating hydrofoil ships with reduced resistance, streamlined double hulls, etc. This is a technical problem that cannot be solved in running, and is to improve the vibration reduction technology within the range of the hull size and waves.
Therefore, the ship's tank, gyro reduction equipment, trim hydrofoil, and fin equipment are to be stored in stormy weather. A single and multiple intakes are provided to accommodate vertical and horizontal swings at appropriate angles to take in water currents and water pressures at high speeds and wave heights. A control valve is provided, and the upper surface of the large-capacity tank is used as an air compression section on the draft, and a suction check valve and a discharge check valve for pressure adjustment are provided at the top of the tank. Use a shock absorber that discharges air at a set pressure, and changes the tank draft when a large ship (heavy goods carrier) is fully loaded or empty, into a sealed tank that is filled with compressed air as appropriate from the pneumatic unit, The ship's momentum, wave height, and water flow pressure are balanced, and the moment of communication between the bow, stern and underwater parts of the left and right air tanks causes the flow of water in the communication pipe under the long front and rear draft to rod from the deck. With manual and automatic remote control valve flow adjustment, the flow load becomes a heavy load moment that raises the water volume between tanks with wave height, undulation up and down and right and left tilt angle and time, front and rear, left and right pneumatic tanks The pressure difference between the two and the water flow in the communication pipe becomes a linked shock absorber, and as one of the methods of using water pressure, a hydraulic linear power generation cylinder with an appropriate small diameter is installed from the underwater part, and many hydraulic piston strokes are provided. The power generation configuration is a pole mover and stator, and the power generation load is a shock absorber.
Large waves of front and rear (pitch) and left and right (roll) that hit the hull are the hull's vertical and horizontal movements, and the water pressure due to the ship's speed and waves is received by the air section of the air tank before the hull's reaction and long The bow and stern communication pipes and the flow load on the left and right side are hydraulic shock absorbers of pitching, and this shock absorber configuration is controlled by rolling from a remote control valve of flow that matches the wave height and wave period of each time. The hull's up and down and left and right movements are mainly reduced according to the appropriate pitching. Shaking of the hull due to waves is a variety of complex, especially pitching and rolling mainly to reduce the size, shape and up / down, left / right movement and up / down compression of tank air under water pressure due to waves. The water pressure due to the vertical movement of the hull is set to a damping structure that absorbs discharge from compression from the pressure setting of the discharge check valve of the air pressure, according to the ship speed, wind and swell, at that time, A device in which the energy that absorbs the water pressure of the wave stroke reduces the hull's length and breadth.
And when sailing with air pressure in good weather and stormy weather, the check valve is a safety valve and the air pressure at the top of the tank that receives this air pressure from the one that compresses the air pressure that matches the wave height and ship speed at that time and the hull bottom area Under the same water pressure, the pressure corresponding to the area is proportional, and the water surface in the tank is compressed by air pressure, and the sealed pressure due to the ship speed becomes the levitation force of the hull.
The location of the water pressure tank is set at an angle that takes in the water flow pressure at a slant angle in the direction of travel of the bow and stern from the bottom of the ship and the bilge keel that receives the speed and pitching, and the intake diameter matches the size of the hull. The tank shape, capacity, and area can be reduced by reducing the stern and making the bow part a large pressure-receiving area according to the hull shape. The air tank of a large ship that rises, especially the draft surface, is vertically long and vertically filled, and is filled with compressed air that matches the wave height and speed of the ship. It becomes a vibration reduction device that reduces
The rolling is controlled by providing a horizontal section at a slight distance between the left and right side water intake pipes and the tank to suck the transverse waves, and the waves change from wind waves to waves and waves, and the waves have a periodic cycle. Assuming that the tidal current and wind direction are entangled and the hull receives irregular waves in the direction of travel, especially large pitching reduces the course and speed of the ship, affects the ship speed and fuel consumption, and And the stern wave must be suppressed and rolling can be supported by the fin stabilizer, anti-vibration tank equipment, bilge keel and the trim hydrofoil equipment. This is not possible with the stern trim hydrofoil, and the damping device of this hydraulic pipe tank cylinder is incomplete, but the damping configuration changes depending on the size of the hull. 2 to the target pitching swinging motion reducing the extent 10 m, was assumed also waves rolling absorption of shape.
And, for calm sailing, air that fits the pressure of the ship's speed is sealed in the air tank, and appropriate air pressure is sealed even in stormy weather to create a compression cylinder structure with water pressure, and the hull speeds up from trim ascent. In addition, the double ballast tank at the bottom of the ship is equipped with a tank that drains high pressure air from press-fitting, and automatic intake of rods on the deck and manual intake and discharge of air from the bottom water intake remote valve of the ship bottom. Hull buoyancy structure. Then, the valve structure of the right and left side sliding doors was appropriately used, and the tank cylinder intake port was sealed to make the structure without water flow resistance.
Either the trim hydrofoil device of Patent Document 7 or the trim hydrofoil device of claim 3 of the present application is provided at the upper part of the intake port of this hydraulic piston agitator, and the combined use of both devices is stable running. The vertical and horizontal vibration reduction equipment.

The invention of Reference 5
One anti-vibration tank cylinder was installed at the bow and stern, and the vertical vibration was reduced at the center of the left and right anchors. For current ships, side thrusters are always in place, and the hydraulic tank cylinder's vibration reduction device is mainly for reducing vertical vibrations. Unlike the installation structure, a side thruster is provided at the intake of one hydraulic pipe tank cylinder at the tip of the bow and stern, and it is integrated with the current side thruster, so that the upper part of the propeller blade at the time of berthing and direction change The surface is the structure of the lower surface of the hydraulic pipe tank cylinder, the structure is a discharge structure that receives water flow from the left and right dredgers, and the structure for reducing the air pressure in the cylinder upper tank from the ship bottom and the left and right dredger intakes At the time of dimming during voyage, compressed air was appropriately sealed in the air tank, and the structure was made to reduce the water flow resistance from the hovering of the above-mentioned ballast tank levitating equipment.
The front and rear hydraulic pipe tank cylinders have a flow control configuration with a remote control valve that communicates with the draft, and a vertical load tank cylinder attenuator and a side thruster are installed at the same intake position. Anti-vibration device.

The invention of Reference 6
The anti-vibration device for speeding up a ship sailing for a long period of time includes a hydraulic pipe tank cylinder anti-vibration device mainly for pitching from the bottom of the bow and stern, the dredge on the left and right side of the bottom of the ship, and the intake provided in the bilge keel. Trim hydrofoil unit for swinging and swing-up folding slide storage mainly for shaking is installed at the upper part of the same position, this hydrofoil unit is controlled from the hydraulic unit in the state of waves, folded from deployment, hydraulic actuator Slidably housed on the surface and on the deck, or equipped with a tank agitation equipment and a gyro agitation equipment on the ship, paired with either of them, above the intake port of the bow part of the fin structure of a small area for rough weatherフ ィ ン Fin and stabilizer equipped mainly for rolling of storage and deployment with hydraulic actuator from inside, and vertical swinging of storage and deployment mainly on the stern intake. Equipped with a rim tab (similar to fins and stabilizers), stored and deployed with hydraulic actuators from inside the dredger, the tank cylinder anti-vibration device and a pair of hydrofoil are dedicated for sailing, and reduce vibration when stopping The effect is that the on-board vibration reduction equipment and the plurality of water intakes are tank cylinder vibration reduction devices for pitching and rolling.
The hydraulic cylinder tank cylinder attenuator for vertical / horizontal vibration reduction during stormy waves is installed at the right and left sides of the ship and at the bottom of the ship where waves are received, and the upper part of the water from the draft is absorbed by air compression. A shock absorber equipped with a large-capacity tank with a check valve for discharge, and a shock absorber equipped with a communication pipe control valve communicating with the underwater part of the front, rear, left and right tanks is linked to the compression of the tank air, especially at the bow and stern. The vertical flow of the water flow with the difference in the slope of the slope is composed of sailing that absorbs the weight load of the amount of water in the communication pipe and vibration reduction at the time of stopping.
This device and equipment has an appropriate hull shape and the bow is equipped with a large air tank, hydrofoil, or fin, and a pair of controls for either the air tank cylinder anti-vibration device alone, the inboard anti-vibration device, or the wing equipment. A vertical and horizontal anti-vibration device for the hull.
A wide trim hydrofoil above the intake port is slid from the storage part on the deck, and the angle control of the main wing and flap is a vibration reduction device that mainly suppresses speed and roll. The fin stabilizer equipment and trim tab equipment reduce the vertical and horizontal vibrations, and the constant speed of the fin stabilizer equipment and tank cylinder anti-vibration equipment for stormy weather navigation has a low fuel consumption effect. Trim hydrofoil sailing has reduced the speed of the hull from rising and speeded it up, and made the above-mentioned bottom ballast tank buoyancy and trim equipment as another means to reduce the weight of the hull. Even during calm sailing and stormy short-term sailing, pressure is properly sealed in the air tank from the pneumatic unit, compressed air is sealed in the ballast tank at the bottom of the ship, and it is equipped with floating levitation and appropriate trim equipment. Hydrofoils device, and the combination with fins equipped, also in the port and starboard sliding door to eliminate the proper flow resistance and the opening and closing structure of the tank cylinder intake valves remote control.
And it was set as the thing of control from having various control equipment.
For non-regular ocean vessels, there is a sea area with no wave height and a sea area with undulations, and the anti-vibration equipment will be able to travel with sufficient margin from the anti-vibration equipment if the stormy day is 5 days with the planned number of sailing days of 10 days. Therefore, the trim hydrofoil unit and the tank cylinder vibration reduction device were combined with a vibration reduction device on a sunny day due to speed reduction of the hull buoyancy and low fuel consumption.

The invention of claim 1 is mainly described in FIGS. 2, 6, 7 and Example 7,
Most propeller aircraft are turboprop engines, helicopters are turboshaft engines that transmit almost 100% to the rotational force, and the tilt rotor and tilt fan engines of this application are turboshaft engines. An engine was used to make the free turbine chamber an annular slide door structure. And we made a wide-blade small-diameter variable ducted ring rotor blade machine and a multi-blade ring fan blade machine with a smaller diameter. The twin-engine turboshaft engine is fixed at the center of gravity of the fuselage side of the upper left and right main wings, the left and right engines are linked to the shaft, and the variable ducted equipment in the left and right main wings is 2 A wide blade area in the duct equipment that tilts and rotates, with the shaft shaft engaging the ring rotor and ring fan in the duct equipment in the main wing from the speed reduction and direction changing gear equipment, with the inside of the wide main wing fixed axis. The ring rotor blade of 4 to 6 blades with a small diameter is used, the ring frame and the tip of the rotor blade are fixed with a universal joint, and the rotor blade control ring ring variable angle of the rotor hub control mechanism. And variable pitch blade control. Fixed blade fan blades with multi-blade 8 to 20 are equipped with ducted ring fans with smaller calibers, and both blades are equipped with variable ducted equipment from rotation control, vertical, forward and backward inclined levitation and hovering The turboshaft engine is designed to be able to turn left and right. This turboshaft engine has a hub mechanism speed reducer connected to the compressor shaft in the air intake duct, variable pitch front fan blades, 8 to 10 blade blades, and an open / close door. Use a bypass passage for control, a turbofan engine structure that surrounds the compressor, combustion section, and turbine section. The free turbine chamber is a chamber that has a width at the shaft insertion section of the high-pressure turbine. An annular slide in the free turbine chamber with a structure of a circular plate for jetting of air and a structure that smoothly jets into the bypass passage The expansion and contraction of the hydraulic cylinder and the rotation of the hydraulic motor, the expansion and contraction of the electric cylinder and the preliminary mechanical rotation, the rotational force of the ring rotor and ring fan connected to the free turbine and the shaft from the control device of the annular slide door, The ratio of the jet spray output is variable, and the opening and closing of this door is an engine of choice of rotary propulsion and jet propulsion, and an open / close valve provided on the annular sliding door of the free turbine chamber and the bypass part of the front fan as appropriate The jet nozzle from the on-off valve is installed at the appropriate position on the main wing, horizontal tail, etc. to make it an auxiliary equipment for levitation, and switching from hovering ring rotor and fan flight to jet flight is possible with the annular sliding door and front of the free turbine room・ From the fan opening / closing door control, the jet ejection volume gradually increases, and the rotor to the ring rotor and fan The shaft is clutch-stopped, the rotary brake is fixed, the ducted equipment is stored in the main wing of the upper and lower sliding doors, and the free turbine chamber sliding door is fully opened as a turbojet engine, and the variable pitch front fan The air volume adjustment of the two open / close doors of the blade part, the inner surface and the outer surface becomes a bypass ratio engine for jet propulsion with an arbitrary air volume, and it becomes a turbofan engine with a jet propulsion speed of an appropriate turbine rotation that matches the body speed, The ducted equipment is stored, the main wing surface is sealed with the sliding doors on the upper and lower wing surfaces, and it becomes a horizontal take-off and landing aircraft from high speed jet propulsion flight, and the ducted equipment is deployed from the main wing to Half-open controlled flight is a combination of jet propulsion and rotor propulsion. It becomes a BOL prop engine STOL, and the free turbine chamber jet ejection sliding door is fully closed, it is a single flight with ducted equipment, and the flight with low bypass ratio thrust is the turbo shaft engine and turbo fan engine V / STOL aircraft, increased output, control of variable front fan and open / close doors and full opening of annular slide door to turbo jet / after burner engine, equipped with various control devices linked, takeoff and landing and take off The twin-rotor turboshaft engine tilt-rotor aircraft and tilt-fan aircraft that make the ship easier are constructed.
That is, the present invention is a turbo-shaft engine rotor and fan flight and a turbo-jet engine to turbo-fan engine flight, the ducted equipment is not housed in the main wing, and the rotation of the rotor flight is from the turbo-prop engine to the turbo-fan.・ The ratio of rotation and jet propulsion to switch to the engine is variable, and this tilt rotor is a VTOl aircraft of a turboshaft engine in a place without a runway. On the runway, a horizontal takeoff and landing with a turbojet engine In a turboprop engine, it is a short rotor takeoff and landing, a tilt rotor machine in which a small diameter ducked rotor from the wide blade is provided in the main wing, and a multiblade blade with a smaller diameter A small number of passenger aircraft for short-distance transportation of fan machines, places without runways, and existing It will be faster than the existing tilt-rotor aircraft. The free turbine jet engine is the same as the engine installed in the floater of claim 1, and is a fixed, portable prime mover ducted fan that serves as a floating door for the floating volume below the fuselage of claim 2. The equipment was appropriate.

The invention of claim 2 is mainly described in FIGS. 2, 6, 7 and Example 8,
The invention of claim 1 is a ducted ring rotor and ring fan equipment that tilts in the left and right main wings, and the present application eliminates the duct equipment and horizontally fixes the ring rotor and ring fan equipment in the main wing.
The twin-engine turboshaft engine V / STOL airplane is connected to a ring rotor equipped with a speed reduction and direction change equipment, fixed to the main wing, or a ring fan equipped with a shaft to make a vertical levitation aircraft. Fine adjustment control of the stable horizontal levitation of a ring rotor and fan equipped aircraft that does not tilt is provided with an opening / closing valve and an opening / closing valve for the front fan section on the annular slide door of the free turbine chamber of the aforementioned turboshaft engine. The nozzle pipe of the caliber is connected to each part such as the left and right main wings, the tip of the horizontal tail, the tip of the fuselage, and the rear part, and the jet jet outlet of the piping is separately constructed, and the vertical levitation is hovering stable at 70% of both engine outputs. The forward speed increases the engine output, and the jet output gradually increases from the annular slide door and front fan opening / closing control of the free turbine chamber to the forward speed. The rotor and fan equipment are fully open and the clutch is stopped and the rotary brake is fixed. The jet engine from the free turbine chamber of the twin-turbo-turbo engine with the structure of jet flight from the VTOL levitation to the VTOL floating, and the above-mentioned variable pitch and deceleration front fan part inside and outside two It also becomes a low bypass fan engine with an open / close door and fuel adjustment, and the output increase is a turbo-jet afterburner engine with a fully open annular slide door, and the appropriate lower part of the fuselage is used as a volume expansion door for deployment. The fan wind power from the motorized ducted fan equipment is used to assist the levitation force at the time of takeoff departure from the aircraft vertical levitation. Equipped with place. A turboshaft engine that consists of jet flight from VTOL ascent and selection of jet take-off and landing, and open / close control of the free turbine room of an all-weather twin-engine V / STOL aircraft.

The existing steam catapult traction device is a structure of simultaneous propulsion and front wheel catapult traction, in which the piston catapult's traction force wins from the press-fitting of the steam pressure into the piston chamber of the steam cylinder and the fuselage engine propulsion force is delayed. The aircraft and equipment are placed on the catapult tow float base, all the equipment is lifted, all power of the float engine and aircraft engine is moored, and the float upper front catapult and rear brakes and the deck stabilization wheels are free. The unlocking of the float is a device that starts from the simultaneous release of the front traction equipment with the front traction equipment and the nose rises quickly and glide speed, and the front and rear brakes are released, and the air cushion levitates. From the power up of the engine in the float and the fuselage engine.
The existing catapult launching device pulls the nose wheel with the steam piston at the nose, and the aircraft engine is configured to slide the rear wheel at the full power, and when the catapult is released, the glide speed is driven by the power of the aircraft engine. Thus, the catapult bar is automatically released, which inevitably is a balance between securing the steam pressure and amount within the cylinder distance and the engine power. The difference is that it is easy to power up the float engine, and there is a limit to securing the amount of steam pressure.

And this catapult towing levitation propulsion equipment takes a short distance between takeoff and launch, and landing is made on another land, the landing surface of the runway on the ship is a shock absorber surface and a traveling surface surface that travels simultaneously with the aircraft, and the aircraft brake And the brakes on the moving road surface make it a short-distance landing road surface, and the connection part that reduces the shock absorber of the wheel and the load on the fuselage has a replaceable cushioning structure. From the idea of simplifying this equipment, the portable prime mover ducted ring fan equipment has been made an auxiliary equipment for the engine burden of the vertical levitation machine.

The VTOL tilt rotor, fan engine, rotor, and fan equipment are separated, and the free turbine (power turbine) chamber of the turboshaft engine is structured as an engine with an open door jet and a front fan bypass. , Jet flight and rotor flight combined and selected.

And, the trim hydrofoil device and fin equipment that reduce vibration are integrated with the pneumatic and hydraulic shock absorbers of the tank cylinder vibration reduction device, so that civilian ships can be used for light aircraft carriers from vibration reduction, and appropriate VTOL ship-borne aircraft with a hydrostatic linear power generation cylinder equipped with a power generation load that reduces vibrations, and a bottom ballast tank with a pneumatic trim levitating structure at the bottom water intake outlet, with a significant hull speed-up wind pressure. Since the ship's launching speed action will be performed at the same time as the lock is released, it is important to reduce and speed up the hull. Improving the hull launching capability is one solution to this problem. Both anti-vibration devices and fins were installed on various ships.

It is the schematic of the whole fan linear takeoff launching apparatus of a ship-borne machine. [Embodiment 1] (Fig. A) Overall perspective view of air cushion float / catapult traction equipment. (b) A cross-sectional view of the above two methods as seen from the front. (Fig. c) Overall view of magnetic levitation and linear motor catapult traction equipment, mainly with action. (Figure d) Overall view of the action, suction magnetic levitation and linear motor catapult traction equipment. (e) Front perspective sectional view of the above-mentioned two types of air cushion float / catapult traction equipment. (f) Schematic diagram of the launch of the aircraft from the air cushion float / catapult traction equipment of the above two methods. (Fig. g) Schematic perspective view of the fan linear take-off launching device of the ship-borne aircraft from the front. Schematic of deployment of the lower part of the fuselage of the VTOL machine. [Embodiment 2] (Fig. H) Schematic diagram of the airframe floating by installing fixed and portable prime mover ducted fan equipment under the road surface. (i figure) Schematic of the volume door at the bottom of the fuselage of the tilt and fixed rotor and fan machine. (j figure) The top view which expanded the volume door of the lower surface of the said tilt fan machine. Schematic of the entire trim hydrofoil device installed in a slide groove from the bottom side of the ship to the deck. [Example 3] (Fig. K) Schematic of using trunnion-type hydraulic cylinders for strut plates and slide connecting plates for deployment of hydrofoil blades. (Fig. l) Schematic cross-sectional view of the entire hydrofoil equipment with left and right side slide grooves of the hull with varying draft. (m) Schematic of using hydraulic motors for strut plate and slide connecting plate for deployment of hydrofoil blades. (FIG. n) Schematic view from the front of the spur gear and motor gear engagement in the slide groove and the male shaft. (o figure) Schematic of the cross section accommodated in the deck surface from rotation of the hydraulic motor gear equipped with hydrofoil. Schematic diagram of tank cylinder anti-vibration device [Example 4] (Fig. P) Schematic diagram of tank anti-vibration device, side thruster, and ballast tank levitation equipment at the bow of small Vessel V [Examples 4 and 5] (q Figure) Schematic cross-sectional view of the tank shaker and trim hydrofoil device at the bow of a large ship. [Examples 3, 4, 6] (r view) Schematic front view of a tank shaker for draft fluctuation of a large ship. (s figure) The cross-sectional schematic of said tank fluctuation device for trimming fluctuations, and a trim hydrofoil. [Examples 3, 4, and 6] (t diagram) Schematic of a water intake, a tank damping device, and a trim hydrofoil device as viewed from the bottom of a large ship. [Embodiments 3, 4, 6] (Fig. U) Schematic front view of a tank agitator that moves up and down by the wave height of a large ship. (Fig. v) Schematic side view of one form of a large-sized ship's left and right side integrated tank vibration reduction device, fin stabilizer, trim tab, and ballast tank levitation equipment. [Embodiment 6] (Fig. W) Schematic front view of a spherical tank damping device for a large ship. (x) Schematic of the tank damping device and trim hydrofoil described above. [Examples 3, 4, and 6] Schematic of integrated side thruster and tank cylinder anti-vibration device [Embodiment 5] (y diagram) Schematic front view of tank anti-vibration device, side thruster and ballast tank levitation equipment for large ship. [Embodiments 4, 5, 6] (z diagram) Schematic of installation of a tank damping device and a side thruster at the bow of a large ship. Schematic of a tilted rotor and fan machine. [Embodiment 7] (FIG. 1a) Schematic view seen from the front of a tilt duct rotor blade machine. (Figure 2b) Schematic view from the front of the tilt ducted fan blade machine. (Fig. 3c) A schematic plan view of a tilt ducted rotor machine. (FIG. 4d) Schematic front view of tilt ducted rotor and fan machine. (FIG. 5e) Schematic of the wire structure of the sliding door of the duct part in the main wing of the tilt ducted rotor and fan machine. (Fig. 6f) Schematic plan view of the structure of the sliding door of the main duct of the tilt ducted rotor and fan machine. (Figure 7g) Schematic of the structure of a tilted rotor and fan turboshaft engine. (Fig. 8h) Schematic of the structure as seen from the front of the tilt ducted rotor and fan machine. Schematic of a ring rotor and ring fan equipped machine that is horizontally fixed in the main wing. [Eighth Embodiment] (FIG. 9i) A schematic plan view of a ring wide rotor machine. (Fig. 10j) A schematic plan view of the opening of the body lower volume door of the ring fan machine. (Fig. 11k) A schematic diagram of a sliding door equipped with a ring fan on the lower main wing surface. (Fig. 12l) Schematic diagram of the structure of a ring rotor, turbomachine of a fan machine. (Fig. 13m) Schematic view from the front of the fuselage deployment door and fan levitation equipment of a ring rotor and ring fan equipment. (FIG. 14n) The front view which stored the fuselage expansion | deployment door of said ring rotor and a ring fan equipment. (Fig. 15o) A schematic front view of the fuselage lower unfolding door. Schematic of remote hydraulic control of trim hydrofoil device, fin stabilizers, trim tabs, and automatic hydraulic control circuit of tank cylinder vibration reduction device. [Examples 3, 4, 5, 6] (Fig. 16p) A control circuit diagram of a trunnion hydraulic cylinder for deployment and folding of a hydrofoil plate of a trim hydrofoil device. (Fig. 17q) The same control circuit diagram from the draft to the deck as above for the hydraulic motor gear. (Fig. 18r) Schematic circuit diagram for controlling the hydrofoil front and rear flaps with a hydraulic cylinder. (FIG. 19s) Schematic diagram of a pneumatic filling configuration into the air tank and the bottom ballast tank of the tank cylinder attenuator. (Fig. 20t) Simplified overall control schematic diagram of various hydraulic actuators with electronic control to cope with the changes in the flap wave of the fin equipped with the same control method as the trim hydrofoil device on the left and right side, the tank damping device, and the hydrofoil .

  This will be described based on the drawings and reference numerals.

(Fig. 1) (f, g diagram) is the air cushion launching equipment of the carrier aircraft (P), with the catapult air cushion float base (A) equipment on the sliding deck (I) of (a). FIG. 2 is a schematic view of a ship with an air cushion levitation propulsion engine and a fuselage engine provided with two turboshaft engines (B) in the center of the float.
Assuming a fuselage weight of 25t and a total float weight of 5t, the float area and volume is 15m long, the floating area of 2m wide is 30m2 and the capacity is 25m3. A 3000kW free turbine and a 2-shaft shaft are connected to the float side with a reverse jet duct and fan, and 100% of the engine output is used as the fan rotational force. The air volume and pressure is 90 m, about 20 m3 / s and 0.03 MPa. Air cushion levitation is achieved by eliminating the leakage of the hull sliding and heat-resistant fluorine plastic flat road surface and seal material (E), and the material is the skirt material of the air cushion boat (urethane) System, PVC system, nylon system, etc.) are made of elastomer material that is almost the same material, and can be exchanged at multiple launches.Starting from stop levitation, the free turbine chamber (X) covers the cover surface. Heat resistant, pressure resistant metal annular slide (Y), the annular outer frame material (Z) is a free-turbine chamber with a support base structure and a fully open distance of about 3 to 10 cm slide of this annular door, and the ratio of fan and jet propulsion by opening and closing the door Remote controlled hydraulic actuator with variable structure, telescopic and rotating configuration with fine adjustment of electric cylinder, machine operation to avoid heat, free turbine connection with front compression turbine The structure of the fluid clutch is such that the free turbine blade plate is a free turbine chamber with a circular plate (29) width that opens and closes when opened and closed, and smoothly bypasses the rear by opening and closing the sliding door. The structure is a structure that does not leak from the door. The turbojet afterburner engine (57), which is appropriately formed with the launch float of various aircraft and large aircraft, makes the jet thrust 10t from the float rise to 13t, and the output ratio is 70-80%. The air leakage of the gliding was replenished and the catapult front wheel was pulled. 20% of the weight received by the front wheels and 80% of the weight of the rear wheels, and the weight 20t of the rear wheels of the fuselage is the stability wheels on the left and right deck surfaces sandwiching the rear float stand and the fuselage on the top surface of the float Received by the suspension support wheel, the float table of the front wheel part of the catapult towing and the float part of the rear wheel part communicate with each other, the total equipment weight 30t becomes the air cushion levitation, and all equipment floats without mechanical resistance It was assumed to have a configuration.
The traction catapult traction equipment shown in the lower diagram of (b, e) has the front wheel on the center of the float by reducing the opening width of the traction catapult on the deck surface and the float plate surface (A1) that can be used for various aircraft. The width of the tow catapult plate (61) that receives the weight of the aircraft of the catapult and the rear wheel is set to a straight opening width of about 3 cm to 10 cm, and the width and length of the plate on which the aircraft is placed on the tow straight plate (61) of this width To the float plate surface (A1) integrated with the float on which large and small aircraft are mounted, and small wheels (59) are provided on the deck surface on the left and right sides of this float plate surface, and stable levitation running, All equipment is floated.
In addition, the remote control air supply valve (N) at the upper part of the float is appropriately opened and closed.The rear part of the fuselage (Fig.g) is used as an open / close volume door, and the rear part of the fuselage is lifted by wind pressure from the soft material (O). did.
And by using an appropriate pneumatic float stand together with magnetic levitation (M), almost all equipment becomes stable levitation, mechanical resistance is almost eliminated, and the aircraft engine thrust in the float is 6t and the engine thrust in the float is 10t. The propulsion configuration was set to start with full power at the same time.
And the towing catapult distance is about 100m at maximum, the ship speed is set at a minimum of about 30m, and the brake structure and the tip part gradually reduce the speed by sandwiching it with multiple cushion tires (G) on the side at a position of about 50m Equipped with a reverse injection valve (H) for automatic contact.
When starting off, the release of the mooring lock (D) for remote control of the float base (A) and the float plate surface (A1), the aircraft wheel catapult is automatically released, and the rear support wheel brake is released manually and with the front wheel catapult. Automatic release of linkage. From the one that accelerates the speed of the launch at the same time as the launch, the main structure is automatic operation. In addition, this traction float engine has one or two engines arranged side by side and various spare engines and an aircraft with a body weight of 50 tons are interchangeable with the engine of the lift and afterburner thrust. J) was installed, and the anti-sway cushion wheels (G) were provided on the left and right sides of the fuselage.

(Figs. c and d): Float platform and road surface are magnetic levitation (M) and linear motor (L) traction, turboshaft engine fan levitation and propulsive force, and appropriately open / close volume of rear fuselage Float open / close air supply duct rear wheel floating configuration, and front wheel catapult traction force uses the AC high output vector control inverter VVVF synchronous (induction) linear motor of the ground primary type linear motor installed on the catapult float base and side wall Then, the cushion tire on the side wall for stopping is eliminated, and the jet propulsion and the linear motor propulsion are employed, and the schematic diagram is of a sudden stop structure.
And, it is composed of a combination of a powerful fixed electromagnet and coil armature, or a coil field element, and the road surface and float base are repulsive magnetic levitation and suction levitation and linear motor (L) of forward and backward movement, the technology is The output of the existing linear motor train specification is increased, and the propulsion power of the fuselage engine is configured by using the above-mentioned fan levitation, jet propulsion catapult traction equipment, and optionally a linear motor.
The combined launch system is an optimal equipment suitable for various ships, is a linear motor that uses air pressure instead of complicated superconducting magnetic levitation linear motor equipment, and VTOL by opening and closing the air supply valve of the float part Wind levitation assistance equipment on the fuselage deployment door.
And if you have a simple magnetic levitation and jet engine equipment or an air cushion and engine float traction equipment under the runway surface of a landliner, etc., and an auxiliary take-off equipment at the start, you can take off on a short runway The landing is affected by the weather, but the landing road surface is a shock absorber (58), and the landing surface is a section of air cushion float, wheel float, magnetic levitation float, linear motor (power generation) float with an appropriate area, Mounted on the float section from the landing road surface, the rear weight is set to a speed integrated with the float section, and the small and lightweight aircraft is configured to be mounted on the next light float, engine in the float, magnetic levitation, linear motor machine The box should be box-type traction equipment that does not touch the lower part of the road surface. By using various brakes on the road surface, the actual take-off and landing distance will be about 200 m. The float thickness is as thin as possible for large machine floats. I made it to a float base with a structure that does not bear the burden of the aircraft due to the inclination of the tip part by oversliding, making it about 15 cm with a lightweight aircraft.

The launching device of about 2 seconds increases the gravity load of the pilot, the front wheel towing catapult coupling device from the ascent to the automatic release configuration, and the appropriate rear fuselage volume door automatically closes, In order to achieve a glide with a 50m run, it is impossible to control the acceleration weight in only 1 to 2 seconds, and the pilot can only monitor the instrument at the start of the ship. From start to gliding, automatic control should be prioritized. Manual control can be performed by checking lift wings, pre-sliding engine and various control systems, checking automatic and manual release wheel brakes, and catapult personnel. Only mooring lock (D) for shared remote operation was released.
Wind pressure, wind direction and air volume change due to changes in ship speed and speed at the time of start, the contact surface of the main wing changes, the catapult personnel are from the start judgment of various weighing instruments and various monitoring equipment of the float table, and The landing method of hanging the aircraft hook on the wire is the same, and the deck and landing road surface are made of fluid springs, rigid springs, shock absorber shock absorber surfaces (58) to reduce the load on the aircraft As for the ship, the landing was related to the pilot's proficiency, but it was assumed to have a steering assist structure.
The ship's catapult float part with a simple opening on the deck surface described in (a, c) has a complete cover (K) structure, and if the ship's air cushion and rigid spring float deck are used, the captain will be about 200m It becomes an aircraft carrier, and the configuration of the current aircraft carrier will change from the installation of the hydrofoil device and tank cylinder anti-vibration device and the cylinder cylinder anti-vibration device to ascend, trim, reduce vibration and speed up.

[Fig. 2] V / STOL aircraft are used for small aircraft carriers, helicopter light aircraft carriers, etc., and the turbocharged jet engine engine (Q) is assumed to have the full weight of the bypass ratio. All of the turbofan thrust that is levitated is propelled to the bottom, and this fan thrust is the engine load. It is operated as. Therefore, the present application is based on a plurality of prime mover ducted fan equipment (R) provided under the deck and under the road surface with the VTOL machine as a deployment door (V) on the lower surface of the fuselage, and a pressure receiving surface and a volume part receiving wind force. The soft material (O) is extended on the road surface, and the fan wind pressure assists the levitation force at the time of takeoff departure of the aircraft vertical levitation turbofan engine, and reduces the impact load on the aircraft at the time of vertical landing landing It is an auxiliary equipment for ascending and landing from the motorized ducted fan equipment, and it is equipped with the air cushion float engine (B) and the air supply duct equipment, and it is easy to take off and landing at any place with the aforementioned ship. It was portable.

The trim hydrofoil device of Patent Document 7 aims to reduce the vibration and improve the speed and fuel consumption of a configuration in which the hydrofoil plate is hinged to the dredger of the large steel ship described in claims 1 to 3 and is folded and deployed. It is a thing.
The hull form for speed is not limited to the size of the ship, it has a hull structure with the bow rising as the output increases. Therefore, a hydrofoil for trim purposes is also provided at the stern, or the center of the hull's center of gravity is a single hydrofoil, which inevitably speeds up. The purpose of connecting with is a hydrofoil blade with a wide area and folding and a free-angle hydrofoil deployment plate, and flap control and wing surface control are speedup and vertical and horizontal vibration reduction.
The steel welding is fixed to the underwater part of the left and right sides of the waterfoil, which is the base of a hydrofoil that receives a high speed of 30 knots and top and bottom waves, and the double-triple safety and the rotating hinge part as a cushion part such as a rubber ring. The flaps were controlled manually and automatically, and the swinging was controlled by vertical control of the hydrofoil surface.
In addition, it is difficult to control the vertical and horizontal shaking of the large ship, which is common with the present application, and it is based on speed control and advancing angle, and at the same time, the vertical (pitching) and horizontal (rolling) swing control is different from an airplane. Therefore, the hydrofoil can not withstand the vertical and horizontal water pressure and resistance of the hydrofoil that secures the area. To control the left and right blade flaps before and after (Fig. 18r), the vertical and horizontal swings and the optimal travel angle (Fig. 20t) are input to the electronic control unit (48). It was linked to the gyro sensor (47) and automatically controlled by the hydraulic cylinders (51, 52) in the main wing from the solenoid valves from the left and right hydraulic pump units.

[Fig. 3] (k, l, m diagrams) shows the purpose of using a carrier with a difference in draft between the full load and the empty ship and a small ship as a carrier and reducing and speeding up underwater when landing. The wing equipment is equipped with a slide groove (5) of the support plate (2) on the side of the bottom of the ship from the deck, and the support plate is lowered from the dredging on the upper surface to an arbitrary position under the draft. The hinge-connected hydrofoil plate (1) has an area and strength structure, and the strut plate slide female groove (Fig. N) from the vertical movement of the male shaft of the slide connection plate (8) to the four-bar link support fixing plate (9) Folding and the development of hydrofoil blades, the hydrofoil blade area is a hydrofoil plate with a width and length proportional to the support fixing plate, and the male or female shaft of the slide connection plate (Fig. 16p) is The expansion and contraction control of the cylinder rod can be folded by connecting it with multiple trunnion type hydraulic cylinders (4) or double-acting hydraulic cylinders with universal joints fixed from the top, bottom or bottom of the column plate. Or the slide groove of (Fig. 17q) is constructed from the engagement of single and plural hydraulic motor gears (13) on the slide coupling plate of the spur gear and the slide rotation of the male shaft, except when necessary As a thing of the trim hydrofoil device stored in the water,

The folding and unfolding structure is the same as in Patent Document 7, but the difference is that there is a groove that slides the column plate of (k, m figure) from the bottom side of the draft to the deck surface with the hydraulic motor (7). The inside of this groove is a spur gear, and the mounting part of the deck and deck deck is a round rotating slide groove structure, and a plurality of hydraulic motor gears (13) and male shafts provided at appropriate positions on the support plate are used as the rotation axis. With the vertical rotation structure, the storage configuration on the deck is the male surface (11) of the hydrofoil hinge part of the strut plate, the male surface (10) of the strut intermediate link part, the center part of the strut and A plurality of male surfaces (12) depending on a column area of the column plate are configured to be disengaged from the groove portion, and a column plate is configured to be slid and accommodated on the deck by rotating a plurality of hydraulic motors.
Then, the strut plate is rotated from the deck to the scissors and engaged with the slide groove to develop the hydrofoil. The water pressure and wave resistance make the slide trough grooves female width, and the strut plate rail is male width. In each hydraulic motor (7), it is not sufficient to stop the flow of the control valve alone so that the upper and lower hinge portions, the hydraulic motor portion, and the plurality of intermediate male surfaces of the supporting column receive wave forces. Then, the drum was installed and closed with the brake band (25) of the hydraulic cylinder, and the fixed configuration was adopted. For speed sailing and vertical and horizontal vibration reduction, a hydrofoil device that slides to an appropriate draft position that matches the ship and the wave height with the fluctuation range of the draft surface is made with a hydrofoil with a larger bow than the stern. .

And with the front edge and rear edge flaps (6) or the tip of one flap, the vertical and horizontal vibrations are controlled by the main blade angle, and the control method is the existing technology of Fig. 20t. The same as the fins and stabilizers of existing hydrofoil ships, gyroscopes, pressure sensors, etc., and the right and left and front and rear main wings and flaps of each of the computer controlled sensor switches are operated appropriately. For example, the control of the main surface of the hydrofoil swaying rolls the hydrofoil angle of the right and left side of the optimal course, and makes the wave angle almost constant to suppress the wave cycle. The front / rear and front end flaps are integrated with the flexible connecting shaft that can be folded together with the main wing, and the front and rear flaps are automatically controlled. The front and rear flaps are connected with a pair of rod cylinders inside the main wing. Bei was. The pitch is from the optimal trim wing surface angle and ascent speed, and the flap is the main control of ascent and roll, and the bow wing surface from the speed up is almost horizontal angle to the stern. The control method of the resistance angle of raising and lowering the main wing surface from the horizontal angle was used, and the vertical and horizontal swing control mode was selected mainly. And when launching and landing an airplane in stormy weather, sail toward the wind and use the hydrofoil angle and flap angle that match the direction of the waves at that time, and reduce the pitching described later. The main tank cylinder vibration reduction device was mainly used, and the hydrofoil was used in combination with the wave height.

Hydrofoil blades with a lift structure are made of metal plates (aluminum, stainless steel, steel), which are bonded to hard plastic or elastomeric lift plates and made into metal flying wing shapes. At the time of departure, speed 40 knots due to hydrofoil cruising results in a wind speed of 25 m / s, and the acceleration start at 100 m / h between 20 m from the aircraft's levitation float and synthesis with ship speed 170km / h, wind speed from the front is 60m / s, and the propulsive force can be launched at a distance of about 30m from the main wing lift. And the glide from the surface of the 25t aircraft was affected by the waves, and the hull reduction device was necessary, and the vertical takeoff and landing jet fighter launches and landings were also turbocharged vertically. Hovering for a short time with high airflow from the fan engine is suitable for the hull swaying, reducing the shock of leaving the ship and saving fuel.

[Fig. 4] is provided with single and multiple hydraulic pipe intakes (15) that take in the water current and water pressure due to the ship speed and the horizontal and vertical water pressures on the ship bottom and dredging side using wave power of the open ocean. Manual, electric, and hydraulic remote control valves (butterfly valves, ball valves, etc.) (45) from the shipboard are used as intakes on the hydraulic cylinder, and large volumes of air in various shapes to suit the ship's structure between the draft and the water It is a tank cylinder vibration reduction device connected to the tank (16), and an air suction check valve (17) and a discharge check valve (18) are provided on the upper surface of the air tank. The draft surface is a piston, or the area of the hull weight on the tank is a piston, which compresses the air in the tank above the draft, and the air pressure suppresses the vertical movement of the hull. One or more intake pipe diameters of 0.7m, tank Assuming the air volume of 5.0m from the surface of 100m2 of water, the vertical shaking of the 3.0m hull due to waves at 1.000.000cm2 is assumed to be 1000m2 assuming that the ship's bottom area at the bow is 20m wide and 50m long Assuming that the bottom of the ship is moving up and down by an average of 3m alternately from the center of gravity and back and forth, and the tank bottom surface at the tip of the tank is 10.000t, the air tank area of the left and right side for rolling Is about one-fifth the area of 200m2 with respect to the bottom of the ship, and the water flow pressure due to the ship speed will be described later, and the above-mentioned 500m3 air volume 3m compression is about 0.15MPa. The air pressure piston device is repelled from the compression of the air in the tank, and the check valve of the tank has an appropriately set adjustment pressure of 0.10 MPa. Rebound from the compression of wave height and swell hull up-and-down movement and the shock of rebound are simultaneously absorbed by the discharge valve. Attenuation and negative pressure are shock absorber tanks of automatic atmospheric pressure check valve, and it becomes a vibration reduction device from about 30% attenuation. When descending, the stern rises and repeats alternately, and many hulls have a large area at the bow due to the position of the engine and the forward hold structure, and the tank at the stern has an appropriate shape that is smaller than the bow. Therefore, the hull of the full tanker (e.g. r, s) and the draft surface of the empty ship with the draft surface changed to a vertically long tank, and the 3m wave height from the high-pressure air unit (46) (p. 19s). Up and down movement, as well as good weather due to the pressure of the speed of the ship speed, air pressure 0.10 to 0.15 of the assumed ship speed pressure in the four air tanks (16) on the bow and stern draft of the up and down movement in stormy weather A safety valve type in which MPa is sealed and the suction and discharge check valves are set to the pressure, or the sealed pressure is maintained. With this air pressure sealed near the bottom of the tank and supported by ship speed water flow pressure, the hull has a buoyancy of 6.000 tons, and the water pressure increases further, the air pressure increases, and the air pressure increases further. 10% of the total weight of the assumed unloaded hull weight of 50.000t will surface, and the hull will rise about 1m.
And the rocking bow, stern, and left and right tank cylinders communicate with each other under draft, and a remote control valve (21) is provided in the communication pipe (19, 20), and the extension rod on the deck is operated manually and hydraulically. In the case of stormy weather, the flow load of the water flow pipe in the control of the electric actuator is a weight load that increases the water volume between the tanks with the wave height and the degree of inclination of the swell, and the load of the flow adjustment is shock It became an absorber and a remote control valve linked to the tank air pressure.
Adjusting the discharge pressure setting of the shock absorber of the air tank due to wave height and swell, the filling pressure injected into each tank capacity of each hull during navigation during calm times, and the tank filling pressure changed at the time when the speed was reduced during stormy weather. By compressing and attenuating the sealed air pressure at the wave height, it becomes a damped air pressure tank with an effect proportional to the ship bottom pressure receiving area, and the suction and discharge check valves are set as safety valves.
In particular, the pitching of the hull reduces the load because the tip of the hull enters the underwater and the dredging of the dredger keeps the propulsion unevenness that rises, suppresses air entrainment, and keeps the engine rotation constant, In particular, when the speed of a sailing ship that stabilizes the draft surface is almost constant and the speed of the sailing ship is stable and the draft rises and falls, especially when empty ships such as large oil tankers,
Although the navigation time is slightly reduced, the emission gas and fuel costs are reduced. When installed on a small aircraft carrier, the width of stormy ships is widened, and the existing tankers described in (p, v, y) The double bottom ballast tank (44) of existing ships such as ships, container ships, passenger ships, ferries and small FRP ships is made into a pneumatic trim tank that floats on the hull, and the bottom of the ballast tank is extended from the deck. A manual and electric / hydraulic intake remote valve (45) is installed on the rod shaft, floats with high-pressure air from the high-pressure air unit (46), and discharges into a ballast tank for water intake. A ballast tank of 2.000m3 with an area of 2.000m2 and 0.1Mpa sealed will be a 2.000t bow, stern trim levitation and weight hull, the ballast weight can be easily adjusted, and a 15t FRP ship. The bottom ballast tank and the front and rear pneumatic tanks A tank with a surface area of about 5m2 and a volume of 2.0m3 will be used as a floating and anti-vibration tank when the ship's velocity and pressure are taken from the intake. And the buoyancy equipment of the trim adjustment ballast tank water intake and drainage equipment by air intake and drainage from the bottom of large and small ships.
In passenger ships, seasickness is the suppression of vertical and horizontal swings, vertical and horizontal movements, the size of the hull, the type of ship, and the shape of the hull, and the shape of the waves, the fluctuations received vary, and it can reduce any waves. The device is not possible, and the small FRP ship (p.p.) is a light hull that prioritizes speed, and the tank cylinder vibration reduction device functions with the speed of the wave shape and the wave height. The bow and stern are structured so that the bow part rises from the output increase, and the communication pipe is appropriately reduced under draft, and high-pressure air is sealed in the bow and stern tank at the time of sailing, It is faster from any levitation and front / rear trim, and is similar on large ships, as well as the trim hydrofoil device (q, s, x) and (u, v). Fin equipment and anti-vibration tank equipment on board, gyro stabilizer on board Use the Bei, and corresponds to the shaking of the vertical and horizontal directions in combination.
From the existing propulsion shaft ship to the stern electric propulsion screw pod ship, from the inboard electric motor shaft to the upper and lower screw hydraulic equipment that lowers the screw shaft below the bottom of the ship, and from the flat (slightly inclined) stern bottom stern of the draft Z propeller ship (azimuth thruster) eliminates air entrainment, speeds up due to stable propulsion and high-pressure air levitation and anti-vibration effect in the air tank, and requires ballast water in the screw lifting device. Disappear.

One anti-vibration tank cylinder is provided at the bow and stern for the purpose of reducing the pitching, and it is provided at the center of the left and right side, and the roll is controlled by hull width, bilge keel, fin stabilizer, gyro It can be supported by the stabilizer equipment, the hydrofoil device of this application, etc., and the side thruster (23) of the current ship of [Fig. 4, 5] (p, y, z diagram) and the tank shaker are installed at the same position. The tank cylinder anti-vibration device is equipped with an air tank (22) connected to the hydraulic cylinder at the center of the bow and the tip of the stern at an appropriate angle with respect to the direction of travel of the hull, and the remote intake valve (45) The bottom of the ship, the bottom side of the ship, or the left and right side of the tank is made into a water intake (16), the intake and discharge of the side thruster are made the same as the intake of the tank cylinder, and the upper surface of the propeller blade is the intake of the tank cylinder. In the structure of Or a tank cylinder that has no influence on the discharge capacity and communicates with the water intake on the bottom of the tank cylinder. By making the tank large and flat before and after the air pressure part and making the bow area large, the vibration reduction effect is improved, and a suction check valve and a discharge pressure adjustment check valve are provided on the deck from the top of the tank The bow and stern tanks communicate with each other under draft, and the above-mentioned communication pipe is provided with a remote control valve so that the compression of the tank air volume and the flow of the communication pipe are linked in the vertical direction. It becomes a shock absorber for damping vibration, and the air pressure between the bottom of the ship and the tank plane due to hydraulic pressure is proportional. Large to match the course, ship speed, wind and swell For small vessels, discharge pressure setting, communication pipe water flow control, high pressure air is appropriately sealed in the air tank, high pressure air is appropriately sealed in the ballast tank described in Example 4, and right and left side opening Is a remote sliding door, speeding up, reducing fuel consumption and shaking, and a tank cylinder vibration reduction device that is installed at the same position as the side thruster and at the water intake outlet.

Ships equipped with the main tank cylinder vibration reduction device and roll trim hydrofoil device of [Figs. 3 and 4] are installed on the bow and stern bottoms and on the left and right sides of the bottom of the ship and on the side ridge (Fig.m) both have a hydrofoil that slides at the same position on the upper part, and the fin equipment for small area for stormy weather (Fig.v) is a pair of vertical and horizontal reductions from the combined use with the tank cylinder anti-vibration device. Rolling of storage and deployment from the inside of the anchor at the top of the bow intake (15), which is the swing device, with the main fin stabilizer (42) and storage and deployment at the top of the stern intake The trim hydrofoil device is equipped with the main trim tab equipment (43) for stormy weather waves, folded from an appropriate angle in the state of waves in (q), and slidably stored on the water deck with a hydraulic actuator. Then, the hydrofoil blade (1) and the hinged strut plate (2) The male and female fasteners are formed in the gutter slide groove, and the wing device and fin equipment are equipment for cruising, existing control equipment and technical scope, and are used for anchoring and cruising for stormy weather. The tank cylinder anti-vibration device of both effects is the trim hydrofoil main wing with the hydraulic pipe cylinder remote control valve (45) as appropriate, with the single and multiple intakes of the vertical and horizontal sides at the proper angle on the bottom and side of the bottom It is assumed that the surface and the front and rear flaps (6) are at the angle of intake suction at an appropriate ship speed and flow rate, and that both devices receive the hull shape and waves in the traveling direction from the bow and oblique angles, and from the center of gravity position to the bow. The appropriate bow is installed from the distance of the stern, and it is installed at the appropriate position to receive the waves.The compression of the upper air in the air tank is made up of the suction check valve (17) and the discharge check valve (18). Adjust pressure valve, front and rear, right and left tank cylinders The communication pipe is provided with the above-mentioned remote control valve (21), and the compression of air and the water flow load on the top and bottom of the communication pipe, or the water flow load on the left and right, are reduced from the linkage during stormy weather to the damping shock absorber. The fin stabilizer equipment and the trim tab equipment of the fin equipment are existing technologies for stormy weather, and the ship equipped with either the tank hydrostatic device or the trim hydrofoil device or the fin equipment. And, as mentioned above, high-pressure air is enclosed in the tank appropriately to make the hull buoyancy and trim configuration, and the air compression of the pitching tank and the reduced sailing of the hydrofoil or fins reduce the fuel consumption from the constant speed, and the constant course It becomes an anti-vibration device that increases the average speed from vertical and horizontal vibration reduction, and there are waves in front and behind the fine weather, rough weather, wave height, swell, wind wave and heading, and hydrofoil equipment is used when sailing The on-board fluid tank anti-vibration equipment, the solid movement anti-vibration equipment, and the on-board gyro-stabilizer anti-vibration device are for both sides of the on-board It is an outboard equipment, and when used in combination with a tank cylinder vibration reduction device, the vertical and horizontal vibration reduction effect is large. .
Waves are characterized by the wind waves of the Sea of Japan in the winter near Japan and the swell of the Pacific Ocean in the summer.The waves are almost the same overseas, and the pitch of about 50,000 tons of medium-sized passenger ships described in (20t figure) In rolling vibration reduction, the air tank cylinder vibration reduction device and trim hydrofoil cruising at a speed of 20 knots are assumed to have a vertical and horizontal wave height of 3 m and 30% vibration reduction with the tank cylinder vibration reduction device described in Example 4. And 20% buoyancy, and the trim hydrofoil device of Example 3 has a 20% speedup from trimming pitch reduction and suppression of flap control rolls, or almost vertical and horizontal oscillations from fin equipment. The ship's ballast tank described in Example 4 is filled with high-pressure air, and the cruise with 10% of the hull weight trimmed appropriately, tank cylinder vibration reduction device, trim hydrofoil device and fin, tab equipment Vessels equipped with various onboard anti-vibration equipment, various equipment It was of swinging motion reducing apparatus comprising a substantial swinging motion reducing the speed and low fuel consumption of a combination.

The propeller aircraft is a turboprop engine and the large helicopter is a turboshaft engine. [Fig. 6] (Figs. 1a, 2b, 8h) The machine has a turboshaft engine (B) fixed to the top of the main wing, and a free turbine and a two-shaft front shaft reduction and direction change (36) mechanism with a ducted ring rotor and fan-equipped ring in the left and right main wings A wide rotor blade (U) frame and a multi-blade ring fan blade (T) frame, which are configured to be sealed with a sliding door (28) in the upper and lower main wings of (5e, 6f), and the free turbine chamber of (7g) The (X) annular sliding door (Y) is a hydraulic cylinder, motor or electric cylinder, motor and spare mechanical manual opening / closing structure.・ D The front fan blade hub device (35) with variable pitch and speed reduction in the air intake duct connected to the compressor shaft is provided with an open / close door (flap) (32) in the bypass passage from the combustor. The free turbine chamber (X) that is fluidly connected to the compression turbine section is a chamber for the free turbine circumferential plate (29) that is set at a slight distance from the structure in which it is opened by the annular sliding door (Y) for jet ejection. Using the bypass passage (31) as a support frame, the open / close door (32) is fully opened and the free turbine sliding door is fully opened, which is a low bypass turbofan engine.・ Rotation of the engine rotor and fan.
The annular sliding door (Y), the variable output of the front fan, the fine opening / closing of the inner open / close door (32) and the outer open / close door (56) are in the form of any of the above jet engines, The output increase is the turbojet afterburner engine (57), and horizontal takeoff and landing can be done with both rotary propulsion force and jet propulsion engine configuration, and the speed of horizontal flight will be increased, and it will be an all-weather type vertical takeoff and landing aircraft .

And, the assumed aircraft weight is 30 tons, and the twin-tilt turbo engine with a 30-crew engine is equipped with a free turbine and a variable ducted ring rotor with a shaft connection. The ring fan equipment will be smaller, with a maximum of about 5.0M, and will be a vertical and horizontal take-off and landing tilt rotor and fan machine that will fit in a main wing with a maximum front and rear width of about 70cm and a maximum height of about 70cm.
In the ring rotor machine of the above-described rotor hub control mechanism (39), the fixed ring fan blades of the multi-blade 8 to 20 are equipped with a ducted ring fan having a smaller caliber for variable angle and variable pitch blade control.
Featuring the convenience of the helicopter and the noise and noise countermeasures of the turbofan engine machine for horizontal flight, the tilt-rotor for storing the all-weather type, and the fan equipped turbojet engine jet.
The twin-engine tilt-rotor machine, which will be a V / STOL machine, is equipped with a lifted blade with a ring-wide rotor area and a variable ducted rotor with a small diameter, and the turboshaft engine is suitable for the center of gravity moment of the upper left and right main wings. The lift configuration provided at the position, the variable ducted rotor equipment, the configuration that fits in the main wing outside the engine, the variable rotation of the hydraulic motor at an appropriate angle above and below the variable duct with the left and right bearings (41), and the variable duct The ring rotor equipment that rotates inside is connected to the variable gearbox of the drive shaft from the shift and direction change mechanism at the front of the engine, and the ring rotor equipment of the left and right main wings is connected to the shaft so that one engine output at the time of failure The main wing area can be used for rotor flight landing and jet flight, and model selection based on engine output and fuel consumption is based on helicopters and propellers. Compared to jet aircraft, this is an efficient one, and this application is a tilt-rotor machine in which a variable duct is housed in the main wing with a rotating hydraulic device for duct, and the above-mentioned appropriate fuselage lower surface is a volume wind power deployment door (V), and a fixed and portable prime mover equipped with a ducted fan (R) with a wind-assisted levitation configuration.

And the ring rotor equipment can move backwards and swivels from ascending levitation from a wide area of the blade angle and variable duct, and can perform vertical and water smooth running and landing, and from the vertical takeoff gradually to the horizontal flight at the same time During horizontal cruise flight, switch from turboprop flight to turbojet flight, and the adjustment control of the annular slide door is the rotor rotation and jet ratio, and the ring rotor rotation is stopped by the clutch stop (38). With the rotary brake (40) fixed, it becomes turbojet engine flight when fully open, and it becomes a tilt-rotor machine when fully closed and clutch input.
During turbojet flight, the variable ducted rotor equipment part slides the sliding door (28) of the main wing from the fuselage internal storage on the upper part of the fuselage and the lower part of the left and right main wings to the wing circumference of the duct frame (W). The support slide deployment frame (54) of the hydraulic / pneumatic cylinder deployment from the circumference of the main wing is used as a guide and support, and electric or hydraulic motor winches are installed at appropriate positions on the main wing and fuselage, and the upper and lower slide cover doors are connected with wires. The winding wings are sealed and opened or closed by winding up two interlocking winches around the entire circumference, or by expanding and contracting multiple hydraulic telescopic cylinders. The entire area of the left and right main wings will be enough to lift and increase the speed. Also, the airplane will be a short-distance section of rotor, fan rotation and jet propulsion, and a medium-distance section of jet propulsion, and the landing will be made by horizontally landing the turbojet with the sliding door closed or switching to the ducted rotor flight. The blades from the ring rotor consist of vertical takeoff and landing in a place without a runway, horizontal takeoff and landing on the runway, and short takeoff and landing at the fuselage expansion volume door of the V / STOL aircraft described above. This is a tilt-rotor machine with a small caliber ducked rotor.

And, it is possible to take off and landing from any land and indoors from a small ship, and a large sized equipped with a variable ducted rotor on the main wing and a small ducked rotor on the left and right of the fuselage, or a turbofan engine In the configuration of vertical take-off and landing of passengers and transport aircraft 50t, the opening and closing valve (33) of the sliding door (Y) of the free turbine room and the opening and closing valve (55) on the front fan bypass opening and closing door (32) as appropriate A jet nozzle (37) with various calibers is provided at appropriate positions on the fuselage, main wing, horizontal tail, etc. to assist in ascent.
The tilt-rotor and turbine jet engines add speed to the convenience of the helicopter, ensuring speed and safety.
The current tilt-rotor machine is an integrated engine and rotor blade, and the fixed main wing and the engine must be variably controlled from the mechanism where the engine is variable by about 100 degrees. The difference between maneuverability and safety is obvious when compared with the fact that it is an engine-fixed machine and jet flight is used for cruise flight, and the STOL sliding take-off and landing of the turboprop flight reduces noise and improves fuel efficiency. Tilt rotor machine.

Unlike the helicopter rotor blades and propeller airplane blades, the ring rotor and fan equipment of (1a, 2b) can be made smaller in diameter, and as a propeller that can be fixed separately on the shaft connection with the turboprop engine, Since it is housed in the main wing, the thickness and width of the main wing are inevitably widened, and the mechanism ensures the strength of the tip.The fuselage, the left and right main wing frames, and the duct frame frame are made of an integral metal frame. The tip of the main wing is structured to draw a frame such as a wire or piano wire.

The ducted ring rotor that tilts in the left and right main wings and fan equipment (S1) described in Example 7 is eliminated, and the ring rotor and fan equipment (S2) of [Fig. 7] is horizontally fixed vertically in the main wing. In order to control fine adjustment of the aircraft's stable horizontal levitation, open / close valves (33) are installed in the annular slide doors of the free turbine chambers of the left and right turboshaft engines described above, and nozzle ports (37 ) And the nozzle opening (37) of the opening / closing valve (55) and the opening / closing valve (33) of the aforementioned variable pitch and deceleration front fan section. ) Separately or in communication, and the jet engine and the main wing ejected from the free turbine of the twin-turbo-turbine engine with the structure of jet flight from the VTOL rising to the free turbine From the control of the annular sliding door (Y) of the chamber and the opening and closing doors (32) and (56) of the inner surface of the front fan section, the jet ejection amount gradually increases, and the low bypass fan engine with air volume and fuel adjustment Then, the lower part of the fuselage, which assists the appropriate levitation described above, is used as the volume expansion door (V) for deployment, and the fan wind power from the fixed and portable prime mover ducted fan equipment (R) is lifted vertically. As an aid to the levitation force at the time of take-off and departure, the opening and closing duct on the upper part of the air cushion float launch equipment was made the place of departure.

This airframe will be hovering stable at levitation with an engine output of 70%, and jet jets will gradually increase from the opening of the annular slide door (Y) in the free turbine section. The fully open slide door and open / close door will have a jet propulsion ratio of 100%. When the rotor and fan are fully open, the clutch (38) and rotary brake (40) are stopped, and the main wing is sealed with the upper and lower slide covers (28). Low-passage fan with internal engine open / close door (32), external open / close door (56) and fuel adjustment jet engine jetting from twin-turbo-turbine engine free turbine with the above configuration and variable pitch and deceleration front fan・ Becomes an engine, and from VTOL's ascent to jet flight configuration and jet takeoff and landing selection, it becomes an all-weather twin-engine V / STOL aircraft, control is hydraulic, electric actuator And by a mechanical to spare, the output up, in the turbojet afterburner engine (57), turboshaft engine airplanes consisting of opening and closing control of the free turbine chamber.

Below, the control method of the turboshaft engine of this application and the anti-shake device of a ship is demonstrated easily.
In the control of the engines of Examples 1, 2, 7, and 8, the free turbine chamber of the turboshaft engine was an annular sliding door. The sliding door is opened and closed from jet flight to jet flight. The front and rear widths of the two-shaft shaft shaft inserted into the compression turbine shaft at the front of the free turbine are provided, and the free turbine plate has a circumferential frame structure. Therefore, the sliding door is fully opened and ejected into the bypass passage by force due to the resistance of the blade surface.Slight door opening / closing ratio and full opening and closing are the rotation of the blade surface and the jet ejection. The ratio is variable, with a few millimeters of control and a rapid hydraulic flow control of 3cm and an electric screw cylinder method. It was supposed to be.
The biggest challenge is to secure the width, thickness, length, and strength of the main wing by making the rotor and fan equipment variable and fixed in the main wing. It was decided to use a multi-blade fan with as small a diameter as possible and to have a high rotational output, so that it would fit in the main wing and the main wing would have an open / close cover structure. In this control and maneuvering, the turboshaft engine can be used with the engine output with a margin from the one fixed on the upper part of the fuselage, and the configuration in which the rotor and fan are fixed to the main wing of Example 8 reduces the weight of the fuselage. Thus, a nozzle jet outlet for fine adjustment of horizontal levitation is provided at each part, which is simpler than the ducted ring rotor variable machine of the seventh embodiment.

The control method of the annular sliding door in the free turbine room is to control the hydraulic cylinder, hydraulic motor, electric cylinder, mechanical straight line and loose male and female screw slide, the door is about 5cm in length and has a structure with no leakage and pressure resistance. The construction of remote hydraulic, electrical, mechanical and wireless operation is made of heat-resistant metal, is of existing technology, air cushion levitation float stand equipment has been established, and the front and rear wheels of the aircraft The configuration of simultaneous start and unlocking on the float table is to use an electromagnetic rod control hook etc. that can be released with a slight force, and (c) to make the entire surface under the deck magnetically levitated, space, maintenance and inspection Not easy, combined with air cushion levitation, and (d) front wheel catapult traction force is AC high output of the primary linear type linear motor installed on the catapult float table and side wall Use vector control inverter VVVF synchronous (induction) linear motors, eliminating the cushion tire sidewall for stopping, the jet propulsion and the linear motor propulsion is a schematic diagram becomes a sudden stop structure.
And, it is composed of a combination of a powerful fixed electromagnet and a coil armature, or a coil field element, and the road surface and the float base are made to have a repulsive magnetic levitation and suction levitation and linear motor (L) that moves forward and backward. The output of the existing linear motor train specifications has been improved, and the propulsion power of the fuselage engine is configured by using the above-mentioned fan levitation, jet propulsion catapult traction equipment, and optionally a linear motor.

The trim hydrofoil device, fin equipment, and tank cylinder vibration reduction device of Examples 3, 4, 5, and 6 suppress the speed of the hull and the vibration of pitch and roll during waves. The floating structures are inevitably united with the waves, speeding up and becoming submerged double hulls and hydrofoils that are not subject to streamlined bows and stern waves, with reduced vibration during sailing and stopping In the ship, the fin stabilizers are the mainstream of the roll reduction from the various roll reduction equipment installed on the deck in the ship and the gyro stabilizer equipment installed in the bottom of the ship. It seemed impossible.
Most ships need hull tank volume, receive waves in wide hulls, and need speedup and vertical and horizontal vibration reduction of fixed wing and rotary wing launchers, not only in stormy weather and fine weather The aircraft carrier, the ship, and the like were the same as those in Example 6 that combined various hydrofoil, various anti-vibration equipment in the ship, and tank cylinder anti-vibration device.
Similar regular tanker oil tankers, container ships, ore carriers, large passenger ships, etc. require average long-term vibration reduction, and a combination of fin equipment with a small wing surface and tank cylinder vibration reduction device 6 things.
For large fluid and heavy goods carriers, the double bottom ballast tank is used as a high-pressure air tank, the hull levitation, trim, and bottom water intake are manually and automatically electronically controlled from the deck, and the water intake is discharged from the remote valve. For flat water vessels, etc., the position of the hydraulic pipe tank cylinder is secured in the side wall of the ship bottom and draft at the time of design, and the shape of the ballast tank integrated with the hull is used to effectively utilize the narrow space The combination of the support plate of Patent Document 7 for the purpose of speed with the trim hydrofoil device that unfolds and stores the side wall from the pivot of the shaft is made appropriate.

The trim hydrofoil device of this application is composed of a hydraulic motor and cylinder that slides from the ship bottom to the space above the deck with the configuration of Patent Document 7, and fins, fins, stabilizers, and trim tabs are currently in various structures. The hydraulic pump control unit, electrical control unit, and machine control equipment are those of existing technology.
The tank cylinder vibration reduction device suitable for various hulls is a new idea. The air tank in the hull is used as a shock absorber cylinder. It is a simple one that discharges with the set check valve, and the control that makes the main blade angle of the trim hydrofoil device and one of the flap and fin equipment paired with the tank vibration reduction device is mainly for all back and forth movements. It is not possible to correspond to the shape of the wave of the ship, the course that fits the hull, ship speed, wave height and wave period, and direction of the wave are temporarily divided into 8 directions 45 degrees from the bow course, assuming the wave height 1m to 15m, and the wave cycle time is divided into 1 to 10 seconds and input to the electronic control unit (48) with numerical settings. Set to the basic manual setting that matches the value close to the course and wave height, The adjustment of fin angle and air tank pressure discharge shall be the automatic adjustment of actuators for electric and mechanical transmission, various hydraulic and pneumatic units from sequence and feedback of electronic control unit from various sensors (gyro, pressure) (47). Manual and automatic steering devices such as GPS are linked to the course.
The air volume of the air tank device, the discharge pressure, and the filling pressure are empirical rules that match the hull, and the pressure settings are simple, change with ship speed, the wave angle by the course, and the high In addition, the left and right front and rear side trim hydrofoil, fin stabilizers, trim tab vertical and horizontal swing reduction angle, tank compressed air check valve and communication pipe valve water load shock absorber It is possible to cope with each pressure sensor and gyro sensor, and to delay either of them In the trim hydrofoil with the width and area, the left and right main wing surfaces are fixed at the optimum deployment angle by waves, and the control of the leading and trailing edge flaps of the appropriate width is almost the same as that of the fin stabilizer. The same left and right side The flaps are lifted by the speed of the ship, and the trim tab equipment is for stabilizing the pitch from the stern to the rolling effect, and the control is the same as the fin stabilizer. Yes, the pressure control of each check valve of the hydraulic motor and air tank in the main wing preferentially operated by the gyro sensor, pressure sensor, limit switch and digital timer was made electronically controlled by the remote electromagnetic valve. The fins and trim tab equipment can be stored in the hull as appropriate.
A ship equipped with either a fluid tank agitation equipment, a solid movement agitation equipment, an inboard gyro-stabilizer agitation equipment and a tank cylinder agitation equipment on board or in the ship is a vibration equipment without outboard equipment, It will be able to handle both vertical and horizontal shaking almost automatically by adjusting air pressure and water flow.
The area of the trim hydrofoil device can be increased from the hydraulic trunnion type cylinder that supports the support and fixing plate in the middle part of the hydrofoil plate to a large area that cannot be compared with fin stabilizers. It also reduces the vertical and horizontal swaying of the open ocean cycle in the heavens, and in order to increase the speed of the aircraft carrier and the ship for a short time, trim from the above-mentioned air tank anti-vibration device, ballast tank levitation equipment and the front and rear adjustment trim of the hull. It becomes the effect of sailing by hydrofoil equipment.
Current ship navigation electronic control equipment, optimal course and oil / pneumatic electromagnetic operation equipment that reduces vibration, various oil / pneumatic pressure, sequence of vibration sensor and timer, oil pressure of feedback control, electronic control of electric actuator The existing control equipment technology of the current hydrofoil, catamaran hydrofoil, fighter plane control circuit automatic and manual selection.

In the jet engines of Examples 1, 7, and 8, the jet airplane is a turbofan engine with a high bypass ratio due to noise and fuel consumption. Boeing 747 aircraft was born 20 years after the war, and 40 years later Due to the high price of oil and fat, it has become a small machine and low fuel consumption. The root seems to come from population growth and demand for cars and electrical equipment.
The development of coal-fired rotating machinery equipment 200 years ago has led to a new one after another, and transportation is currently the largest for tourism. An aircraft that requires a long runway has a certain airfield, and its cost is enormous and has a mass consumption structure. In the V / STOL machine described in Examples 7 and 8 of the present application, if the weight of 50 tons of 50 to 100 passengers can safely take off and landing in a small space at a speed of 700 km / h, the transportation form will change.

The fan linear takeoff launching device of the present application has a short runway between the ship and the land, and every place is a takeoff and landing place. The present invention is an equipment that launches the towing catapult from the air cushion float base ascending with the propulsion of the aircraft and internal engine, the magnetic levitation and the catapult linear motor traction force are appropriate, and VTOL The lower part of the fuselage of the turbofan engine machine is deployed and the prime mover ducted fan wind force is applied to the levitation by applying the wind pressure and air volume from the extension of the duct frame elastomer, which is used for small aircraft carriers, etc. And then, the turbo shaft engine fan equipment was made into a portable assembly structure that could take off and land everywhere.
In addition, the powerful ducted equipment with small caliber for vertical and horizontal takeoff and landing that is installed in the main wing from the turbo shaft engine of the V / STOL tilt rotor and fan aircraft is stored and sealed in the main wing during horizontal cruise flight. Opening the engine's free turbine room and switching from a fan bypass ratio to a turbofan engine, it becomes a jet-propelled horizontal flight and gliding take-off and landing aircraft, the speed of an all-weather turbine jet, the convenience of a tilt rotor and fan aircraft Become a sex aircraft. In addition, the ring rotor and fan equipment are fixed in the main wing, and each part is a V / STOL airplane with a twin-shaft turboshaft engine that is lightweight and simple for jet forward flight from hovering of jet nozzle ejection from the free turbine chamber.

By making the ducted rotor equipment of the tilt rotor machine into a ring rotor blade with a universal joint, the blade angle remains almost constant even when the engine output is increased, and the rotor hub control (39 ) To be the variable angle of the ring rotor. With this ring frame free fixing method, the blade width can be widened, and the ducted ring rotor can be equipped with a small small diameter rotor that can be installed in the main wing, can be fixed separately from the engine, and the above-mentioned jet shaft engine Appropriate take-off and landing and departure and landing with the air cushion device.

With the free turbine part of the turboshaft engine as the chamber, the opening control equipment is configured as a turboprop engine that opens the annular slide door and the ratio of propulsion shaft shaft rotational force and jet spray output is variable. When the door is fully open, the jet of the turbojet engine is ejected, and the front fan with variable pitch connected to the compressor shaft and the reducer in the air intake duct has an appropriate bypass ratio that matches the speed of the aircraft from the open / close door on the inner and outer surfaces. It becomes a turbofan engine, and an open / close valve is provided on the sliding door of the free turbine room and on the front fan part. / STOL amphibious aircraft, tilt aircraft, helicopters, air cushion boats, ships, amphibious vehicles, etc. The adoption of a combination of various cushion emerged. In addition, it is also possible to increase the output by 100% jet ejection by fully opening the annular sliding door of the free turbine chamber and the rear part as an afterburner combustion part.

This turboshaft engine helicopter is a free turbine engine that opens and closes the sliding door of the free turbine chamber. By finely adjusting the opening and closing, the levitation propulsion force of the rotor blades is 50% and jet jet propulsion is 50%. Then, the speed will be increased, and the rotor and one engine from the two free turbine engines on the left and right will be jet propulsion, and it will be a new all-weather jet helicopter with ample output.

In addition, it has a trim hydrofoil device with a vertical slide structure that reduces the roll of various ships (light aircraft carrier, ship) and speeds up, and the large area of the hydraulic pipe tank cylinder shaker from the ship bottom that absorbs the pitching Air tank floating, pneumatic shock absorber equipment, and communication pipe water pressure shock absorber equipment, both devices can produce a wide hull from trim and stabilizer, speed up, and speed up for a long time A large loading ship such as oil, ore, steel tanker, etc., and various carriers, and an aircraft carrier and an electric propulsion ship as an electric propulsion ship. Or a hydraulic actuator device that raises and lowers the electric motor shaft in the ship and the screw shaft for changing the direction, and there is no draft or air entrainment under the ship's bottom The hull, which has been lowered to a position and has a flat structure at the stern draft and a plurality of Z propellers (azimuth thrusters) stored in the bottom of the ship as needed, has been lifted lightly from the empty ship state, resulting in faster ascent and faster fuel efficiency. Vertical and horizontal reduction of drilling vessels that do not require ballast water and stop at a certain position in the open ocean, platforms with large depths (3.000 m or more), wind power generation boats, low-speed resource survey vessels, longline vessels, etc. The equipment of the rocking tank cylinder vibration reduction device must maintain a fixed position against waves and tides, and the tank cylinder vibration reduction device that suppresses the hull movement is integrated with the DPS and azimuth thruster. As a resource development ship, it becomes a hull construction with the above-mentioned width of the hull, and the hull construction is a change of national inspection that gives priority to safety based on the length of the hull.
And the upper side of the tank cylinder anti-vibration device that uses the side thrusters on the sides of the left and right side as a water inlet, and the roll of storage and deployment with the hydraulic actuator from the inside of the eaves of the bow of the existing technology and the main anti-vibration fin stabilizer In the upper part of the water intake at the stern, a trim tab for main vibration reduction and storage is provided, and the water speed and water pressure of the ship speed are introduced to the water intake just above the tank cylinder vibration reduction device. Structure and configuration.
The trim hydrofoil unit is a device for speeding up the main swing and reducing the weather in rough weather when the main wing area is enlarged and the angle can be adjusted freely by submersion. It was not able to withstand the wave height, and from a small fin structure with a small area for rough weather, it became a pair of vertical and horizontal anti-vibration devices when combined with a tank anti-vibration device. The main features were tank cylinder vibration reduction equipment, and trim hydrofoil equipment and small area fin equipment were installed in combination with the bow and stern as appropriate depending on the hull form and purpose.

Under the surface of the runway of large and small airplanes, the above-mentioned turboshaft engine catapult towing air cushion levitation propulsion equipment is installed and auxiliary takeoff equipment at the time of departure can be taken off on a short runway, landing is Although it depends on the weather, the landing road surface is a shock absorber surface, and the running road surface is an air cushion float, wheel float, magnetic levitation float, and linear motor (power generation) float with appropriate area sections, The small body is placed on the next small float section, mounted on the float section, and mounted on the next small float section. By adopting the power generation brake configuration, the actual takeoff and landing distance is about 200m.

The ballast tanks on the front, back, left and right of the double bottom of the ship are made into high-pressure pneumatic tanks, and a water intake is provided on the bottom of the bottom tank from the deck to the bottom of the remote control valve connected to the rod. The press-in and discharge functions as intake tanks proportional to the tank area and capacity, as well as adjustment tanks for the rise and trim of the drainage hulls.

Intake and drainage into the double bottom ballast tank is drained from the bottom valve by press-fitting high-pressure air, and the intake is evacuated from high-pressure air, and each compartment tank is appropriately performed during voyage, and the side ballast tank on the draft The water is pumped up at the same time as the drainage, and the bottom and side tanks are connected by remote control valves. Not to be brought into the port.

A linear power generation ship and a ship that move up and down due to waves are used as a power generation device for a stroke of a linear power generation cylinder of a stator with a field mover rod connected to the upper surface of the water as a piston stroke of the intake pipe cylinder.

With the existing steam and gas pressure catapult equipment, either the above-mentioned magnetic levitation, linear motor and prime mover float air cushion levitation and propulsion equipment are integrated into one device, and the weight of the aircraft is placed on the float. The catapult gas pressure is low and small because the levitation equipment is levitated, and it also becomes a launching device for large aircraft.

In a railway that travels between ground stations on a single straight line that is a solution to noise and inside a deep and small-diameter tunnel, the rear part of the tunnel is configured to be a reaction effect of the jet engine bypass passage and jet ejection, and the existing electric vehicle The combination of weight reduction of a linear motor vehicle and an air cushion levitation vehicle, or a magnetic levitation vehicle, and the above-described simple turboshaft engine free turbine chamber duct / fan levitation propulsion equipped vehicle and rotating wheel vehicle In combination, the combination of jet engine and high-speed underground electricity and jet propulsion railway will increase the propulsion power of electric vehicles.

It communicates with the gravity power generator using a balance with the underwater intake of the bow and the pressure load device of the engine described in Patent Document 8, and the water flow according to the ship speed is taken into the cylinder head chamber to increase the pressure and water volume. The hybrid engine is connected to the propulsion engine from the balance ratio of the upper and lower two stages, and is connected to the propulsion engine by the rotating force of the crank linked to the closed circuit hydraulic cylinder. The intake port used in combination with a communication pipe for a water pressure shock absorber that communicates with the tank cylinder under draft.

A Air cushion levitation propulsion float base equipment A1 Float plate surface B Turbo shaft engine C Ducted fan equipment D Mooring lock E Air cushion seal material

F Front wheel tow hook equipment G Cushion / Tire part H Reverse jet valve I Deck (Deck) J Spare wheel K Deck slide cover L Linear motor equipment M Magnetic levitation equipment
Opening and closing air supply duct to the N aircraft volume O soft material P
QV / STOL turbofan engine machine R fixed and portable prime mover equipped with ducted fan
S1 tilt rotor, fan machine S2 main ring fixed ring rotor, fan-equipped fixing machine
T multi-blade ring fan blade U ring wide rotor blade V fuselage lower volume door W duct frame
X Free turbine chamber Y (open), annular slide door Y (closed), annular slide door Z annular support frame

1 hydrofoil plate 2 prop plate 3 link support fixing plate 4 trunnion type hydraulic cylinder
5 Slide groove 6 Flap 7 Vertical slide hydraulic motor 8 Slide connecting plate
9 Link fixing plate 10 Male surface release position of prop link fixing plate part 11 Male surface release position of prop hydrofoil part
12 Male surface release position in the center of the column 13 Spur gear and hydraulic motor gear groove 14 Male shaft 14a Female part
15 Intake port 16 Air tank 17 Suction check valve 18 Discharge check valve 19 Front and rear communication pipes 20 Left and right communication pipes

21 Remote control valve 22 Air tank in the center 23 Side thruster 24 Ship bottom 25 Drum brake
26 Limit switch 27 Brake hydraulic cylinder 28 Sliding door on upper and lower main wing surface
29 Free turbine circumferential plate 30 Front fan blade 31 Bypass passage 32 Bypass opening / closing door (flap) 33 Open / close valve on the annular sliding door 34 Float jet
35 Front / fan deceleration variable pitch hub device 36 Deceleration and direction change equipment 37 Nozzle outlet

38 Clutch 39 Hub mechanism 40 Rotating brake 41 Bearing 42 Fin stabilizer
43 Trim tab equipment 44 Ship bottom ballast tank 45 Remote intake control valve 46 Pneumatic unit
47 sensors (pressure, gyro) 48 electronic control unit (digital timer, sequence, feedback)
49 Hydraulic unit equipped with starboard wing 50 Hydraulic unit equipped with port wing 51 Various hydraulic actuators equipped with starboard wing

52 Various hydraulic actuators equipped with port wings 53 Wire 54 Support slide deployment frame 55 Internal opening / closing valve
56 External doors 57 After banners 58 Shock absorber surfaces 59 Small wheels
60 Spring material (fluid spring, rigid spring, shock-absorbing elastic material) 61 Catapult traction plate

It relates to the structure of turbo shaft engine V / STOL machine.

Departures other than V / STOL aircraft are launched by means of catapult propulsion and full power.

Japanese Patent Application 57-48155 Combined engine with convertible output Actual Application Sho 61-94406 Patent No. 2700734 Vertical take-off and landing aircraft Patent No. 3677748 Aircraft created by fixing the rapid airflow generating wind direction changing device directly on the side or side wall of the fuselage. Japanese Patent Application 2011-113112

The existing VTOL turbofan engine was made an auxiliary equipment for vertical levitation by applying the wind power of the fixed and portable prime mover ducted fan to the fuselage volume surface. The VTOL tilt rotor machine and fan machine of the present application are equipped with a small-diameter ducted ring rotor and ring fan that are fixed in the upper part of the fuselage main wing and stored in the main wing separated from the engine. For flight, vertical takeoff with two fixed left and right turboshaft engines, free turbine room with open sliding door structure, and turbo fan engine with bypass ratio engine fan door opening and closing appropriately, jet flight and rotary flight A combination of selected flight configurations.

The composite engine capable of converting the output of Patent Document 1 uses a free turbine with variable blade control, and unlike a helicopter rotor hub mechanism that is variable at the center, links multiple turbine blades that rotate at high speed. At the same time, the control method for making all wings variable is for a rotating machine with low rotation and low safety, and is an unreasonable technique that cannot be used in the center of an airplane engine. In the present application, an annular cover portion is used as a slide door, and the structure has no problem in safety.

If a new short-range launching device that can launch is possible, the number of personnel will be reduced, and all advantages will be achieved.
Patent Document 5 discloses that a fixed-wing, fixed-engine carrier-based aircraft (fighter) launches a large-sized aircraft from an existing aircraft carrier with a small hull such as a diesel engine. As a catapult of levitation, jet propulsion, magnetic levitation, and linear motor, the aircraft body is placed on the air cushion float base from the fan equipment of the optimal prime mover (turbo shaft engine), and the machine friction is eliminated and gliding with the thrust of both engines The catapult device to be used.

The present application also enables the launch of larger aircraft from existing aircraft carriers, and ships and land-specific VTOL aircraft have a small diameter of ring rotor machines and ring fan machines that tilt separately from the engine. A variable ducted rotor, equipped with a fan, a sliding plate sealed structure that is housed in the left and right main wings, a gear connected to a turboshaft engine fixed on the left and right main wings, and combined use of vertical and horizontal takeoff and landing, and rotor From the flight as a plane or fan, gradually switch from the ejection of the open sliding door of the free turbine room to the jet flight, and the ducted rotor is stored in the main wing to increase the speed of the jet flight, and the horizontal takeoff and landing from the jet flight It was supposed to be possible. In addition, it is equipped with a portable fan that helps to lift the burden of the V / STOL turbofan engine and assists the engine output of landing, and can take off from the small hull and take off and landing from the inside. .

Then, avoid the fuel tank and the equipment on the lower part of the fuselage fuselage of the VTOL aircraft mounted on the turbofan engine, and make the lower part of the full fuselage the structure of the deployment door, the structure of the fan levitation and jet propulsion, and the linear motor catapult With the combined use of towing, the launch of wind power, air cushion float and airframe engine output from the front of the ship speed is very small, the launch distance without the burden of the engine is very small, the landing deck distance plane is marginal The ship speed can be set at normal speed, or can be launched in a stopped or moored state, and the various hydrofoil devices and tank cylinder vibration reduction devices described in Patent Document 5 are waves. Easier to launch, speeding up the aircraft from strong winds, making it easier to launch. And the portable fan equipment that assists the levitation output to reduce the burden on the VTOL aircraft makes it easy to take off and land from any location.

Most of the propeller aircraft of claim 1 are turboprop engines, the helicopter is a turboshaft engine that transmits almost 100% to rotational force, and the engine of the tilt rotor aircraft and tilt fan aircraft of the present application is Using a turboshaft engine, the free turbine chamber has an annular sliding door structure. Then, we made a wide-blade small-diameter variable ducted ring rotor blade machine and a multi-blade ring fan blade machine with a smaller diameter. The twin-engine turboshaft engine is fixed at the center of gravity on the fuselage side of the upper left and right main wings. The left and right engines and the ring frame are linked to the shaft, and the variable ducted equipment in the left and right main wings is a free turbine. The two-shaft shaft from the gear is engaged with the ring rotor and ring fan in the duct equipment in the main wing from the gear reduction and direction change gear equipment, the inside of the wide wing is the fixed axis, and in the duct equipment that rotates tilt Rotor hub control with a wide blade area from 4 to 6 blades and ring rotor blades, with a ring frame and rotor blade tips fixed at universal joints, and each rotor blade attracting the ring. The ring / rotor variable angle and variable pitch blade control of the mechanism were adopted. Multi-blade 8-20 fixed ring fan blades are equipped with smaller diameter ducted ring fans, and both blades are equipped with variable ducted equipment to control vertical, forward and reverse tilting and hovering. The turboshaft engine can be turned left and right, and the hub shaft speed reducer and variable pitch front fan blades connected to the compressor shaft in the air intake duct and 8 to 10 blade blades can be opened and closed. It is a bypass passage for door control, a turbofan engine structure that surrounds the compressor, combustion section, and turbine section. The free turbine chamber is a chamber that has a width in the shaft insertion section of the high-pressure turbine. A circular plate structure for jetting into the free passage, and a structure that smoothly jets into the bypass passage. The door can be expanded and contracted by a hydraulic cylinder, the rotation of a hydraulic motor, the expansion and contraction of an electric cylinder and a preliminary mechanical rotation, and the ring rotor and ring fan rotation connected to a free turbine and a shaft from one of the control devices of the annular slide door. The ratio of force and jet spray output is variable, and this door opening / closing becomes an engine of choice of rotational propulsion and jet propulsion, and an opening / closing valve provided on the annular sliding door of the free turbine chamber as appropriate, and the front fan The injection nozzle from the on-off valve of the bypass section is installed at the appropriate position on the main wing, horizontal tail, etc. to make it an auxiliary equipment for levitation, and switching from hovering ring rotor and fan flight to jet flight is a ring in the free turbine room From the sliding door and front fan opening / closing door control, the jet ejection amount gradually increases and the ring rotor, fan The drive shaft to the clutch is stopped, the rotary brake is fixed, the ducted equipment is stored in the main wing of the upper and lower sliding doors, and the free turbine chamber sliding door is fully opened as a turbojet engine, variable pitch The air volume adjustment of the front and rear fan blades and the two open and close doors on the inner and outer surfaces is a bypass ratio engine that enables jet propulsion with an arbitrary air volume, and a turbo fan with a jet propulsion speed that is suitable for the aircraft speed. It becomes an engine, and the ducted equipment is stored, the main wing surface is sealed with the sliding doors on the upper and lower wing surfaces, and it becomes a horizontal take-off and landing aircraft from a jet-propelled flight with high speed, and the jetted equipment is deployed from the wing and jet ejected The half-open control flight of the sliding door is performed by the jet propulsion and the rotor propulsion. It becomes a STOL aircraft of the combined turboprop engine, and the full closing of the free turbine chamber jet ejection slide door becomes a single flight with ducted equipment, and the combined use with thrust of low bypass ratio, turboshaft engine and turbofan The engine is a V / STOL machine, and the output is increased by controlling the variable front fan and each open / close door and fully opening the annular slide door to the turbojet afterburner engine, and various control devices linked to it. A twin-rotation turbo-shaft engine tilt-rotor and tilt-fan aircraft that make it easy to take off and land and take off.
That is, the present invention is a turbo-shaft engine rotor and fan flight and a turbo-jet engine to turbo-fan engine flight, the ducted equipment is not housed in the main wing, and the rotation of the rotor flight is from the turbo-prop engine to the turbo-fan. The ratio of rotation and jet propulsion to switch to the engine is variable, and this tilt rotor machine is a turboshaft engine VTOL machine in a place without a runway. This is a tilt-rotor aircraft that has a small-diameter ducked rotor provided in the main wing, which is a short-range take-off and landing in a turboprop engine. A small number of passenger planes for short-range transport of wing blade fan machines, no runway, and , Faster than existing tilt-rotor machines.

The invention of claim 1 is a ducted ring rotor and ring fan equipment that tilts in the left and right main wings, and the invention of claim 2 eliminates the duct equipment and the ring rotor and ring fan equipment in the main wing. Was fixed horizontally. The twin-engined turboshaft engine V / STOL airplane is equipped with a vertical levitation fuselage by connecting a shaft with a ring rotor or ring fan that is fixed in the main wing from a speed reduction and direction change device. Fine adjustment control of the stable horizontal levitation of a ring rotor and fan equipped aircraft that does not tilt is provided with an opening / closing valve and an opening / closing valve for the front fan section on the annular slide door of the free turbine chamber of the aforementioned turboshaft engine. The nozzle pipe of the caliber is connected to each part such as the left and right main wings, the tip of the horizontal tail, the tip of the fuselage, and the rear part, and the jet jet outlet of the piping is separately constructed, and the vertical levitation is hovering stable at 70% of both engine outputs. The forward speed increases the engine output, and the jet output gradually increases from the annular slide door and front fan opening / closing control of the free turbine chamber to the forward speed. The rotor and fan equipment are fully open and the clutch is stopped and the rotary brake is fixed. The jet engine from the free turbine chamber of the twin-turbo-turbo engine with the structure of jet flight from the VTOL levitation to the VTOL floating, and the above-mentioned variable pitch and deceleration front fan part inside and outside two The opening and closing door and fuel-adjusted low bypass fan engine can also be used. Increased output can be achieved by using a fully open turbojet afterburner engine with an annular sliding door, and an appropriate volume lowering door for deployment. The fan wind power from the prime mover ducted fan equipment is used as an auxiliary to the lift force at the time of takeoff departure from the vertical flight of the fuselage, and the upper air opening and closing air supply duct of the air cushion levitation propulsion float departure equipment is released. Equipped with ship location. A turboshaft engine that consists of jet flight from VTOL ascent and selection of jet take-off and landing, and open / close control of the free turbine room of an all-weather twin-engine V / STOL aircraft.

The VTOL tilt rotor, fan engine, rotor, and fan equipment are separated, and the free turbine (power turbine) chamber of the turboshaft engine is structured as an open door jet and front fan bypass mixed propulsion engine. , Jet flight and rotor flight combined and selected.

Schematic of V / STOL aircraft and turbojet engine. [Embodiment 1] (Fig. A) Schematic view seen from the front of a tilt duct ring rotor blade machine. (b) Schematic view from the front of the tilt ducted ring fan blade machine. (c) Schematic plan view of tilt ducted ring rotor machine. (d figure) The front schematic of a tilt ducted ring rotor and a fan machine. (e figure) Schematic of the wire structure of the sliding door of the duct part in the main wing of a tilt ducted ring rotor and fan machine. (f figure) The plane schematic diagram of the structure of the sliding door of the tilt ducted ring rotor and the main wing duct of a fan machine. (g) Schematic of the structure of a tilted ring rotor and turbofan engine for a fan. (h) Schematic of the structure as seen from the front of the tilt ducted ring rotor and fan machine. Schematic of a ring rotor, ring fan equipped machine that is horizontally fixed in the main wing. [Example 2] (Fig. I) A schematic plan view of a ring-wide rotor machine. (j figure) The plane schematic of opening of the fuselage lower volume door of a ring fan machine. (k) Schematic of the sliding door equipped with the ring and fan on the lower wing surface. (Figure l) Schematic diagram of the structure of a ring rotor and turbomachine of a fan machine. Schematic of deployment of the lower part of the fuselage of the VTOL machine. [Embodiment 3] (Fig. M) Schematic diagram of airframe floating by installing fixed and portable prime mover ringed ring fan equipment under road surface. (n figure) The front view which stored the fuselage expansion | deployment door of the said ring rotor, ring fan equipped machine. (o) Expanded the volume door on the lower surface of the tilt ring fan machine

  This will be described based on the drawings and reference numerals.

The propeller aircraft is a turboprop engine, the helicopter is a turboshaft engine, and the twin-engine tilt-rotor aircraft (S1) and fan (S1) aircraft of this application in [Fig. 1] (Fig. 1a, b, h) The turboshaft engine (B) is fixed to the upper part of the main wing surface at the top of the fuselage, and the ducted ring rotor is inserted into the left and right main wings from the free turbine and the front shaft deceleration and direction change (36) mechanism. Or use a ring equipped with a fan, a ring / wide rotor blade (U) frame, or a multi-blade ring / fan blade (T) frame. The upper and lower wings are sealed with sliding doors (28), and the annular sliding door (Y) of the free turbine chamber (X) in (g) is opened and closed with a hydraulic cylinder, motor or electric cylinder, motor and spare machine manual. Structure and half-open jet The combination of propulsion and ducted ring rotor and fan rotation propulsion becomes a turboprop engine machine, and the variable pitch and deceleration front fan blade hub device (35) in the air intake duct connected to the compressor shaft is The open turbine door (flap) (32) is provided in the bypass passage, and the free turbine chamber (X) fluidly connected to the compression turbine section from the combustor is opened by the annular slide door (Y) to make jet ejection. The chamber of the free turbine circumferential plate (29) that sets a slight distance, the bypass passage (31) as a support frame, the open / close door (32) fully open and the free turbine section slide door fully open are low. The bypass turbofan engine is used, and the free turbine chamber is fully closed by rotating the rotor and fan of the turboshaft engine.
The annular sliding door (Y), the speed reduction variable pitch hub (35) output of the front fan (30), and the fine adjustment opening / closing of the inner opening / closing door (32) and the outer opening / closing door (56) are any of the above. The jet engine form, and the output increase is the turbo jet afterburner engine (57), horizontal take-off and landing can be done with the configuration of both rotary propulsion and jet propulsion engines, and the speed of horizontal flight, It will be an all-weather vertical takeoff and landing aircraft.

And, the assumed aircraft weight is 30 tons, and the twin-tilt turbo engine with a 30-crew engine is equipped with a free turbine and a variable ducted ring rotor with a shaft connection. The ring fan equipment will be smaller, with a maximum of about 5.0M, and will be a vertical and horizontal take-off and landing tilt rotor and fan machine that will fit in a main wing with a maximum front and rear width of about 70cm and a maximum height of about 70cm.
The ring-rotor machine of the rotor hub control mechanism (39) uses duct variable angle and variable pitch blade control, and the fixed ring fan blade of the multi-blade 8 to 20 is equipped with a ducted ring fan with a smaller diameter.
Featuring a helicopter convenience and noise-fitting horizontal flight turbofan engine, a tilt-rotor that houses all-weather storage, and a fan-equipped turboshaft engine jet.
The twin-engine tilt-rotor machine, which will be a V / STOL machine, is equipped with a ring-wide rotor-equipped lift blade and a small-diameter variable ducted ring rotor. The lift configuration provided in the appropriate position, the variable ducted ring rotor equipment, the configuration that fits in the main wing outside the engine, and the variable rotation of the hydraulic motor at an appropriate angle above and below the variable duct with the left and right bearings (41) In the variable duct, the ring / rotor equipment rotating in the duct is connected to the variable gearbox of the drive shaft from the speed change and direction changing mechanism in the front of the engine. It is assumed that it has a main wing area that can perform rotor flight landing and jet flight with one engine output at the time, and model selection from this engine output and fuel consumption is Compared with helicopters, propellers, jets and the efficiency, and this application is a tilt ring rotor machine in which the variable duct is housed in the main wing in the rotating hydraulic equipment for duct, and the above-mentioned appropriate fuselage lower surface Is a volume wind power deployment door (V), and a fixed, portable prime mover equipped with a ducted fan (R) is used as an auxiliary structure for floating by wind power.

And the ring rotor equipment can move backwards and swivels from the surface of the blade with a wide area and variable duct, can move backwards and swivels vertically, and can run and take off and land smoothly. In horizontal cruise flight, switching from turboprop flight to turbojet flight, the adjustment control of the annular slide door (Y) becomes the rotor rotation and jet ratio, and the ring rotor rotation is clutched The stop (38) and rotary brake (40) are fixed, and the turbo-jet engine flight is achieved when fully open, and the tilt ring rotor machine is achieved when fully closed and the clutch is input. During turbojet flight, the variable ducted ring rotor equipment part slides the sliding door (28) of the main wing from the fuselage internal storage on the upper surface of the fuselage and the lower surface of the left and right main wings to the wing circumference of the duct frame (W). The support slide deployment frame (54) for the hydraulic / pneumatic cylinder deployment from the circumference of the main wing is used as a guide and support, and electric or hydraulic motor winches are installed at appropriate positions on the main wing and fuselage, and the slide (upper and lower) is supported by the wire (53). The cover door is wrapped around two cover winches to form a closed and open wire structure, or a plurality of hydraulic telescopic cylinders can be expanded and contracted. The total area of the left and right main wings is enough to lift and lift up the speed. Also, the airplane will be a short-distance section of rotor, fan rotation and jet propulsion, and a medium-distance section of jet propulsion, and the landing will be made by horizontally landing the turbojet with the sliding door closed or switching to the ducted rotor flight. Vertical takeoff and landing in a place without a runway, horizontal takeoff and landing on a runway, and takeoff and landing of a short distance with the above-mentioned V / STOL fuselage expansion volume door, from the ring rotor From the blade area, it is a tilt ring rotor machine with a small caliber ducked ring rotor equipment.

And, it is possible to take off and land from any land and indoor from small ships, and equipped with variable ducted rotor equipment on the main wing part and small ducked rotor equipment or turbofan engine on the left and right of the rear of the aircraft Set up a vertical take-off and landing of large passengers and transport aircraft 50t, and open / close valves (33) on the sliding door (Y) of the free turbine room and opening / closing valves (32) on the front fan bypass opening / closing door (32) as appropriate. 55) is provided for communication, or separate nozzles (37) of various calibers are provided at appropriate positions such as the fuselage, main wing, horizontal tail, etc., to assist in ascent.
The tilt and ring rotor and turbine jet engines are designed to ensure speed and safety and add speed to the convenience of the helicopter.
The current tilt-rotor machine has an engine and rotor blades integrated, and the fixed main wing and the engine must be variably controlled from a mechanism that makes the engine variable by about 100 degrees. Is a fixed engine, and the difference in maneuverability and safety is clear when compared to jet flight during cruise flight. When STOL sliding take-off and landing of the turboprop flight is performed, noise is reduced and fuel consumption is improved. It became the tilt rotor machine.

Unlike the helicopter rotor blade and propeller airplane blade, the ring rotor and fan equipment of (a, b) can be made small in diameter and as a propeller that is fixed separately with a shaft connection with the turboprop engine. Since the main wing is inevitably stored in the main wing, the thickness and width of the main wing are increased, and the strength of the tip is ensured. The fuselage, the left and right main wing frames, and the duct frame frame are integrated into a single metal frame. And the wing tip has a structure such as wire or piano wire.

The ring rotor and fan equipment (S2) shown in [Fig. 2] are fixed horizontally in the main wing instead of the ducted ring rotor and fan equipment (S1) tilted in the left and right main wings as described in Example 1. For fine-tuning control of the aircraft, the open / close valve (33) is provided on the annular slide doors of the left and right turboshaft engine free turbine chambers described above. 37) shall be ejected from the pipes at the left and right main wing tips and the fuselage tip fuselage rear part, and the opening and closing valves (55) and the opening and closing valves (33) of the above-mentioned variable pitch and deceleration front fan part. (37) is separately or communicated, and the main wing from the jet engine ejected from the free turbine of the twin-engine turboshaft engine with the structure of jet flight from the rise of VTOL has the above-described upper and lower slide cover (28) sealed structure. ,free The jet injection volume gradually increases from the control of the annular sliding door (Y) in the turbine room, the inner door (32) and the outer door (56) in the front fan section, and the low bypass fan engine with air volume and fuel adjustment The fan from the fixed and portable prime mover ducted fan equipment (R) described above, with the lower body part of the fuselage as the above-mentioned appropriate floating support in FIG. The wind force was used as an auxiliary to the levitation force at the time of takeoff and departure from the aircraft vertical, and the upper and lower ducts on the air cushion float launch equipment were used as the place of departure.

This airframe will be hovering stable at levitation with an engine output of 70%, jet jets will gradually increase from the opening of the annular slide door (Y) of the free turbine, and the slide door and the open / close door (32) will be fully opened. 100% of the flight, with the ring rotor and fan equipment fully open, the clutch (38) and rotary brake (40) are stopped, and the main wing is sealed with the above-mentioned upper and lower slide covers (28). Jet engine jetted from free turbine of twin-turbo-turbo engine with floating to jet flight configuration, front and rear doors (32) and outer doors (56) of variable pitch and deceleration front fan, and fuel adjustment From the rise of VTOL and the choice of jet flight configuration and jet take-off and landing to an all-weather twin-engine V / STOL aircraft, control is hydraulic, electric actuated A turboshaft engine airplane consisting of a turbojet and afterburner engine (57), and a free turbine chamber opening and closing control, with a spare and a mechanical system as a reserve.

In the control of the engines of Examples 1 and 2, the free turbine chamber of the turboshaft engine was an annular sliding door. The sliding door is opened and closed from jet flight to jet flight. The front and rear widths of the two-shaft shaft shaft inserted into the compression turbine shaft at the front of the free turbine are provided, and the free turbine plate has a circumferential frame structure. Therefore, the sliding door is fully opened and ejected into the bypass passage by force due to the resistance of the blade surface.Slight door opening / closing ratio and full opening and closing are the rotation of the blade surface and the jet ejection. The ratio is variable, with a few millimeters of control and a rapid hydraulic flow control of 3cm and an electric screw cylinder method. It was supposed to be.
Making the rotor and fan equipment variable and fixed in the main wing, ensuring the width, thickness, length and strength of the main wing is the biggest challenge, the blade area from the reduction ratio of the ring rotor and fan, A wide rotor and a multi-blade fan with a small diameter as much as possible, and a high-rotation output, fits in the main wing, and the main wing has an open / close cover structure. In this control and maneuvering, the turboshaft engine can be used with the engine output from the fixed to the upper part of the fuselage, and the configuration of fixing the ring rotor and fan to the main wing of Example 2 The weight is reduced, and a nozzle jet outlet for fine adjustment of horizontal levitation is provided at each part, which is simpler than the ducted ring rotor variable machine of the first embodiment.

In the jet engines of Examples 1 and 2, jet airplanes are mainly turbofan engines with a high bypass ratio due to noise and fuel consumption, and aircraft that require a long runway have a certain airfield, The cost is enormous and has a mass consumption structure. In the V / STOL machine described in Examples 1 and 2 of the present application, when the weight of 50 to 100 passengers and the weight of 50 tons is safely taken off and landing in a small space at a speed of 700 km / h, the transportation form changes.

The powerful ducted equipment with small caliber for vertical and horizontal takeoff and landing that is installed in the main wing from the turbo shaft engine of the V / STOL tilt ring rotor aircraft and fan aircraft of this application is enclosed and sealed in the main wing during horizontal cruise flight, Opening the free turbine chamber of the shaft engine and switching from the front fan bypass ratio to the turbofan engine, it becomes a jet-propelled horizontal flight and gliding take-off and landing aircraft, the speed of the all-weather turbine jet and the tilt ring rotor It will be a convenient machine for fan machines. In addition, the ring rotor and fan equipment are fixed in the main wing, and each part is made into a V / STOL airplane of a twin-shaft turboshaft engine that is lightweight and simple for jet forward flight from hovering of jet nozzle ejection from the free turbine chamber. .

Making the ducted ring rotor equipment of the tilt ring rotor machine into a universally connected ring rotor blade makes the blade angle almost constant even if the engine output is increased, and the rotor hub similar to a helicopter From the control (39), the angle of the ring rotor is changed. With this ring frame free fixing method, the blade width can be widened, and the ducted ring rotor can be equipped with a small small diameter rotor that can be installed in the main wing, can be fixed separately from the engine, and the above-mentioned jet shaft engine Appropriate take-off and landing and departure and landing with the air cushion device.

With the free turbine part of the turboshaft engine as the chamber, the opening control equipment is configured as a turboprop engine that opens the annular slide door and the ratio of propulsion shaft shaft rotational force and jet spray output is variable. When the door is fully open, the jet of the turbojet engine is ejected, and the front fan with variable pitch connected to the compressor shaft and the reducer in the air intake duct has an appropriate bypass ratio that matches the speed of the aircraft from the open / close door on the inner and outer surfaces. It becomes a turbofan engine, and an open / close valve is provided on the sliding door of the free turbine room and on the front fan part. / STOL amphibious aircraft, tilt aircraft, helicopters, air cushion boats, ships, amphibious vehicles, etc. The adoption of a combination of various cushion emerged. In addition, it is also possible to increase the output by 100% jet ejection by fully opening the annular sliding door of the free turbine chamber and the rear part as an afterburner combustion part.

This turboshaft engine helicopter is a free turbine engine that opens and closes the sliding door of the free turbine chamber. By finely adjusting the opening and closing, the levitation propulsion force of the rotor blades is 50% and jet jet propulsion is 50%. Then the speed will be increased, and the rotor and two engines from two free turbine engines will be jet propulsion, and it will be a new all-weather jet helicopter with ample output.

B turboshaft engine QV / STOL turbofan engine
R fixed and portable prime mover with ducted fan S1 tilt ring rotor, fan machine
S2 main wing fixing ring / rotor, fixing machine with fan T multi-wing ring / fan blade
U ring wide rotor blade V fuselage lower volume door W duct frame
X free turbine chamber Y annular sliding door (open / close) Z annular support frame

28 Sliding doors on the upper and lower main blade surfaces 29 Free turbine circumferential plate 30 Front fan blade
31 Bypass passage 32 Open / close door (flap) in bypass section 33 Open / close valve on annular slide door 34 Float outlet 35 Front fan deceleration variable pitch hub device 36 Deceleration and direction change equipment 37 Nozzle outlet 38 Clutch 39 Hub mechanism 40 Rotating brake 41 bearing 53 wire
54 Slide frame 55 Open / close valve 56 Open / close door on the outside 57 Afterburner

Claims (2)

The twin-rotor turboshaft engine tilt rotor (S1) and tilt fan (S1) have left and right main wings fixed to the upper fuselage, and the turboshaft engine (B) has a fuselage side above the left and right main wings. The right and left engines are fixed in place at the center of gravity, and the left and right engines are linked to the shaft, and the variable ducted rotor and fan installed in the left and right main wings of the center of gravity are equipped with a two-shaft shaft from the free turbine. The ring rotor in the duct equipment that engages with the ring rotor and ring fan in the duct equipment in the main wing and tilts with the inside of the wide main wing as the fixed axis is a ring wide with a small blade diameter from a wide blade area In the rotor blade (U), the ring frame and the tip of the rotor blade are connected with a variable universal joint, and the rotor blades are configured to pull the ring together. The rotor hub control mechanism (39) has a ring rotor variable angle and variable pitch blade control, and the multi-blade fixed ring fan blade is equipped with a duct with a smaller diameter than the rotor blade machine. The turboshaft engine is controlled by hydraulic, electric, or mechanical, with an air intake duct that can adjust the vertical / forward / reverse tilted levitation from the pivot control and the left / right turn from hovering. The structure of the turbofan engine is surrounded by a bypass passage from the front fan blade equipment (35) with a speed reduction and a variable pitch front fan blade, and the free turbine is provided with a circumferential plate (29) for ejection. The ring rotor and fan connected to the free turbine and shaft from the control of the annular sliding door (Y) that opens the side wall of the free turbine chamber (X) The ratio between the rolling force and the jet spray output is variable, and the opening and closing of this sliding door is an engine of choice of rotational propulsion and jet propulsion, and the sliding door opening and closing valve (33) and front fan are appropriately Jet nozzles (37) with various caliber nozzles (37) provided at the bypass opening / closing door (32) at appropriate positions are provided as auxiliary equipment for levitation, and jet flight from ring rotor and fan flight during cruise flight Is switched from the annular sliding door (Y) and the front fan opening / closing door (32) control in the free turbine chamber to gradually increase the jet ejection amount, and connect the drive shaft to the ring rotor and fan to the clutch (38) and rotary brake (40 ) Stop, the ducted ring rotor and fan equipment are sealed with the main wing upper and lower sliding doors (28), and the free turbine section sliding door is fully opened・ By adjusting the air volume of the front fan blade with variable pitch inside the duct of the air intake and the air volume of the open / close door (32) and the external door (56) in the duct of the air intake, bypass for jet propulsion with an arbitrary exhaust air volume The turbine rotation jet propulsion and aircraft flight speed turbofan engine suitable for the specific engine speed, and the ducted equipment storage becomes the horizontal take-off and landing aircraft from the speed jet propulsion, the ducted equipment The half-open control flight of the jet ejection slide door deployed from the main wing becomes the STOL aircraft of the turboprop engine used in combination with the jet propulsion and rotary propulsion, and the jet ejection slide door is fully closed by the ducted ring rotor aircraft and fan. This is a single flight of the aircraft. Engine and turbofan engine V / STOL machine, output increased to turbojet and afterburner engine (57), and the fan floating of the volume expansion door (V) with the fuselage lower part deployed (R) A twin-rotation turbo-shaft engine tilt-rotor machine and a tilt-fan machine that are equipped with various control devices linked to each other, and that make it easy to take off and land and take off from the selected engine flight. The V / STOL aircraft of the twin-engine turboshaft engine is a twin-engine turboshaft engine that is fixed to the main wing side at the top of the fuselage, and is equipped with a ring rotor (S2 ), Or equipped with a ring fan (S2) and a vertical levitation fuselage with a shaft connection, stable horizontal levitation and fine adjustment of the fuselage can be performed by opening and closing valves (annular slide doors in the free turbine chamber (X) of the turboshaft engine). 33) and an open / close valve (55) for the front fan unit, communicating nozzles and separate small-diameter nozzle pipes to the left and right main wings, horizontal tail tips, fuselage tips, and fuselage rear nozzle outlets (37 ) Control, and the forward movement from the hovering gradually increases the jet ejection amount from the control of the annular sliding door (Y) and the variable front fan opening / closing door (32) in the free turbine chamber. With the clutch (38) and rotary brake (40) stopped, the main wing is sealed with the upper and lower slide covers (28), and it becomes jet flight, the structure of jet flight from the rising of VTOL, jet takeoff and landing and The all-weather twin-engine V / STOL fuselage of the departure ship, and the lower part of the fuselage is appropriately constructed with the auxiliary structure of the fan expansion (R) of the volume expansion door (V) of the deployment, inside the free turbine room and variable front fan part The control of the outside opening and closing doors (32, 56) is a low bypass turbofan engine, and the output increase is a turbojet afterburner engine (57), comprising various control devices. V / STOL plane with twin-engine turboshaft engine.

Images