JP3052090B2 - Aircraft landing gear and control system - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to an aircraft landing gear which attaches a pneumatic motor to an aircraft wheel device, controls a pneumatic circuit during takeoff and landing of the aircraft, and rotates the wheel. Related to control system.

[Prior art] Conventionally, fixed-wing aircraft support the fuselage by an landing gear,
The engine (propulsion device) thrusts on the runway with the propulsion of the engine and lifts up in the air with the lift acting on the wings. However, the running power from the start to the levitation was limited to the propulsion of the engine only.

Therefore, to obtain the lift required for levitation, a long running distance and the maximum output of the engine were required, and fuel consumption and noise generation were further increased.

Also, taking the case of land aircraft for landing, for example, an aircraft that steadily descends in the landing system will reduce the engine output, enter the airport while keeping the aircraft's lift to a minimum, and land using the landing gear, Because the wheels of the landing gear hit the runway violently in a stopped state, there were problems such as damage and damage of tires due to the impact, and impact on the aircraft.

[Problems to be Solved by the Invention] On the other hand, the development of aircraft as the fastest transportation means has been remarkable, and many large-sized aircraft suitable for long-distance flight have been introduced for ordinary passenger and cargo transport aircraft. The cargo capacity of freight passengers has also increased, and the weight of the cargo has increased as well as the weight of the aircraft.

Therefore, the length of the runway required for takeoff, power up of the engine, strengthening of the landing gear, impact mitigation during landing, etc.
It has many challenges.

An object of the present invention is to reduce the sliding distance required for takeoff by mainly rotating the wheels at the time of takeoff of the above-described landcraft and accelerating the running speed by using the wheel power together with the propulsion force of the engine, and Sometimes, the purpose is to reduce the impact of the landing gear by rotating the wheels in accordance with the landing speed, and at the same time, to reduce the seizure, breakage, wear and the like of the tire at the landing point.

Further, the same applies to the case of a seaplane, with the object of shortening the sliding distance on the water surface and allowing water to be separated from a short channel.

[Means for Solving the Problems] Hereinafter, embodiments of the present invention will be described with reference to the drawings.
The figure shows an example in which a pneumatic motor is attached to the shaft of the wheel of the landing gear.

A rotor 3 for rotating wheels is mounted on a shaft 2 fixed to the tip of a column 1, an impeller 4 of a pneumatic motor inside the rotor 3, a brake disk 7 on a flange portion of the rotor 3, and a wheel 8 on a side surface of the flange. Are attached and secured by fastening bolts 12 previously driven in.

Further, the rotor 3 is rotated by a plurality of bearings 10 press-fitted into the shaft portion, and is integrally assembled by a collar 11 provided on the shaft 2.

The brake disk 7 is a donut-shaped disk, the outer periphery of which is fixed to the flange portion of the rotor 3, and a known brake device 9 which is sandwiched between brake pads is mounted inside, and the caliper of the brake device is fixed to the column 1 together with the circular case 6. I have.

The wheel 8 is a normal wheel having an aircraft tire mounted on the wheel, and is mounted on a side surface of the rotor 3 so as to rotate integrally with the impeller 4 of the pneumatic motor.

Next, the pneumatic motor 20 will be described with reference to FIG.
As shown in FIG. 3, the impeller 4 of the pneumatic motor has a water wheel-shaped rotation in which a plurality of curved spoon-shaped blades 5 are formed at the boss 15 of the impeller, and circular side plates are attached to both sides and fixed. The protruding portion of the boss 15 is fitted to the bearing of the circular case 6 with the blade, and a small gap is provided so that the impeller 4 and the circular case 6 do not come in contact with each other, and the bearing is fixed with a bearing. Sealed.

Further, several keys are cut directly on the outer periphery of the rotor 3 to form a spline 17 which is engaged with a groove formed in the boss 15 of the impeller (FIG. 4), and the impeller 4 and the rotor are formed. 3 rotates together and press-fits bearing 10 so that torque is transmitted to the wheel.
Has been assembled.

The pneumatic motor 20 configured as described above connects the pneumatic injection pipe 22 to the connection device 21 attached to the pneumatic inlet 13 of the circular case 6, injects high-pressure air to rotate the impeller,
It is structured to discharge from a discharge port 14 provided in the lower part.

At the mouth of the discharge port 14, an opening / closing lid 23 which is automatically opened by the internal pressure and automatically closes when the pressure is reduced is attached, preventing the intrusion of dust, rainwater, insects and the like from the outside while parked, It plays a role in protecting the impeller from pollution.

Next, the rotation of the pneumatic motor will be described. When the impeller 4 is sealed by a circular case, when the high-pressure air 18 compressed by the pneumatic pressure inlet 13 is injected (arrow), the pressure energy becomes a curved rotation. The impeller 5 is pressurized and flows, and the impeller 4 is rotated in the direction of arrow 19 to be discharged from the discharge port 14.

The connection device 21 attached to the air pressure inlet 13 is an air pressure pipe.
This is a device for joining 22.
It has a detachable function.

The air injection pipe 22 is a connection pipe that connects the pressure circuit inside the fuselage and the pneumatic motor, and has a structure that has heat resistance for sending high-pressure air and cold resistance during flight, and flexibility when pulling out and pulling in wheels. In addition, the flexible structure at the key points, and the main part of the pipeline is tightly attached to a part of the support column in case of an unexpected accident from the outside, and is covered with the cover of the main landing gear.

[Operation] Normally, a commercial transport aircraft taking off from the airport releases the brakes when the engine output reaches the maximum and glides at a gradually increasing speed. A long run distance is required.

Therefore, when the wheel device configured as described above is attached and used, the aircraft releases the brakes, starts the forward movement of the fuselage, and simultaneously opens the pressure control valve of the pressure control device to rotate the pneumatic motor, The rotational torque of the pneumatic motor is directly transmitted to the wheels to generate wheel power, which allows the aircraft to move forward with the self-propelled power of the wheels and at the same time assists the propulsion of the engine to accelerate takeoff speed at a stretch, allowing the aircraft to levitate with a short gliding distance. Required take-off speed.

The propulsion force at which the aircraft takes off has an output that gives the aircraft maximum speed and maximum climbing power during flight,
The less the load resistance on the wheels, the faster the aircraft will move forward.

The same applies to the characteristics of a pneumatic motor.When the load resistance at the start is in an overloaded state, the compressive properties of the gas work and the starting torque is slightly weak, but it accelerates steplessly as the load decreases and rotates at high speed in a short time. Can be realized. Therefore, by setting the air flow rate of the pneumatic motor necessary for the takeoff speed in advance, the speed can be increased at an accelerated speed in competition with the propulsion of the engine, and the takeoff can be performed with a short run distance.

In addition, since an aircraft that descends steadily in the landing system lands on the runway with the landing gear pulled out of the fuselage and the wheels stopped, the tires receive heavy impact friction at the time of landing and glide for a moment with white smoke.

However, if the wheel device of the present invention is used, an air motor is operated when entering the runway in the landing system, and the wheels are rotated in accordance with the landing speed, the aircraft landing on the runway at the same speed. If you land on a sprinting car and land, then glide and stop steadily, it will be more stable by reducing tire damage and runway seizure during landing, and alleviating impact of landing gear, etc. It is possible to enter the airport at a reduced speed, which can enhance safety during landing.

As described above, the present invention has an action of accelerating the running speed at takeoff and taking off at a short distance by attaching the pneumatic motor to the wheel device of the aircraft and rotating the wheel to apply power to the wheels, and at the time of landing, Has two functions of reducing the impact of landing by rotating the wheels in accordance with the landing speed.

In recent years, it is a well-known fact that the safety of aircraft during flight is very high due to the sophistication of the fuselage and the advance of flight technology, but there are still many problems in safety at takeoff and landing, The present invention works more safely in the face of disturbances such as snow cover, freezing, icing on the fuselage surface due to the deterioration of seasonal weather conditions, and sudden gusts and thunderstorms around the airport. .

[Example] Hereinafter, an example of the present invention will be described with reference to the drawings.

FIG. 5 and FIG. 6 show a four-wheel structure wheel device in which a plurality of axles are attached to both ends of a frame 31 and a support 30 is fixed to a center portion of the frame. 37 is inserted and installed.

Axles 32 attached to both ends of the frame are pneumatic motors.
33, disk brake 34, wheels 36 are arranged symmetrically,
These are integrally formed, attached to the hub of the wheel, press-fitted with a bearing, and assembled to the axle 32 (this structure is almost the same as that described with reference to FIGS. 1 to 4 above). ing).

Although four pneumatic motors 33 are used in this embodiment, this structure has the advantage that it can drive the wheels during take-off and landing of the aircraft, and at the same time can omit a complicated device that allows the differential of each wheel. And the whole can be made compact and lightweight.

Although the brake device is shown as a single-plate brake device in which the brake disc 34 is sandwiched between pads, a brake device used in an actual large-scale machine combines a multilayer carbon disc and sandwiches several places of the disc simultaneously. The brake disc is integrated inside the wheel.

A tachometer 38 is attached to each of the shafts of the wheels, and a detected signal is read by a computer, and the rotation speed is adjusted by controlling a pressure valve of a pressure control device.

FIG. 7 shows another embodiment in which the pneumatic motor 33 is mounted inside the frame 31, which can be made more compact than those shown in FIGS.

However, the impeller of the pneumatic motor 33 in this case is
As shown in the figure, it is desirable that the left and right impellers be configured in a double configuration so as to be differential. When only one impeller is used, a differential device for the left and right wheels is required.

The embodiment shown in FIG. 9 is an example in which a pneumatic injection device is attached to a main float of a small seaplane.

Nozzle 82 for injecting fluid into main float 81 of seaplane 80
At the base of the nozzle, a jet control device combining a check valve / pressure regulating valve 83 for preventing backflow of fluid and a solenoid valve 84 for opening and closing the pressure circuit is attached and connected and fixed to a pneumatic cylinder 85. ing.

Ideally, the pneumatic cylinder 85 is a replaceable cylinder that is as small and lightweight as possible and can be easily attached and detached.The compressed air that can be used several times is filled outside, and it is used every time.
If you don't need it, just fly with it removed.

The pneumatic cylinder is fixed on both sides with mounting brackets 86 and 87, and the body is fastened with a band 88 so as not to come off from the mounting equipment due to an impact at the time of separation or landing.

In addition to the fitting for fixing the pneumatic tank, a fitting that can be freely attached and detached and a pipe joint that connects the pipes are attached to the fitting 87.

FIG. 10 is an example of a main part of an air pressure source device applied to a large flying boat and the like, and an example of an injection device that draws water from the front using jetting of compressed air and jets the water from a rear portion. A device that is used by connecting it to an engine generator or auxiliary generator, etc.
91, air compressor 92, pneumatic tank 93, and compression regulator 9
4. It is composed of a pressure control valve 95 and the like, and has a structure controlled by an electric circuit connected to a computer 90 of the cockpit.

The injection device is provided with an injection nozzle 96 inside the water absorption pipe 97,
Squeeze the flow path near the injection port slightly narrower and pressurized air from the nozzle.
When 98 is sprayed, a pressure difference is created inside the pipe and water 99
And inject compressed air and water vigorously from the rear.

FIG. 11 is an embodiment showing a configuration of a pneumatic device of the present invention and a control system of a pneumatic circuit.

As shown in the figure, this pneumatic device comprises an air pressure source device 300 and a pressure control device 400 inside the fuselage, and a plurality of wheel devices 500 provided outside the fuselage, and a plurality of pipes branched via the pressure control device. A series of pneumatic circuits connected by roads to rotate the pneumatic motor 501 of the wheel device using the compressed air of the pneumatic source device, and controlled by an electric circuit connected to the cockpit control device 101 It has become.

Also, the electric circuit connected to the computer device 102 of the cockpit is a speedometer (rotometer) of the pneumatic motor.
When connected to 502, the signals detected by the individual speedometers are transmitted to the computer device, and at the same time, the signals are transmitted to the flow control valve.
The pressure control valve 4 connected to the cockpit control 101 by forming a feedback circuit to communicate to 402 and back to the computer device
01 and a flow control valve 402 connected to and connected to the computer device 102, interlocking and controlling each other in response to a command from the computer device, automatically adjusting the flow rate of the pressurized air to thereby control the rotation speed of the pneumatic motor 501. Control.

This control system, especially when the connecting pipe connected to the pneumatic motor outside the fuselage is branched into a plurality, the unbalance of the compressed air caused by the length of each pipe line and the mounting state of the connecting pipe, and the control of the pneumatic motor A system that automatically controls the flow rate of compressed air according to the function status, etc.
It is an important means to solve complicated problems in pneumatic circuits.

Next, the air pressure source device will be described.
Reference numeral 300 denotes an electric motor 301, an air compressor 302, and an air pressure tank 303. The electric power source of the electric motor 301 is an engine (propulsion device) 2
It is connected to 00 and operated from the cockpit.

The compressed air compressed by the air compressor is accumulated in the pneumatic tank 303 through the pipeline, and the compressed air generates a large amount of drain as it is cooled by high temperature and high humidity.
Dry air from which this drain has been removed is used for operation.

Further, the pressure of the pneumatic tank 303 during operation is automatically controlled by a switching operation of the pressure regulator 304 attached to the tank, and the air pressure is kept constant.

As described above, this embodiment is a pneumatic circuit of an aircraft that rotates wheels using compressed air and its control system, and an automatic control system that controls the rotation of a pneumatic motor by an electric circuit connected to a computer device of a cockpit. It is. (This embodiment includes a safety valve, a check valve,
The suction filter, pipe joint, connection device, etc. are omitted and are not described).

The air pressure source device 300 also has a large weight and outer shape when including ancillary equipment, and if there is a problem when actually mounted on an aircraft, the in-flight pressurizing device or ancillary device of the engine, or any of these. A method of using a spare device, a method of attaching only a pneumatic tank and supplying air from an external device on the ground, or a method of replacing a pneumatic tank that can be used several times for each flight may be used.

[Effects of the Invention] This method is based on a method in which a pneumatic motor is attached to a wheel device of an aircraft and a wheel is rotated, so that an aircraft takes off at a short running distance by accelerating a glide speed at takeoff, and a landing device of a landing gear at landing. It has the effect of reducing impact, preventing tire damage and runway seizures, and further enhancing the safety of aircraft taking off and landing.

The effects described above are not limited to aircraft only, but also include economical effects on airport facilities construction costs, runway maintenance costs, etc., fuel savings at takeoff, and solutions to airport problems, including noise problems. Can not be overlooked.

Another object of the present invention is to protect the landing gear from impact during landing so that it is possible to enter and land at the airport at a faster speed than before, and abrupt changes in air pressure and gusts that occur during the landing system. Contributes to its safety even if it is inferred from the effects of preventing stall accidents on the verge of landing due to disturbances such as snowfall, freezing, and thunderstorms caused by the geographical conditions of the airport. The effect of doing is great.

[Brief description of the drawings]

FIG. 1 is an embodiment of a wheel device according to the present invention, and the left half is a sectional view thereof. FIG. 2 is a longitudinal sectional view of a pneumatic motor. FIG. 3 is a cross-sectional view of the pneumatic motor. FIG. 4 is a boss of an impeller and a spline of a rotor. FIG. 5 is another embodiment of the present invention, and is a side view of a wheel device. FIG. 6 is a plan view showing the configuration. FIG. 7 is an application example (of FIG. 6) and FIG. 8 is an enlarged sectional view of a main part thereof. FIG. 9 shows an embodiment of a small seaplane. FIG. 10 is a cross-sectional view of the injection device system and main parts. FIG. 11 shows the pneumatic circuit and control system of the present invention. DESCRIPTION OF SYMBOLS 1 ... Prop of landing gear 2 ... Wheel axle 3 ... Rotor 4 ... Impeller of pneumatic motor 5 ... Rotating blade 7 ... Brake disc 8 ... Wheel 9 ... Brake device 300 ... Air pressure source Device 400 …… Pressure control device 400 …… Wheel device

Claims (3)

(57) [Claims] 1. A pneumatic motor is attached to a plurality of wheel devices which are supported at a lower portion of a fuselage and slides while supporting the fuselage. The pneumatic pressure source device is provided inside the fuselage and a plurality of pressure circuits are connected to the outside of the fuselage. An aircraft landing gear for controlling an electric circuit by connecting an electric circuit to a pneumatic circuit connected to a motor, wherein a pneumatic circuit for rotating the pneumatic motor is branched via a pressure control device (400) and a wheel device outside the fuselage. (500) a plurality of pipelines, and a plurality of pressure control valves (401) and a flow control valve (402) attached to the plurality of pipelines for controlling the pressure of a pneumatic circuit connected to the wheel device. The pressure control valve (401) and the flow control valve (402) of the pressure control device (400) are linked to a feedback circuit individually connected to and connected to the speedometer (502) of the wheel device. Adjust the pressure,
An aircraft landing gear and control system for controlling the pneumatic motor to rotate wheels during takeoff and landing of an aircraft by an electric circuit connected to a computer system of a cockpit. 2. An aircraft landing gear and control system having a pneumatic circuit and an electric circuit according to claim 1, wherein a pneumatic motor is attached to a wheel device outside the fuselage to rotate wheels. 3. The air pressure source device according to claim 1, further comprising at least one air pressure circuit connected to a pressure control device, wherein the air pressure circuit includes another air pressure device mounted on the airframe, and the air pressure circuit is mounted on a bottom of the airframe. Or a landing gear and control system for a watercraft that is connected to a jetting device attached to a main float and jets fluid using gas pressure.