CN110744978A - Boosting triphibian coaxial double-rotor wing vertical lift aerobat - Google Patents
Boosting triphibian coaxial double-rotor wing vertical lift aerobat Download PDFInfo
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- CN110744978A CN110744978A CN201810807975.3A CN201810807975A CN110744978A CN 110744978 A CN110744978 A CN 110744978A CN 201810807975 A CN201810807975 A CN 201810807975A CN 110744978 A CN110744978 A CN 110744978A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
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Abstract
The boosting triphibian coaxial double-rotor wing vertical lift flying vehicle is one capable of running on ground, sea and in the air or hovering. The system mainly comprises a vehicle body system, an engine system, a parachute-falling assisting system, a coaxial double-rotor system, a fuel tank, an electric electronic light instrument control system, a coupler system, a transfer case system, a steering system, a transmission system, a propeller system, a brake system, a running system, a combat system, a comprehensive system and the like. The helicopter can freely select ground, sea or air operation according to the situation. Generally, a single engine is adopted, and the rotor wings rotate forwards and reversely for double rotor wings and can be automatically folded in a rotating mode. And when flying at high speed, a boosting turbofan engine is adopted. When the engine has a fault, the landing aid umbrella is opened to safely land, and a main engine and an auxiliary engine can also be adopted. The invention has the advantages of good safety, high speed, low manufacturing cost and good maneuverability, is suitable for vehicles such as rescue and relief work, army combat, frontier patrol, public security duty, forest fire prevention, government, enterprises, individuals and the like, and has very wide application.
Description
Technical Field
The invention relates to a vertical lifting aircraft capable of running on land, sea and air, in particular to a boosting type coaxial double-rotor-wing vertical lifting aerocar taking a turbofan or fan engine as auxiliary power. The invention aims to provide a land, sea and air triphibian coaxial double-rotor helicopter with a boosting function, and the operation mode and the state can be rapidly changed according to the operation environment and requirements.
Background
At present, the main transportation tools of human society are automobiles and trains running on land; amphibious vehicles, ships and aircraft operating in the air operating on water surfaces. The boosting type triphibian coaxial double-rotor helicopter flying vehicle can operate in any traffic space and environment. Particularly in military island-climbing operations, the aircraft can sail from the water surface in order to avoid monitoring of airborne radar. After landing, the vehicle runs on the road and can hover in place like a helicopter flying vertically when encountering an obstacle. For long-distance targets, to quickly reach the destination, the tail-boosted turbofan engine is started. The horizontal flying speed of the helicopter can be increased by multiple times. When the boosting coaxial dual-rotor helicopter flyer is used for performing military missions, a radar, a machine gun, a laser weapon, an electronic weapon, a small and micro missile and the like can be installed.
The boosting type land, sea and air triphibian coaxial double-rotor helicopter is suitable for civil use: emergency plans such as earthquake resistance, flood disaster, snow disaster, marine disaster, volcano, rescue and relief disaster, geological survey, mail and power transmission, emergency rescue, forest fire prevention, medical health, meteorological detection, ocean monitoring, remote sensing and mapping, drug contraband and smuggling, aerial sightseeing, air seeding and forestation, insect pest prevention, aeronautical and sports, aerial surveying, scientific investigation, offshore oil development, patrol of high-voltage transmission lines and oil transmission pipelines, and field operation, transportation and tourism in desert, marsh, sea surface, island and mountainous area inconvenient traffic areas; government agencies, enterprises and institutions, families, individuals and other vehicles. And is suitable for military use: army combat, high-altitude reconnaissance, target tracking, frontier patrol, police duty and the like. The vertical lift aerodyne has the advantages of good safety, high speed, compact structure, low cost and good maneuverability, and can vertically lift, fly, stay in the air, travel on the ground and navigate on the water surface. The device does not need runways and airports, and can rise and fall in roads, fields, swamps, deserts, water surfaces, roofs and large yards. Is an ideal vehicle in the 21 st century and is an air private car of modern and future common people. The invention has the patent numbers: the patent ZL961166126 briefly describes the general structure of a helicopter, and does not relate to the construction scheme and application of booster and triphibious operation of land, sea and air, and weaponry.
Disclosure of Invention
The purpose of the invention is realized by the following technical scheme:
the boosting type land, sea and air triphibian coaxial double-rotor helicopter consists of a vehicle body system, a boosting engine system, a power system, a transmission system, a steering system, a running system, a braking system, a coaxial double-rotor system, a propeller system, an electric and electronic instrument light signal control system, an air conditioning system, a fighting system, a parachute-falling assisting system, an oil tank, a comprehensive system and the like.
The main functions of the vehicle body system are to bear drivers and position devices of various systems. Consists of a vehicle body, a tail wing, a seat and the like. The vehicle body is of a main beam type aluminum alloy or carbon fiber structure, and the bottom of the air-ground cab is horizontally and totally closed. As shown in fig. 13. The ship bottom of the land, sea and air type cab is in arc-shaped full-closed. As shown in fig. 14 and 15.
The main function of the power system is to generate power. The horizontal boosting type engine consists of a single engine or a main engine, an auxiliary engine and a horizontal boosting turbofan or fan engine. The engines are all four-stroke gasoline engines, and the single engine is used for land running, water surface navigation and air flight. The main engine can also adopt a turboshaft engine, and is mainly used for normal flight of the helicopter. The auxiliary engine is mainly used for driving on land, navigating on water and flying in the air, and can quickly replace the main engine to fly when the main engine breaks down. The boosting turbofan engine is mainly used for high-speed horizontal flight of the helicopter.
The transmission system mainly has the function of transmitting power to wheels, propellers and rotors. There are three forms of road driving transmission, water surface navigation transmission and air flight transmission.
1. The road driving transmission system mainly comprises a coupler or an auxiliary coupler, a front transmission shaft, a universal joint, a transfer case, a rear transmission shaft and a universal joint, a rear axle transmission system (comprising a speed reducer, a differential and a half shaft) and wheels.
2. The water surface navigation transmission system mainly comprises (1) a coupler, a front transmission shaft, a universal joint, a transfer case, a propeller transmission shaft and a propeller. (2) The auxiliary coupler, the front transmission shaft, the universal joint, the transfer case, the rear transmission shaft, the rear axle system and the wheel water spinner. (3) Auxiliary coupler, front transmission shaft, universal joint, transfer case, propeller transmission shaft, propeller system and the like
3. The aerial flight transmission system mainly comprises (1) a coupler, a front transmission shaft, a universal joint, a transfer case, a rotor wing transmission system and a rotor wing system. (2) The main coupling, the main transmission system, the rotor wing system and the like. (3) The auxiliary coupling, preceding transmission shaft, universal joint, transfer case, intermediate gear pair, main drive system, rotor transmission system, rotor system constitute.
The steering system has the main function of controlling the movement direction of the helicopter, including ground running, water surface running and air flying. Mainly comprises a steering gear, a tie rod, a drag link, a steering angle, a rotor system, an empennage, a rudder and the like.
The main function of the running system is to enable the vehicle to move in parallel on the road through the rotation of wheels. Mainly comprises a front axle, a rear axle, front wheels, rear wheels and the like.
The main function of the braking system is to control the driving, sailing or flying speed of the helicopter, and to decelerate or stop. Consists of a pedal hydraulic brake, a hand brake, a transfer case and an accelerator.
(1) The pedal hydraulic brake mainly refers to a hydraulic brake master cylinder, a slave cylinder, brake shoes, a brake drum, an oil pipe and the like. The pedal hydraulic brake is used for decelerating or braking when the ground runs. Meanwhile, the speed reduction and braking of the propeller or the rotor wing can be switched.
(2) The hand brake includes: brake discs, brake pads, brake levers, and the like. The brake is mainly used for parking braking.
(3) The power between the engine and the wheels, the water spinner, the propeller and the rotor wing is cut off or connected by the transfer case.
(4) The throttle minimizes the power and speed of the engine.
The coaxial double-rotor system mainly has the functions of enabling the helicopter flyer to vertically lift, stop in the air and horizontally fly. The rotary wing steering mechanism consists of a rotary wing, a rotary wing inner shaft, a rotary wing outer shaft, a steering regulator, a transmission pair, a rotary wing transmission system and the like. The rotor totally 2 layers, every layer becomes 90 degrees by 2 blades each other, and the rotor can expand or fold soon automatically.
The boosting engine system mainly has the function of improving the speed of the helicopter in the horizontal direction, and consists of 2 turbofan engines or fan engines, and after the engines are started, the horizontal flying speed of the helicopter is improved by 2-4 times.
The fuel system is a supply system of the energy of the helicopter. An oil pump is arranged on the engine and used for conveying fuel from a fuel tank to an electronic fuel injection and a cylinder of the engine. The fuel oil is burnt to generate heat to do work to push the vertical lift aerodyne to operate.
The air conditioning system provides fresh air which is filtered, dehumidified, heated or cooled into the cabin of the helicopter.
The comprehensive system comprises a helicopter flying vehicle control system, a hydraulic transmission system, a deicing system, vehicle-mounted equipment and the like.
1. The steering system includes a vertical elevator, a rudder or steering wheel, an empennage, etc. The main functions are to realize pitching, hovering, tilting, left-right steering and the like by matching with a steering wheel.
2. The hydraulic transmission system is a complete device which takes oil as a working medium and drives an actuating mechanism to complete specific operation actions by means of oil pressure.
3. The deicing system is a device for preventing the surface of the body of the helicopter from icing or effectively removing an ice layer when icing.
4. The vehicle-mounted equipment mainly provides the working state information of the helicopter and the system thereof for the driver. The vehicle-mounted navigation system mainly comprises a Beidou navigation system, an altimeter, a computer, a camera, multimedia, a sound box, a reversing radar and the like.
The electric electronic light instrument control system has the main function of controlling all mechanisms of the helicopter flying car to operate orderly and providing power. The device consists of a storage battery, a switch, an ignition coil, a spark plug, a starting motor, a generator, light, a loudspeaker, an instrument, an electronic or intelligent control system and the like.
The main function of the battle system is to catch enemy targets during fighting and to launch active attacks and attacks on the enemy targets. The device consists of radar, a machine gun, an ultrasonic weapon, a laser weapon, an electronic interference weapon, a small and micro missile and the like. Including ammunition magazines, shooting cradles, sights, etc.
The parachute-falling assisting system has the main function of ensuring that the parachute can safely land after the helicopter engine or the main engine and the auxiliary engine simultaneously break down. Comprises a spherical umbrella ball, a composite falling-assisting umbrella made of high-fiber textiles and the like. Mounted on top of the rotor system. The device is used when the engine fails.
The transmission principle of the helicopter flying vehicle in various running states is as follows:
1. land driving
(1) The single engine is adopted, and the main working principle is that the engine drives → the coupler → the front transmission shaft and the universal joint → the transfer case → the rear transmission shaft and the universal joint → the rear axle transmission system → the wheels, so that the helicopter is driven on the road, as shown in fig. 7.
(2) The main working principle of the auxiliary engine is that the auxiliary engine drives → the auxiliary coupler → the front transmission shaft and the universal joint → the transfer case → the rear transmission shaft and the universal joint → the rear axle transmission system → the wheels, so that the helicopter is driven on the road.
2. Sailing on sea
(1) When sailing on the sea, the main working principle is to use a single engine to drive → coupler → front transmission shaft and universal joint → transfer case → propeller transmission shaft → ship propeller system, so that the helicopter is sailing on the water surface, as shown in fig. 7.
(2) When navigating on the sea, the main working principle is that the helicopter is driven by the auxiliary engine → the auxiliary coupler → the front transmission shaft and the universal joint → the transfer → the propeller transmission shaft → the ship propeller system, and the helicopter is navigated on the water surface, as shown in fig. 10.
(3) When navigating on the water surface, the main working principle is that the helicopter is driven by the auxiliary engine → the auxiliary coupler → the front transmission shaft and the universal joint → the transfer case → the rear transmission shaft and the universal joint → the rear axle transmission system → the wheel water rotator, as shown in fig. 11.
(4) When navigating at high speed on the sea, the main working principle is that when the single engine is driven → the coupler → the front transmission system and the universal joint → the transfer case → the propeller transmission shaft → the ship propeller system operates normally, the boosting turbofan engine is started to push the helicopter to navigate at high speed on the sea, as shown in fig. 7.
3. Flying in the air
When flying in the air, the main working principle is as follows:
(1) when the helicopter is flying normally, a single engine is adopted to drive → the coupler → the front transmission shaft and the universal joint → the transfer case → the rotor transmission system → the coaxial double-rotor system, as shown in fig. 7.
(2) When the helicopter is flying normally, the main engine is adopted to drive → the main coupler → the main transmission system → the rotor transmission system → the coaxial double-rotor system, as shown in fig. 10.
(3) When the main engine of the helicopter has a fault, the auxiliary engine is adopted for driving → the auxiliary coupling → the front transmission shaft and the universal joint → the transfer case → the intermediate gear pair → the main transmission system → the rotor transmission system → the coaxial double-rotor system, as shown in fig. 10.
(4) When the main engine fails, the auxiliary engine quickly replaces the main engine to continue flying. When the main engine and the auxiliary engine simultaneously break down, the falling assisting umbrella is quickly opened, so that the helicopter flyer can safely land in the air, as shown in fig. 10. .
(5) When the helicopter is flying at a high speed, the booster turbofan or fan engine is started while the system such as the engine (or the main engine) is working normally, as shown in fig. 7.
The structure and features of the present invention may be further understood by reference to the accompanying drawings in which:
FIG. 1 is a front view of an air-ground type coaxial dual-rotor helicopter
FIG. 2 is a left side view of an air-ground type coaxial dual-rotor helicopter
FIG. 3 is a view of a flying car
FIG. 4 is a main view of a land, sea and air type coaxial dual-rotor helicopter
FIG. 5 is a left side view of the air-ground type coaxial dual-rotor helicopter
FIG. 6 is a view of a land, sea and air type coaxial dual-rotor helicopter
FIG. 7 is a diagram of a boosting land, sea and air type single engine working transmission system
FIG. 8 is a diagram of a boosting air-ground type single engine working transmission system
FIG. 9 is a diagram of an air-ground type single engine operating transmission system
FIG. 10 is a diagram of the propeller operating transmission system of the boosting type land, sea and air main and auxiliary engines
FIG. 11 is a diagram of a water-rotating wheel working transmission system of a boosting type land, sea and air type main engine and auxiliary engine
FIG. 12 is a schematic view of a boosting type airborne dual-rotor helicopter
FIG. 13 is a front view of a body of an airborne coaxial dual-rotor helicopter
FIG. 14 is a front view of a land, sea and air type coaxial dual-rotor helicopter
FIG. 15 is a left side view of a land, sea and air type coaxial dual-rotor helicopter
Parts in the figures are labeled as follows: 1. the system comprises a vehicle body system, a boosting turbofan engine system, a booster parachute, a coaxial double-rotor system, an air conditioner, an electric and electronic instrument light control system, a tail wing, a steering system, a 9 engine, a 10 coupler, a 11 transfer case, a 12 rear axle transmission system, a 13 auxiliary engine, a 14 rotor transmission system, a 15 main coupler, a 16 main engine, a 17 auxiliary coupler, a 18 front axle, a 19 rear axle, a 20 front transmission shaft, a 21 wheel water spinner, a 22 wheel, a 23 rear transmission shaft, a 24 main transmission system, a 25 universal joint, a 26 propeller transmission shaft, a 27 propeller, a 28 combat system, a 29 fuel tank, a 30 comprehensive system and a 31 gap axle transmission pair.
The embodiments are further described with reference to the accompanying drawings.
Example 1: when the invention is used for army island-robbing or border defense patrol, the single-engine boosting type navy, land and air triphibian coaxial double-rotor helicopter mainly comprises a vehicle body system 1, a boosting turbofan engine system 2, a landing boosting umbrella 3, a coaxial double-rotor system 4, an air conditioner 5, an electric and electronic instrument light control system 6, a tail wing 7, a steering system 8, an engine 9, a coupler 10, a transfer case 11, a rear axle transmission system 12, a rotor wing transmission system 14, a front axle 18, a rear axle 19, a front transmission shaft 20, wheels 22, a rear transmission shaft 23, a universal joint 25, a propeller transmission shaft 26, a propeller 27, an operation system 28, a fuel tank 29, a comprehensive system 30 and the like.
Before taking an island, a troop flies to the sea from army camp on continents and navigates from the sea to the opposite bank in order to prevent the opposite enemy or radar from finding the enemy. After the island is landed, the vehicle rapidly runs from the ground to the target, when an obstacle is met, the vehicle vertically takes off the straight running target immediately, and attacks or controls the enemy fire.
For this purpose, the engine 9 is first started to drive the coupler 10, then the front transmission system 20, the universal joint 25, the transfer case 11, the rotor transmission system 14, and the coaxial dual-rotor system 4, so that the helicopter is vertically lifted. And then starting the boosting turbofan engine system 2 to fly to the seaside at a high speed. After landing on the sea, the transfer case 11 is switched. The engine 9 drives the coupler 10, then drives the front transmission shaft 20, then drives the propeller transmission shaft 26 through the actuator 11, and then drives the sailing propeller 27 to make the helicopter start sailing on the water, and the bottom of the vehicle body is closed into an arc shape as shown in fig. 14 and 15. If rapid arrival to bank is not desired, the booster engine system 2 is shut down. After the landing, the transfer case 11 is operated to cut off the propeller shaft 26 and the propeller 27. And the rear drive shaft 23, the rear axle drive system 12 and the wheels 22 are switched on, from the sailing state to the driving state. When the helicopter encounters an obstacle in the ground running process, the transfer case 11 is immediately switched, the rear axle transmission system 12 and the wheels 22 are switched off, the rotor wing transmission system 14 is switched on, and the coaxial double-rotor wing system 4 is driven, so that the helicopter is switched into an air flight state from the road running. When the target is reached quickly, the boosting engine is started immediately, and the flying speed can be increased by 3-4 times. When encountering a fire point or an attack target, the combat system 28 is immediately started, and the Beidou navigation and radar system is utilized to initiate active attack to the target. The target is precisely hit by using a machine gun or an ultrasonic weapon, a laser weapon, an electronic interference weapon, a small and micro missile, and the like. As shown in fig. 7. If the engine 9 breaks down, the parachute-falling assisting switch is pressed, the parachute ball of the parachute-falling assisting 3 at the top of the rotor wing is opened, the parachute-falling assisting 3 pops up, the parachute-falling assisting 3 is unfolded under the action of airflow, and the helicopter flyer lands safely.
Example 2: when the booster land, sea and air triphibian coaxial double-rotor helicopter disclosed by the invention is used for rescue and relief work, public security duty and target tracking, the booster land, sea and air triphibian coaxial double-rotor helicopter mainly comprises a vehicle body system 1, a booster turbofan engine system 2, a booster parachute 3, a coaxial double-rotor system 4, an air conditioner 5, an electric electronic instrument light control system 6, a tail wing 7, a steering system 8, a transfer case 11, a rear axle transmission system 12, an auxiliary engine 13, a rotor transmission system 14, a main coupling 15, a main engine 16, an auxiliary coupling 17, a front axle 18, a rear axle 19, a front transmission shaft 20, a wheel water rotator 21, a wheel 22, a rear transmission shaft 23, a main transmission system 24, a universal joint 25, a propeller transmission shaft 26, a propeller system 27, a combat system 28, a combat system 29, a comprehensive system 30, a bridge gear pair 31 and the like.
The auxiliary engine 13 is first started to drive the auxiliary coupler 17, the front transmission shaft 20 and the universal joint 25, the transfer case 11, the rear transmission shaft 23 and the universal joint 25, the rear axle transmission system 12 and the wheels 22 to drive the helicopter to exit the parking garage. Then, the main engine 16 is started to drive the main coupler 15 and the main transmission system 24, the rotor transmission shaft 14 is driven, the coaxial dual-rotor system 4 is driven to take off, the auxiliary engine 13 is turned off, and the helicopter is in a state of frontier defense patrol or rescue and relief work. If the target tracking is met, the boosting engine 2 is started, and the helicopter flyer flies horizontally at a high speed. If the main engine 16 breaks down, the auxiliary engine 13 is immediately started to drive the auxiliary coupler 17, the front transmission shaft 20 and the transfer case 11, the intermediate gear pair 31 and the main transmission system 24 are driven, and the coaxial dual rotors 4 are driven to rotate through the rotor transmission system 14, so that the auxiliary engine 13 quickly replaces the main engine 16 to continue flying. If the main engine 16 and the auxiliary engine 13 simultaneously have faults, the parachute-falling assisting switch is pressed, the parachute ball of the parachute-falling assisting 3 at the top of the rotor wing is opened, the parachute-falling assisting 3 pops up, the parachute-falling assisting 3 is unfolded under the action of airflow, and the helicopter aerodyne is safely landed. If the helicopter is landed on the sea, the helicopter floats on the water surface because the bottom of the helicopter body is closed, and the boosting engine 2 is started, so that the helicopter can sail on the sea. The steering system 8 of the helicopter is used for controlling the running direction of the helicopter on the road, on the water and in the air. As shown in fig. 10.
Example 3: when the booster-type land-air amphibious helicopter disclosed by the invention is used for petroleum pipeline or high-voltage transmission line detection, government, enterprise and public transport means, the booster-type land-air amphibious helicopter mainly comprises a vehicle body system 1, a booster turbofan engine system 2, a booster parachute 3, a coaxial dual-rotor system 4, an air conditioner 5, an electric and electronic instrument light control system 6, a tail wing 7, a steering system 8, an engine 9, a coupler 10, a transfer case 11, a rear axle transmission system 12, a rotor wing transmission system 14, a front axle 18, a rear axle 19, a front transmission shaft 20, wheels 22, a rear transmission shaft 23, a universal joint 25, a fuel tank 29, a comprehensive system 30 and the like.
The engine 9 is started first, the coupler 10 is driven, the front transmission shaft 20 and the universal joint 25 are driven, the transfer case 11 is driven, the rear transmission shaft 23 and the universal joint 25 are driven, the rear axle transmission system 12 is driven, and the wheels 22 are driven, so that the helicopter is driven out of the parking garage and out of the urban area. The transfer case 11 is switched off to cut off the rear transmission shaft 23, the transfer case 11 is connected with the rotor wing transmission system 14 to drive the coaxial double-rotor wing system 4, so that the helicopter flyer flies vertically, if high-speed flying is needed, the boosting type engine 2 is started, the bottom of the helicopter flyer body is sealed into a plane, as shown in fig. 13, and then the helicopter flyer flies to a target at high speed. After the task is finished, the helicopter returns to the outside of the city to land, the rotor transmission system 14 is cut off, the transfer case 11 is converted into the rear transmission shaft 23 and the universal joint 25, the rear axle transmission system 12 is driven, the wheels 22 are driven to rotate, and the helicopter enters the garage when entering the city. If the engine 9 of the helicopter breaks down, the parachute-falling assisting device 3 is switched on and off, the parachute ball of the parachute-falling assisting device 3 at the top of the rotor wing is opened, the parachute-falling assisting device 3 pops up, the parachute-falling assisting device 3 is unfolded under the action of airflow, and the helicopter is safely landed. If the helicopter is landed on the sea surface, the bottom is closed, so that the sufficient draft is kept, and the helicopter floats on the water surface and is repaired, as shown in fig. 8.
Example 4: the invention is used for earthquake relief, forest fire prevention, agricultural pest control and fertilization, and the land-air amphibious helicopter mainly comprises a vehicle body system 1, a landing-assisting umbrella 3, a coaxial dual-rotor system 4, an air conditioner 5, an electric and electronic instrument light control system 6, a tail wing 7, a steering system 8, an engine 9, a coupler 10, a transfer case 11, a rear axle transmission system 12, a rotor transmission system 14, a front axle 18, a rear axle 19, a front transmission shaft 20, wheels 22, a rear transmission shaft 23, a universal joint 25, a fuel tank 29 and the like.
Firstly, the engine 9 is started to drive the coupler 10, the front transmission shaft 20 and the universal joint 25 are driven, then the transfer case 11 is driven, the rear transmission shaft 23 and the universal joint 25 are driven, the rear axle transmission system 12 is driven, and the wheels 22 are driven to enable the vertical lift aerodyne to reach an operation site. After being filled with pesticide or chemical fertilizer or fire extinguishing agent, the transfer case 11 is switched to cut off the rear transmission shaft, the transfer case 11 is connected with the rotor transmission system 14 to drive the coaxial dual-rotor system 4, so that the helicopter is vertically lifted to fly, and the bottom of the body of the helicopter is sealed into a plane, as shown in fig. 13. After the task is completed, the helicopter returns to the operation site to land, the rotor wing transmission system 14 is cut off, the transfer case 11 is converted into the rear transmission shaft 23 and the universal joint 25, the rear axle transmission system 12 is driven, the wheels 22 are driven to rotate, and the helicopter is driven into a garage. If the engine 9 of the helicopter breaks down, the parachute-falling assisting device 3 is switched on and off, the parachute ball of the parachute-falling assisting device 3 at the top of the rotor wing is opened, the parachute-falling assisting device 3 pops up, the parachute-falling assisting device 3 is unfolded under the action of airflow, and the helicopter is safely landed. If the helicopter is landed on the sea surface, the helicopter floats on the water surface for repair due to the closed bottom, as shown in fig. 9.
Claims (10)
1. The utility model provides a coaxial pair of rotor helicopter of single engine of boosting formula land, sea and air triphibian, mainly by automobile body system (1), boosting turbofan engine system (2), helping parachute (3), coaxial pair rotor system (4), air conditioner (5), electric and electronic instrument light control system (6), fin (7), a steering system (8), engine (9), coupler (10), transfer case (11), rear axle transmission system (12), rotor transmission system (14), front axle (18), rear axle (19), preceding transmission shaft (20), wheel (22), rear drive shaft (23), main drive system (24), universal joint (25), screw transmission shaft (26), screw (27), combat system (28), fuel tank (29), integrated system (30) etc. constitute. The main characteristics are as follows:
when driving on the groundDriving of an engine (9) → a coupler (10) → a front drive shaft (20) and a universal joint (25) → a transfer case (11) → a rear drive shaft (23) and a universal joint (25) → a rear axle transmission system (12) → transmitting power to wheels (22);
when navigating on water surfaceDriving of an engine (9) → a coupling (10) → a front transmission shaft (20) and a universal joint (25) → a transfer case (11) → a propeller transmission shaft (26) → transmitting power to a propeller (27);
in flightThe engine (9) drives → the coupler (10) → the front drive shaft (20) and the universal joint (25) → the transfer case (11) → the rotor drive system (14) → transmitting power to the coaxial twin rotors (4).
At high speed of flightThe left and right two booster turbofan or fan engine systems (2) are activated as shown in fig. 7.
2. The utility model provides a coaxial twin rotor helicopter of two engines on boosting formula land air, mainly by automobile body system (1), boosting turbofan engine system (2), help parachute (3), coaxial twin rotor system (4), air conditioner (5), electric and electronic instrument light control system (6), fin (7), a steering system (8), engine (9), coupler (10), transfer case (11), rear axle transmission system (12), rotor transmission system (14), front axle (18), rear axle (19), preceding transmission shaft (20), wheel (22), rear drive shaft (23), universal joint (25), operation system (28), fuel tank (29), integrated system etc. constitute (30) etc. and constitute. The main characteristics are as follows:
when driving on the groundDriving of an engine (9) → a coupler (10) → a front drive shaft (20) and a universal joint (25) → a transfer case (11) → a rear drive shaft (23) and a universal joint (25) → a rear axle transmission system (12) → transmitting power to wheels (22);
in flightThe engine (9) drives → the coupler (10) → the front drive shaft (20) and the universal joint (25) → the transfer case (11) → the rotor drive system (14) → transmitting power to the coaxial twin rotors (4).
At high speed of flightThe left and right two booster turbofan engine systems or fan engines (2) are started, as shown in fig. 8.
3. The utility model provides a coaxial twin-rotor helicopter of land and air single engine, mainly by automobile body system (1), help umbrella (3), coaxial twin-rotor system (4), air conditioner (5), electric and electronic instrument light control system (6), fin (7), a steering system (8), engine (9), coupler (10), transfer case (11), rear axle transmission system (12), rotor transmission system (14), front axle 18(), rear axle (19), front drive axle (20), wheel (22), rear drive axle (23), universal joint (25), operation system (28), fuel tank (29), integrated system (30) etc. constitute. The main characteristics are as follows:
when driving on the groundDriving of an engine (9) → a coupler (10) → a front drive shaft (20) and a universal joint (25) → a transfer case (11) → a rear drive shaft (23) and a universal joint (25) → a rear axle transmission system (12) → transmitting power to wheels (22);
in flightEngine (9) drive → coupler (10) → front drive shaft (20) and universal joint (25) → transfer case (11) → rotor drive system (14) → transfer power to coaxial twin rotor (4), as shown in fig. 9.
4. A boosting type land, sea and air triphibian main and auxiliary engine coaxial double-rotor helicopter mainly comprises a vehicle body system (1), a boosting turbofan engine system (2), a boosting parachute (3), a coaxial double-rotor system (4), an air conditioner (5), an electric and electronic instrument light control system (6), an empennage (7), a steering system (8), a transfer case (11), a rear axle transmission system (12), an auxiliary engine (13), a rotor transmission system (14), a main coupler (15), a main engine (16), an auxiliary coupler (17), a front axle (18), a rear axle (19), a front transmission shaft (20), a wheel water rotator (21), wheels (22), a rear transmission shaft (23), a main transmission system (24), a universal joint (25), a propeller transmission shaft (26), a propeller (27), a combat system (28), a fuel tank (29), A comprehensive system (30), a gap bridge transmission pair and the like (31), as shown in figure 7. The main characteristics are as follows:
(1)when driving on landThe auxiliary engine (13) is adopted for driving → the auxiliary coupler (17) → the front transmission shaft (20) → the universal joint (25) → the transfer case (11) → the rear transmission shaft (23) → the universal joint (25) → the rear axle transmission system (12) → the wheel (22);
(2)when navigating on water surface，
1) The helicopter is driven by the auxiliary engine (13) → the auxiliary coupling (17) → the front drive shaft (20) and the universal joint (25) → the transfer case (11) → the propeller drive shaft (26) → the propeller (27) to rotate, so that the helicopter sails on the sea surface, as shown in fig. 10.
2) The auxiliary engine (13) is adopted for driving → the auxiliary coupler (17) → the front transmission shaft (20) the universal joint (25) → the transfer case (11) → the rear transmission shaft (23) → the universal joint (25) → the rear axle transmission system (12) → the wheel spinner (21) for rotating, as shown in fig. 11.
3) When navigating on the sea, if the main engine and the auxiliary engine simultaneously break down, the boosting turbofan engine is adopted to drive the helicopter to navigate on the sea.
4) And when the system is designed, 1) and 2) select one of the components.
(3)In flight，
1) The helicopter flies in the air by adopting the driving of a main engine (16), the rotation of a main coupler (15), the rotation of a main transmission system (24), the rotation of a rotor transmission system (14) and the rotation of a coaxial double rotor (4).
2) If the main engine has a fault, the auxiliary engine (13) is adopted to drive → the front transmission shaft (20) → the universal joint (25) → the transfer case (11) → the intermediate gear pair (31) → the main transmission system (24) → the rotor transmission system (14) → the coaxial double-rotor system (4) to rotate, so that the helicopter continues flying in the air, as shown in fig. 10.
3) When the helicopter flies at a high speed, the main engine (16) drives → the coupler (15) → the main transmission system (24) → the rotor transmission system (14) → the coaxial double rotor (4) or the auxiliary engine (13) drives → the auxiliary coupler (17) → the front transmission system (20) → the universal joint (25) → the intermediate gear pair (31) → the main transmission system (24) → the rotor transmission system (14) → the rotor system (4) and in a normal operation state, the booster turbofan or fan engine system (2) is started, as shown in fig. 10, 11 and 12.
5. According to claim 1, 2, 3, 4, a boosting type land, sea, air and air triphibious coaxial double-rotor helicopter parachute-assisted system (3) is mainly characterized in that: when the engine fails or the main engine and the auxiliary engine simultaneously fail, the parachute-falling assisting switch is pressed, the parachute ball of the parachute-falling assisting (3) at the top of the rotor wing is opened, and the parachute-falling assisting (3) is rapidly opened under the action of wind power, so that the helicopter flyer can safely land in the air, as shown in fig. 7.
6. According to the claims 1, 2, 3 and 4, the steering system (8) of the boosting type land, sea and air triphibian coaxial double-rotor helicopter mainly comprises a steering gear, a tie rod, a drag link, a steering angle and the like. The main characteristic of the device is that the device mainly has the main function of controlling the movement direction of the helicopter, including driving on the ground, navigating on the water surface and flying in the air, as shown in figure 7.
7. According to the claims 1, 2, 3 and 4, the body of the boosting type triphibian coaxial double-rotor helicopter is mainly characterized in that the bottom is in a downward arc shape, so that the buoyancy is increased, and the water navigation resistance is reduced; the door and window is sealed to prevent water leakage of the car body, as shown in fig. 14 and 15. The empennage (7) consists of a vertical stabilizing surface and a horizontal stabilizing surface, and is mainly characterized in that the empennage is used for respectively assisting in controlling and adjusting the left and right directions and the lifting direction of the helicopter in air flight, as shown in figure 7.
8. According to the claims 1, 2, 3 and 4, the military is mainly composed of radar, machine gun, ultrasonic weapon, laser weapon, electronic interference weapon, small micro missile, etc. when working. The main characteristic is that the device can defend or actively attack the enemy through self-contained weapons, as shown in figure 7.
9. According to the claims 1, 2, 3 and 4, the boosting type land, sea, air and triphibian coaxial double-rotor helicopter is mainly characterized by comprising two sets of electric and electronic control systems, wherein one set is a manual control system, the other set is an intelligent control system, and the two sets of electric and electronic control systems can be mutually and rapidly switched. In general, an intelligent control system is adopted during high-speed flight.
10. According to the claims 1, 2, 3 and 4, the comprehensive system (30) of the boosting type land, sea and air triphibian coaxial double-rotor helicopter comprises a control system, a deicing system, a Beidou navigation system, an altimeter and vehicle-mounted equipment. The vehicle-mounted device includes: computer, camera, stereo set, back radar, etc. The method is mainly characterized in that the method can control and control the helicopter flying vehicle to run, present, receive or send information of the running process.
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| CN113636077A (en) * | 2021-09-10 | 2021-11-12 | 陕西蓝悦无人机技术有限公司 | Coaxial unmanned aerial vehicle control method |
| WO2024187564A1 (en) * | 2023-03-16 | 2024-09-19 | 易元明 | Air-ground dual-purpose automobile power unit using relative moving air kinetic energy |
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