CN108438201B - Polar region multipurpose all-terrain unmanned transportation system - Google Patents
Polar region multipurpose all-terrain unmanned transportation system Download PDFInfo
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- CN108438201B CN108438201B CN201810272813.4A CN201810272813A CN108438201B CN 108438201 B CN108438201 B CN 108438201B CN 201810272813 A CN201810272813 A CN 201810272813A CN 108438201 B CN108438201 B CN 108438201B
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- 238000004378 air conditioning Methods 0.000 claims description 5
- 230000002146 bilateral effect Effects 0.000 claims description 4
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/52—Skis or runners
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0662—Environmental Control Systems with humidity control
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Abstract
The invention relates to a multi-purpose all-terrain unmanned transportation system for polar regions, which comprises foldable wings, an air cushion high lift system and sledges, wherein the foldable wings are connected with the air cushion high lift system; can be transported under different weather and road conditions in different working modes. The unmanned transportation system is added with the cushion lifting system and integrates the appearance of the ground effect vehicle, so that the polar region multipurpose all-terrain unmanned transportation system can freely switch operation modes according to different tasks, weather and road conditions and move in ice, soil, mud, water surface, ground effect areas and free space; the equipment is unmanned, so that the function of 24-hour all-weather duty is achieved; the wings of the invention can be folded and unfolded, and can adapt to narrower road conditions. The unmanned transportation system has the comprehensive characteristics of sledges, hovercraft, ground effect aircrafts and airplanes, and has great polar adaptability and high originality.
Description
Technical Field
The invention relates to a multi-purpose all-terrain unmanned transportation system for polar regions, and belongs to the technical field of transportation.
Background
With the development of science and technology, people gradually turn targets to south and north poles, and a plurality of polar observation stations are established, and due to the complex polar environment, the existing vehicles are usually icebreakers, helicopters, cargo planes and the like. The use environment is single, needs manual operation, can't realize all-weather on duty.
The medical rescue requirements and freight supply of polar regions have the problem of difficult transportation. The adaptability of the existing unmanned aerial vehicle under the polar region environment is insufficient, for example, the cruising ability is insufficient, and the landing condition cannot be met. Therefore, the existing unmanned aerial vehicle cannot be used for polar transportation.
Therefore, there is an urgent need for an effective and extremely versatile vehicle for transportation, feeding and medical assistance in a complex environment.
Disclosure of Invention
In order to solve the problem of difficult polar region transportation, the invention provides a polar region multipurpose all-terrain unmanned transportation system which can operate on ice (ground), a ground effect area and free space outside the ground effect area in six operation modes to realize polar region cargo transportation and medical assistance.
The purpose of the invention is realized by the following technical scheme:
a polar multipurpose all-terrain unmanned transport system comprising: the fuselage comprises a middle fuselage and a foldable wing;
the foldable wings are arranged on two sides of the middle machine body and can be folded upwards and retracted under the driving of the wing folding and unfolding system.
Preferably, the wing retraction system comprises: the wing body connecting shaft, the wing end connecting rod and the hydraulic actuator cylinder are arranged on the wing body; the connecting point of the hydraulic actuator cylinder and the middle machine body is arranged in the middle machine body, the hydraulic actuator cylinder is hinged with the wing end connecting rod, the wing end connecting rod is connected with the foldable wing, and the hydraulic actuator cylinder can extend out of the middle machine body to drive the wing end connecting rod to drive the foldable wing to be folded.
Preferably, the lower end of the joint of the wing and the fuselage is provided with an automatic buckle, and when the wing is completely unfolded, the automatic buckle locks the wing; when the wing needs to be folded, the flight control system controls the automatic buckle to be unlocked.
Preferably, the air cushion high lift system comprises an air inlet system, an air cushion and an air cushion exhaust rudder; when the air cushion needs to be inflated, the air inlet system fills air into the air cushion, the air exhaust is controlled through the air cushion exhaust rudder, the internal pressure of the air cushion is adjusted, and when the air cushion needs to be exhausted, the air inlet system is closed.
Preferably, the air inlet system comprises an air inlet channel, a fairing and an inflation tube, and the motor drives the pump to pump air into the inflation tube and the air cushion through the air inlet channel and the fairing.
Preferably, the unmanned aerial vehicle further comprises a front landing gear assembly and a main landing gear assembly, wherein the front landing gear assembly is arranged in the middle below the machine head and comprises a telescopic actuating cylinder which can be extended or shortened under the driving of a driving force and can rotate under the driving of a front lifting steering control assembly, so that the unmanned aerial vehicle can steer when sliding; the bottom end of the telescopic actuating cylinder is a sled; the main landing gear assembly is arranged between the fuel cabin and the equipment cabin and comprises two telescopic actuating cylinders which are arranged in bilateral symmetry, the two telescopic actuating cylinders can be extended or shortened under the driving action and can be driven to rotate inwards to realize braking, and the bottom ends of the two telescopic actuating cylinders are sleds.
Preferably, the unmanned aerial vehicle further comprises a front landing gear assembly and a main landing gear assembly, wherein the front landing gear assembly is arranged in the middle below the machine head and comprises a telescopic actuating cylinder which can be extended or shortened under the driving of a driving force and can rotate under the driving of a front lifting steering control assembly, so that the unmanned aerial vehicle can steer when sliding; the bottom end of the telescopic actuating cylinder is a sled; the main landing gear assembly is arranged between the fuel cabin and the equipment cabin and comprises two telescopic actuating cylinders which are arranged in bilateral symmetry, the two telescopic actuating cylinders can be extended or shortened under the driving action and can be driven to rotate inwards to realize braking, and the bottom ends of the two telescopic actuating cylinders are sleds.
Preferably, when the road condition on the snowfield is good and the snowfield is free from obstacles, the wings are controlled to retract, the air cushion high lift system is closed, the front landing gear assembly and the main landing gear assembly are released, and the sled slides forwards when touching the ground.
Preferably, when the road conditions on the snowy ground are poor and the flying is impossible, the control wings are retracted, the air cushion high lift system is opened, and the landing gear is retracted.
Preferably, when the snowfield road conditions are good and no hill, iceberg or water exists in the front of the snowfield road conditions, the wings are controlled to be opened, the air cushion high lift system is closed, the front landing gear assembly and the main landing gear assembly are released, and the snowfield land craft flies in the ground effect area after sliding and taking off by using the sledge.
Preferably, when the snowfield has better road conditions but the front of the snowfield is provided with a hill, an iceberg or water, the wings are controlled to be opened, the air cushion high lift system is closed, the front landing gear assembly and the main landing gear assembly are released, and the snowmobile flies outside the ground effect area after sliding and taking off.
Preferably, when the snowfield has poor road conditions and cannot fly, the control wing is opened, the air cushion high lift system is opened, the landing gear is retracted, and the aircraft flies in the ground effect area after sliding and taking off in an air cushion state.
Preferably, when the road condition on snowy ground is poor and a hill, an iceberg or water exists in the front of the snowy ground, the control wing is opened, the air cushion high lift system is opened, the undercarriage is retracted, and the aircraft flies outside the ground effect area after sliding and taking off in the air cushion state.
Preferably, an air conditioning system is integrated into the cargo compartment to control the temperature and humidity within the cargo compartment.
Meanwhile, an assembly method of the polar region multipurpose all-terrain unmanned transportation system is provided, and comprises the following steps:
1) connecting the front landing gear assembly with the framework of the middle machine body, and connecting the main steering brake steering engine with the framework to form a basic supporting platform;
2) after the motor, the pump, the air inlet system, the gas-filled tube, the left and right sealing plates of the air cushion, the air cushion exhaust rudder and the skirt edge are connected with each other, the air cushion exhaust rudder is connected with an installation interface of an air cushion high lift area at the lower part of the middle machine body;
3) the left and right sealing plates and the skirt edge of the air cushion are connected with a retraction device so as to control the retraction of the air cushion;
4) connecting a front lifting steering control assembly with a front landing gear assembly, and connecting a main lifting steering brake steering engine with a main landing gear assembly;
5) the engine is connected with the propeller, the engine is connected with the engine bracket, the engine and the engine bracket are provided with shock absorber kits, the nacelle is connected with the middle machine body, and the starting power supply is connected with the framework;
6) connecting the foldable wing with the middle body, and connecting the middle body with the tail wing;
7) respectively connecting the wing folding and unfolding system with the middle machine body and the foldable wings, so that the wings can be folded and operated;
8) connecting the communication system with the middle machine body and the equipment board in the equipment cabin;
9) connecting a flight control system, a task management system and an airplane state data acquisition system with an equipment board in an equipment cabin;
10) connecting the main oil tank and the oil pump with the frame of the machine body;
11) connecting the engine, the main oil tank and the oil pump together by using an oil pipe;
12) connecting the low-power engine and the generator with the framework;
13) and the low-power engine, the main oil tank and the oil pump are connected together by the oil pipe.
The disassembly method of the polar region multipurpose all-terrain unmanned transportation system comprises the following steps:
1) disconnecting oil pipes among the low-power engine, the main oil tank and the oil pump;
2) disconnecting the low-power engine and the generator from the framework of the middle engine body;
3) disconnecting oil pipes among the engine, the main oil tank and the oil pump;
4) disconnecting the main oil tank and the oil pump from the frame of the machine body;
5) dismounting the flight control system, the task management system and the airplane state data acquisition system from the equipment board in the equipment cabin;
6) disconnecting the communication system from the middle machine body and the equipment board in the equipment cabin;
7) the connection between the wing retraction system and the middle machine body and the connection between the wing retraction system and the foldable wing are disconnected;
8) disconnecting the foldable wing from the middle body, and disconnecting the middle body from the tail wing;
9) disconnecting the nacelle from the middle machine body, disconnecting the engine from the propeller, disconnecting the engine from the engine bracket, and disconnecting the starting power supply from the framework;
10) disconnecting the front lifting steering control assembly and the front landing gear assembly, and disconnecting the main lifting steering brake steering engine and the main landing gear assembly;
11) the left and right sealing plates and the skirt edge of the air cushion are disconnected with the retraction device;
12) after the motor, the pump, the air inlet system, the gas-filled tube, the left and right sealing plates of the air cushion, the air cushion exhaust rudder and the skirt edge are connected with each other, the air cushion exhaust rudder is disconnected with the mounting interface of the air cushion high lift region at the lower part of the middle machine body;
13) and disconnecting the front landing gear assembly and the framework and disconnecting the main landing gear steering engine and the framework.
When the road condition on the snowy ground is good and the snowy ground is free of obstacles, the wings are controlled to be retracted, the air cushion high-lift system is closed, the front landing gear assembly and the main landing gear assembly are released, and the sled slides forwards when touching the ground;
when the road conditions on the snowfield are poor and the snowfield cannot fly, the wings are controlled to retract, the air cushion high lift system is opened, and the landing gear retracts;
when the snowfield road conditions are good and no hills, icebergs or water exist in the front, the wings are controlled to be opened, the air cushion high lift system is closed, the front landing gear assembly and the main landing gear assembly are released, and the wings fly in the ground effect area after sliding and taking off by using sleds;
when the road conditions on snowfields are good, but hills, icebergs or water exist in the front of the snowfields, the wings are controlled to be opened, the air cushion high lift system is closed, the front landing gear assembly and the main landing gear assembly are released, and the snowmobiles fly out of the ground effect area after sliding and taking off;
when the snowfield road conditions are poor and the snowfield cannot fly, the wings are controlled to be opened, the air cushion high lift system is opened, the landing gear is retracted, and the snowfield flies in the ground effect area after sliding and taking off in the air cushion state;
when the road conditions on snowy ground are poor and hills, icebergs or water exist in the front of the snowy ground, the control wings are opened, the air cushion high lift system is opened, the landing gear is retracted, and the aircraft flies outside the ground effect area after sliding and taking off in the air cushion state.
Compared with the prior art, the invention has the following advantages:
(1) the environmental suitability is strong: due to the addition of the cushion lifting system and the fusion of the ground effect vehicle appearance, the polar region multipurpose all-terrain unmanned transportation system can freely switch operation modes (6 operation modes in total) according to different tasks, weather and road conditions and move in ice, soil, mud, water surface, ground effect area and free space;
(2) the reliability is high: the system is a unique fusion of the existing mature technology, the reliability is necessarily high, and the life safety of people is not endangered due to unmanned operation;
(3) all-weather: the equipment is unmanned, so that the function of 24-hour all-weather duty is achieved;
(4) the economy is good; the air conditioning system is arranged to ensure the temperature and humidity in the cargo compartment, so that the system can be applied to tasks such as supply transportation, medical rescue and the like, and has lower use and maintenance cost compared with special freight airplanes and rescue helicopters;
(5) the originality is high: the system has the comprehensive characteristics of sledges, hovercraft, ground effect aircrafts and airplanes, and has great polar adaptability and high originality;
(6) the trafficability characteristic is good: the wings of the invention can be folded and unfolded, and can adapt to narrower road conditions.
Drawings
FIG. 1 is an isometric view of a folded over skinned wing;
FIG. 2 is an isometric view of a belt skin structure;
FIG. 3 is an isometric view of a skinnless internal structure;
FIG. 4 is a side view of the belt skin;
FIG. 5 is a side view of an interior structure without a skin;
FIG. 6 is a bottom view of the air cushion region;
FIG. 7 is a schematic illustration of a main landing gear brake steering;
FIG. 8 is a schematic view of the folding and unfolding principle of the wings;
FIG. 9 is a schematic view of the landing gear retraction;
FIG. 10 is a schematic diagram of an integrated electrical system.
Detailed Description
The invention aims to design and invent an unmanned transportation vehicle which is safe, reliable, wide in application and strong in environmental adaptability.
(1) The utility model provides an all-terrain unmanned transportation system for polar region includes:
the system comprises a fuselage, a sled landing gear, an air cushion high lift system, a power propulsion system, an operation system, an Auxiliary Power Unit (APU), a fuel system, a task load and communication system, a monitoring and control system, a cargo hold, an air conditioning system and an electrical system.
The fuselage mainly includes: airspeed head 1, middle organism 2, collapsible wing 3, fin 7 and skeleton 16. The middle body 2 is a main body structure of the unmanned aerial vehicle and comprises a framework 16; airspeed tube 1 is located the front end of middle organism 2 for measure unmanned aerial vehicle forward speed.
Foldable wings 3 are provided on both sides of the middle body 2, and can be folded up and retracted, see fig. 1. With reference to fig. 8, the wing retraction system 37 of the foldable wing 3 comprises: the wing body connecting shaft, the wing end connecting rod and the hydraulic actuator cylinder are arranged on the wing body;
the foldable wing 3 is connected with the middle machine body 2 through a wing body connecting shaft, and the foldable wing 3 is turned upwards around the wing body connecting shaft; the connecting point of the hydraulic actuator cylinder and the middle machine body 2 is arranged inside the middle machine body 2 and can extend out of the middle machine body 2, the hydraulic actuator cylinder is hinged with a wing end connecting rod, and the wing end connecting rod is connected with the foldable wing 3 to drive the foldable wing 3 to be folded.
When the wing is folded, the hydraulic actuator cylinder stretches and stretches out of the middle machine body 2, the included angle between the wing end connecting rod and the hydraulic actuator cylinder is reduced according to the triangle principle, the connecting point 1 moves along the track 1, and the connecting point 2 moves clockwise along the track 2 until the wing reaches the position shown in the figure 1.
When the wing is unfolded, the hydraulic actuator cylinder stretches and retracts to be shortened, according to the triangle principle, the included angle between the wing end connecting rod and the hydraulic actuator cylinder is increased, the connecting point 1 moves along the track 1, the connecting point 2 moves anticlockwise along the track 2 until the wing reaches the position shown in the figure 2, and the lower end of the joint of the wing and the body is provided with an automatic buckle to improve the connecting strength.
The unmanned transportation system comprises six working modes, and the wings can be retracted and extended according to different working modes (so as to improve the trafficability of the airplane).
The ski landing gear mainly comprises: a nose landing gear assembly 13 and a main landing gear assembly 8.
The nose landing gear component 13 is arranged in the center below the nose, comprises a telescopic actuating cylinder connected to a framework 16, can be extended and shortened under the driving of a retractable steering engine, and can rotate under the driving of a front lifting steering control component 15, so that the unmanned aerial vehicle can steer when sliding; the bottom end of the telescopic actuating cylinder is a sled. Nose gear retraction and deployment see fig. 9.
The main landing gear assembly 8 is arranged between the fuel tank and the equipment tank 19, is symmetrically arranged at the left and right sides, comprises telescopic actuating cylinders connected to the framework 16, can be extended and shortened under the driving of a retractable steering engine, and can rotate under the driving of a main lifting steering brake steering engine 35 to realize braking; the bottom end of the telescopic actuator cylinder is a sled 41. Main landing gear retraction and deployment see fig. 9.
The air cushion high lift system mainly comprises: motor 33, pump 32, cowling 30 and inlet 31, gas tube 34, air cushion 14, air cushion exhaust rudder 9 and skirt 12. The air cushion 14 is arranged at the bottom of the middle machine body 2, a pump 32 is driven by a motor 33, air is pumped into the inflation pipe 34 and the air cushion 14 through the air inlet channel 31 and the fairing 30, when the air cushion 14 meets the requirement, the air cushion is lifted, the main landing gear component 8 and the nose landing gear component 13 are retracted, air exhaust is controlled through an air cushion exhaust rudder 9, and the internal pressure of the air cushion 14 is adjusted. The skirt 12 is disposed at the front end of the air cushion 14 for restricting the air flow. When air cushion 14 needs to be deflated, main landing gear assembly 8 and nose landing gear assembly 13 are lowered and motor 33 is turned off.
The power propulsion system mainly comprises: an engine 5, a propeller 6, an engine mount 22, an engine nacelle 4, and a starting power supply 23. The engine 5 is used for providing forward power of the whole unmanned aerial vehicle; the engine mount 22 is used to mount the engine 5 to the drone body; the engine nacelle 4 is mainly used for protecting the engine, rectifying and dissipating heat; the starting power supply 23 is used for starting the engine 5.
The operating system mainly comprises: a front-start steering assembly 15 and a main-start steering brake steering engine 35. The kick-off steering assembly 15 is used to control the heading of the drone in ski mode; the main steering brake steering engine 35 is used for controlling the brake of the unmanned aerial vehicle in the sled mode, controlling the two main landing gear assemblies 8 to deflect inwards, increasing the advancing resistance and realizing the brake.
The auxiliary power system (APU) mainly includes: a low power engine 25 and a generator 24. The low-power engine 25 is used for driving the generator 24 to generate electricity to supply power to the whole system.
The fuel system mainly includes: a fuel tank 36 disposed within the fuel compartment.
Within the equipment bay 19, a mission load and communication system and a monitoring and control system are integrated to effect communication and control of the aircraft.
The task load and communication system mainly comprises: line-of-sight communication system 26, antenna 28 and antenna 29 and satellite communication system 27. The line-of-sight communication system 26 communicates with the ground through an antenna 28; the satellite communication system 27 communicates with the ground via an antenna 29.
The monitoring and control system mainly comprises: flight control system 40, mission management system 39, and aircraft state data acquisition system 38. The flight control system 40 is used for controlling the air route of the unmanned aerial vehicle; the task management system 39 is used for flight task management and route planning; the aircraft status data acquisition system 38 is used to monitor the operating status of the drone system.
The electrical system mainly comprises: a power management system and a cable.
(2) The main assembly process related by the invention is as follows:
1) connecting the nose landing gear assembly 13 with the framework 16, and connecting the main lifting steering brake steering engine 35 with the framework 16 to form a basic supporting platform;
2) after the motor 33, the pump 32, the air inlet systems 30 and 31, the inflation pipes 34 and 14, the air cushion left and right sealing plates 10, the air cushion exhaust rudder 9 and the skirt 12 are connected with each other, the air cushion high lift area at the lower part of the middle fuselage is connected with a mounting interface;
3) the air cushion left and right sealing plates 10 and the skirt 12 are connected with a retraction device to control the retraction of the air cushion.
4) Connecting the nose-up steering control assembly 15 with the nose landing gear assembly 13, and connecting the main-up steering brake steering gear 35 with the main landing gear assembly 8
5) The engine 5 is connected with the propeller 6, the engine 5 is connected with the engine bracket 22, the engine 5 and the engine bracket 22 are provided with shock absorber kits, the nacelle 4 is connected with the middle machine body 2, and the starting power supply 23 is connected with the framework 16;
6) connecting the foldable wing 3 with the middle body 2, and connecting the middle body 2 with the tail wing 7;
7) the wing retraction system 37 is respectively connected with the middle machine body 2 and the foldable wing 3, so that the wing can be folded and operated;
8) connecting the line-of-sight communication systems 26, 28 and 29 and the satellite communication system 27 with the intermediate machine body 2 and the equipment board in the equipment cabin 19;
9) connecting a flight control system 40, a task management system 39 and an airplane state data acquisition system 38 with an equipment board in an equipment cabin 19;
10) connecting the main oil tank 36 and the oil pump with the fuselage skeleton 16;
11) the engine 5, the main oil tank 36 and the oil pump are connected together by oil pipes;
12) connecting a low-power engine 25 and a generator 24 with the framework 16;
13) and the low-power engine 25, the main oil tank 36 and the oil pump are connected together by oil pipes.
The related disassembly process comprises the following steps:
1) disconnecting oil pipes among the low-power engine 25, the main oil tank 36 and the oil pump;
2) disconnecting the low power engine 25 and the generator 24 from the skeleton 16;
3) disconnecting oil pipes among the engine 5, the main oil tank 36 and the oil pump;
4) disconnecting the main oil tank 36 and the oil pump from the fuselage airframe 16;
5) detaching the flight control system 40, the task management system 39 and the airplane state data acquisition system 38 from the equipment board in the equipment cabin 19;
6) disconnecting the line-of-sight communication systems 26, 28 and 29 and the satellite communication system 27 from the intermediate fuselage 2 and the equipment boards in the equipment bay 19;
7) the connection between the wing retraction system 37 and the middle machine body 2 and the foldable wing 3 is disconnected;
8) the foldable wing 3 is disconnected with the middle machine body 2, and the middle machine body 2 is disconnected with the tail wing 7;
9) disconnecting the nacelle 4 from the middle machine body 2, disconnecting the engine 5 from the propeller 6, disconnecting the engine 5 from the engine bracket 22, and disconnecting the starting power supply 23 from the framework 16;
10) disconnecting the nose-up steering control assembly 15 from the nose landing gear assembly 13, and disconnecting the main nose-up steering brake steering engine 35 from the main landing gear assembly 8;
11) the air cushion left and right sealing plates 10 and the skirt 12 are disconnected with the retraction device;
12) after the motor 33, the pump 32, the air inlet systems 30-31, the inflation pipes 34 and 14, the air cushion left and right sealing plates 10, the air cushion exhaust rudder 9 and the skirt 12 are connected with each other, the air cushion high lift area at the lower part of the middle fuselage is disconnected with the installation interface;
13) disconnecting the nose landing gear assembly 13 from the framework 16 and disconnecting the main landing gear steering gear 35 from the framework 16.
(3) Description of functional modes
1) Sled, wing retraction and air cushion-free mode
When the road conditions on the snowfield are good, for example, the snowfield is free of obstacles, and the ski can slide, when the mode is used, the air cushion high-lift system is closed, the power propulsion system pushes the machine body to move forwards, the control system can control the front wheel ski to steer, the tail wing 7 can also assist in controlling the direction in a high-speed state, the main ski is controlled to steer and brake, and similarly to the ski deceleration principle, the main starting steering brake steering engine 35 controls the ski 41 to deflect inwards, and the attached figure 7 shows. The forward speed is lower in this mode due to wing retraction.
2) Wing stow + air cushion mode
When the road conditions on snowy ground are poor (such as the road conditions of soil, wetland, water and the like), the sled cannot be used for sliding, and the air cushion high lift system cannot fly, the undercarriage is folded, the power propulsion system pushes the machine body to move forwards, the air cushion high lift system separates the machine body from the ground, the working state of the air cushion is controlled by operating the air cushion exhaust tail vane 9, and the tail wing 7 is used for operating the forward moving direction.
3) Sled, wing deployment and ground effect modes
When the road condition on snowy ground is good and there is no hill, iceberg or water in front, the aircraft can take off by sliding with the sledge. The air cushion high lift system is folded, in order to increase the speed, the body is in a ground effect aircraft mode, and the flight direction is controlled by the ailerons of the wings 3, the ailerons of the tail wing 7 and the rudder of the tail wing 7. The ground effect mode flying height is 3-5 m.
4) Sled + wing deployment + free flight mode
When the road condition on snowfields is good, but hills, icebergs or water and the like exist in the front, the aircraft can take off by sliding through skis, the air cushion high lift system is retracted, the aircraft body flies in free space in a fixed wing aircraft mode without limiting the flying height, and the flying direction is controlled by the ailerons of the wings 3 and the ailerons of the tail wing 7 and the rudder of the tail wing 7.
5) Air cushion, wing unfolding and ground effect modes
When the road conditions of snowy ground are not good (for example, the road conditions of soil, wetland, water and the like are met), the sled can not be used for sliding, and no hill or iceberg exists in the front of the snowy ground, the air cushion high lift system is opened, the airframe is in an air cushion and ground effect vehicle mode, and the flight direction is controlled by the ailerons of the wings 3, the ailerons of the tail wing 7 and the rudder of the tail wing 7.
6) Air cushion, wing expansion and free flight mode
When the road conditions of snowy ground are not good (for example, the road conditions of soil, wetland, water and the like are met), the sled can not be used for sliding, and the front of the snowy ground is provided with a hill, an iceberg or water and the like, the air cushion high lift system is released, the aircraft body flies in free space in a fixed wing aircraft mode, and the flight direction is controlled by the ailerons of the wings 3, the ailerons of the tail wing 7 and the rudder of the tail wing 7.
The cargo holds 16 and 18 integrate air conditioning systems to allow for the transport of cargo, replenishment, and medical assistance in complex polar environments.
(4) Description of the composition of an Integrated Electrical System
An integrated electrical system, comprising: the system comprises the APU, an onboard power supply, a power management system, onboard equipment, a motor and the like. The basic composition principle is shown in fig. 10.
The following functions can be realized:
1) the APU generates electricity to charge a starting power supply, an emergency power supply and an airborne power supply;
2) the APU supplies power to the airborne equipment and the motor through central power distribution;
3) the emergency battery can directly supply power to the airborne equipment in an emergency state;
4) the airborne battery can directly supply power to the airborne equipment;
5) the power management system freely switches the power supply mode according to the technical state of the aircraft and monitors the health state of the whole power system.
The invention realizes the following functions:
1) the ski and air cushion mode can be used on ice or snow to work in contact with the ground;
2) can fly close to the ground in the ground effect area;
3) the device can operate on the water surface in a ground effect state or an air cushion state;
4) the aircraft has the performance of a fixed wing aircraft and can fly in free space;
5) can be used for transporting goods or supplying;
6) medical rescue tasks can be performed in the polar region;
basic properties:
the system envelope size is 10.6mm × 7.6m × 3.3 m.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (12)
1. An all-terrain unmanned transportation system for multiple uses in polar regions, comprising: the fuselage comprises a middle body (2) and a foldable wing (3);
the foldable wings (3) are arranged on two sides of the middle machine body (2) and can be folded upwards and retracted under the driving of a wing folding and unfolding system (37);
a wing retraction system (37) comprising: the wing body connecting shaft, the wing end connecting rod and the hydraulic actuator cylinder are arranged on the wing body; the connecting point of the hydraulic actuator cylinder and the middle machine body (2) is arranged inside the middle machine body (2), the hydraulic actuator cylinder is hinged with a wing end connecting rod, the wing end connecting rod is connected to the foldable wing (3), and the hydraulic actuator cylinder can extend out of the middle machine body (2) to drive the wing end connecting rod to drive the foldable wing (3) to be folded;
the air cushion high lift system comprises an air inlet system, an air cushion (14) and an air cushion exhaust rudder (9); when inflation is needed, the air inlet system fills air into the air cushion (14), exhaust is controlled through the air cushion exhaust rudder (9), the internal pressure of the air cushion (14) is adjusted, and when the air cushion (14) needs to exhaust, the air inlet system is closed.
2. The polar region multipurpose all-terrain unmanned transportation system of claim 1, wherein the lower end of the joint of the wing and the fuselage is provided with an automatic buckle, and when the wing is completely unfolded, the automatic buckle locks the wing; when the wing needs to be folded, the flight control system (40) controls the automatic buckle unlocking.
3. A multi-purpose all-terrain unmanned conveyance system according to claim 1, wherein the air intake system comprises an air intake (31), a fairing (30) and an inflation tube (34), and wherein the pump (32) is driven by a motor (33) to pump air through the air intake (31) and fairing (30) into the inflation tube (34) and air cushion (14).
4. The multi-purpose all-terrain unmanned transportation system for polar regions according to claim 1 or 2, further comprising a nose landing gear assembly (13) and a main landing gear assembly (8), wherein the nose landing gear assembly (13) is arranged in the middle below the nose, comprises telescopic rams, can be extended or shortened under driving, and can be rotated under driving of a nose steering assembly (15), so that the unmanned aerial vehicle can steer when sliding; the bottom end of the telescopic actuating cylinder is a sled; the main landing gear component (8) is arranged between the fuel tank and the equipment tank (19) and comprises two telescopic actuating cylinders which are arranged in bilateral symmetry, the two telescopic actuating cylinders can be driven to extend or contract and can be driven to rotate inwards to realize braking, and the bottom ends of the two telescopic actuating cylinders are sleds (41).
5. The multi-purpose all-terrain unmanned transportation system of claim 4, further comprising a nose landing gear assembly (13) and a main landing gear assembly (8), wherein the nose landing gear assembly (13) is arranged in the middle below the nose, comprises telescopic rams, can be driven to extend or shorten, and can be driven to rotate by a nose steering assembly (15), so that the unmanned aerial vehicle can steer when sliding; the bottom end of the telescopic actuating cylinder is a sled; the main landing gear component (8) is arranged between the fuel tank and the equipment tank (19) and comprises two telescopic actuating cylinders which are arranged in bilateral symmetry, the two telescopic actuating cylinders can be driven to extend or contract and can be driven to rotate inwards to realize braking, and the bottom ends of the two telescopic actuating cylinders are sleds (41).
6. A multi-purpose all-terrain unmanned transportation system according to claim 5, wherein when snowy road conditions are good and snowy ground is clear, wings are controlled to retract, the air cushion high lift system is turned off, the front landing gear assembly (13) and the main landing gear assembly (8) are released, and the sled slides forward while touching the ground.
7. The polar region multipurpose all-terrain unmanned transportation system of claim 5, wherein when road conditions are poor on snowy ground but flight is unavailable, the wings are controlled to retract, the air cushion high lift system is opened, and the landing gear retracts.
8. A multi-purpose all-terrain unmanned transportation system for polar regions according to claim 5, wherein when snowy road conditions are good and there is no hill, iceberg or water in front, the wings are controlled to open, the air cushion high lift system is closed, the nose landing gear assembly (13) and the main landing gear assembly (8) are released and fly in the ground effect area after ski lift.
9. A multi-purpose all-terrain unmanned transportation system for polar regions according to claim 5, wherein when snowy ground conditions are good but there are hills, icebergs or water in front of them, the wings are controlled to open, the air cushion high lift system is closed, the nose landing gear assembly (13) and the main landing gear assembly (8) are released and fly out of the ground effect area after sliding with skis.
10. The polar region multipurpose all-terrain unmanned transportation system of claim 5, wherein when the system is in poor road conditions on snowy ground but cannot fly, the control wings are opened, the air cushion high lift system is opened, the landing gear is retracted, and after the system is in an air cushion state and takes off, the system flies in a ground effect area.
11. The polar region multipurpose all-terrain unmanned transportation system of claim 5, wherein when road conditions are poor on snowy ground and a hill, an iceberg or water is in front of the system, the wings are controlled to be opened, the air cushion high lift system is opened, the landing gear is retracted, and the system flies outside a ground effect area after sliding under the air cushion state to take off.
12. The polar multipurpose all-terrain unmanned transportation system of claim 1, wherein an air conditioning system is integrated into the cargo space to control the temperature and humidity within the cargo space.
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| CN201810272813.4A CN108438201B (en) | 2018-03-29 | 2018-03-29 | Polar region multipurpose all-terrain unmanned transportation system |
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| CN201810272813.4A CN108438201B (en) | 2018-03-29 | 2018-03-29 | Polar region multipurpose all-terrain unmanned transportation system |
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| IL265840A (en) * | 2019-04-03 | 2020-10-28 | Colugo Systems Ltd | Asymmetric multirotor |
| CN112706579A (en) * | 2020-09-10 | 2021-04-27 | 徐州品上空调科技有限公司 | Electric air conditioning device for engineering machinery |
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