Multi-medium unmanned aerial vehicle configuration

Abstract

The invention belongs to the technical field of aviation, and relates to a multi-medium unmanned aerial vehicle configuration. The whole body adopts a truss type structure, a fuselage skin and a nose skin are watertight, a front section and an equivalent section are in smooth transition, and the slenderness ratio is 1.3; the shape of the tail section is in smooth transition with the equivalent section to form an upwarp tail section; first-order and second-order derivatives of the fuselage shape are continuous; the wings adopt a middle single wing layout, the empennage adopts a V-shaped vertical tail form, and the wings and the empennage are telescopic; a front three-point retractable landing gear form is adopted, and front wheels and main wheels are folded forwards; two task cabins are designed on the belly of the unmanned aerial vehicle, the two task cabins are both designed on an equivalent section, the two task cabins are both in a single-plate side-sliding mode, when the cabin is opened, the cabin is firstly moved downwards and then slides towards one side to be opened, and when the cabin is closed, the actions are opposite; a power system engine is arranged at the tail of the multi-medium unmanned aerial vehicle, and when the multi-medium unmanned aerial vehicle needs to sail on the water surface and in water, before the multi-medium unmanned aerial vehicle enters the water, engine blades are retracted backwards along the heading direction, and the rotating speed is reduced.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and relates to a multimedia unmanned machine configuration. Background Art

[0002] With the rapid development of drones, the mission areas involved by drones can gradually cover all the mission areas of manned aircraft. The role of drones is mainly to replace manned aircraft to complete various dangerous tasks and complete tasks that manned aircraft cannot complete. Faced with the huge differences in the physical properties of different media, the aircraft needs to break through a series of difficult problems such as cross-media stability control technology, multi-sensor data fusion technology, and structural deformation integration technology. It is necessary to carry out basic theoretical research and key technology research across disciplines and fields. Summary of the invention

[0003] Purpose of the invention: To provide a multimedia unmanned machine model.

[0004] Technical solution:

[0005] A multi-media unmanned aircraft configuration, which adopts a truss structure as a whole, with a fuselage skin 1 and a nose skin 2 being watertight, a smooth transition between the front section and the equivalent section, and a slenderness ratio of 1.3; a smooth transition between the tail section and the equivalent section to form an upturned tail section; the first-order and second-order derivatives of the fuselage shape are continuous;

[0006] The wing adopts a mid-wing layout, the tail adopts a V-shaped vertical tail form, and the wings and tail are retractable; it adopts a three-point retractable landing gear form, and the front wheels and main wheels are both retracted forward. The belly of the UAV is designed with two mission cabins, and the two mission cabins are designed in the equivalent section. The two mission cabin doors are both single-board side-sliding. When opening, they first move downward and then slide to one side to open the cabin door. When closing, the action is opposite to ensure watertight requirements; the power system engine 7 is arranged at the tail of the multimedia UAV. When the multimedia UAV needs to navigate on the water surface and in the water, before entering the water, the engine blades are retracted backward along the heading and the rotation speed is reduced.

[0007] Furthermore, the engine power source adopts electric power or nuclear power drive mode.

[0008] Furthermore, the slenderness ratio between the front section and the equal value section is 1.3.

[0009] Furthermore, the slenderness ratio of the tail section shape to the equivalent section is 2.5.

[0010] Furthermore, the fuselage structure includes a plurality of common frames, two front landing gear reinforcement frames 9, two wing and main landing gear reinforcement frames 10, a plurality of right-angle common long spars and groove-type reinforcement long spars. The common frame is an integral machined part, and the material is an aluminum pre-stretched plate, and the overall shape is similar to an "I" shape; the front landing gear reinforcement frame 9 is made of an aluminum pre-stretched plate, and the overall shape is similar to an "I" shape; the wing and main landing gear reinforcement frame 10 is made of an aluminum pre-stretched plate, and the overall shape is similar to an "I" shape.

[0011] Furthermore, the skin material is LY12-M-δ2.

[0012] Furthermore, the wing is a shape memory alloy deformable wing 5, and the tail is a shape memory alloy deformable vertical tail 6. By controlling the phase transition temperature of the shape memory alloy material, the shape of the shape memory alloy material is changed to achieve use or control.

[0013] Furthermore, the landing gear doors are all of single-plate side-sliding type. When opening, they first move downward and then slide to one side to open the door. When closing, the action is opposite to ensure watertight requirements.

[0014] Beneficial effects:

[0015] The present invention provides a multi-media unmanned aircraft configuration. By designing a UAV structure into a deformable and intelligent structure and using advanced energy storage electricity or nuclear power as the power source of the UAV, the UAV can adapt to navigation in multi-media. The present invention overcomes the limitation of a single medium and a single aircraft, solves the problem of a single UAV and a single power source, and realizes a complex complex that integrates a land vehicle, a surface or underwater aircraft, and an air vehicle, meeting the use requirements of multi-media adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A side view of a multimedia UAV aerial flight arrangement;

[0017] Figure 2 Arrange a top view of a multimedia drone flying in the air;

[0018] Figure 3 Arrange a front view of a multimedia drone flying in the air;

[0019] Figure 4 A schematic diagram of a multimedia UAV sailing in water;

[0020] Figure 5 Schematic diagram of frame distribution;

[0021] Figure 6 This is a schematic diagram of the distribution of long girders;

[0022] Figure 7 A schematic diagram of a single-wing connection in a multimedia UAV;

[0023] Figure 8 It is a schematic diagram of the telescopic structure of the wing intelligence;

[0024] Fig. 9 This is a schematic diagram of the fuselage watertight line;

[0025] Fig.10 This is a schematic diagram of the mission module door activity.

[0026] Among them: 1. Fuselage skin; 2. Nose skin; 3. Front landing gear; 4. Main landing gear; 5. Memory alloy deformable wing; 6. Memory alloy deformable vertical tail; 7. Engine; 8. Ordinary frame (22 pieces in total); 9. Front landing gear reinforcement frame (2 frames); 10. Wing and main landing gear reinforcement frame (2 frames); 11. Grooved reinforced long stringer (4 pieces in total); 12. Right-angled ordinary long stringer (16 pieces in total); 13. Large mission system cabin; 14. Large movable cabin door; 15. Small mission system cabin; 16. Small movable cabin door. DETAILED DESCRIPTION

[0027] The present application provides a multi-media unmanned aircraft configuration. By designing a UAV structure into a deformable and intelligent structure and using advanced energy storage electricity or nuclear power as the power source of the UAV, the UAV can adapt to the multi-media navigation of flying in the air, maneuvering on land, and sailing on the surface or in water. The present invention overcomes the limitations of a single medium and a single aircraft, solves the problem of a single UAV and a single power source, and realizes a complex complex that integrates a land vehicle, a surface or underwater vehicle, and an air vehicle, meeting the use requirements of multi-media adaptability.

[0028] like Figures 1 to 4 As shown, a multimedia motion unmanned aircraft configuration is provided, which mainly includes: fuselage skin 1, nose skin 2, front landing gear 3, main landing gear 4, memory alloy deformable wing 5, memory alloy deformable vertical tail 6, engine 7, common frame (22 pieces in total) 8, front landing gear reinforcement frame (2 frames) 9, wing and main landing gear reinforcement frame (2 frames) 10, groove-type reinforced long stringer (4 pieces in total) 11, right-angle common long stringer (16 pieces in total) 12, large mission system cabin 13, large movable cabin door 14, small mission system cabin 15, and small movable cabin door 16.

[0029] Overall design. It mainly includes fuselage design, wing design, tail design, landing gear layout, engine tail layout, etc. It is necessary to consider the aerodynamic / fluid performance of the whole aircraft in various states of multi-media, weight control, navigation control, environmental adaptability and other aspects. The whole aircraft is watertight, the structure can withstand the pressure of the fluid, and the appearance is simple and smooth. The front section and the equivalent section have a smooth transition, and the slenderness ratio is 1.3. The tail section shape and the equivalent section have a smooth transition, and the slenderness ratio is 2.5, forming an upturned tail section. The first and second order derivatives of the shape are continuous, the shape is smooth, the resistance is small, and the requirements of the aircraft's ground rubbing angle are met. The wing adopts a mid-wing layout, the tail adopts a V-shaped vertical tail form, and the wing and tail adopt an intelligent structural design, which is designed to be intelligent and retractable. The UAV adopts a front three-point retractable landing gear form, and the front wheels and main wheels are both retracted forward. The retractable landing gear and landing gear compartment are designed. The engine meets the requirements of multi-media use and power. A multi-media unmanned aircraft type, which is suitable for air flight, land maneuvering, and surface or underwater navigation. Figures 1 to 3 , see the navigation status in water Figure 4 The maximum dimensions of a multimedia unmanned aircraft are a×c×d mm (length×width×height), and the fuselage equivalent section size is φb mm. The wing root chord length is about q mm, and the wing tip chord length is about w mm. Figure 8 .Depend on Figure 4 It is known that the wings and tail of the underwater navigation adopt an intelligent structural design, and the overall dimensions are changed to e×f mm (width×height), reducing the navigation resistance.

[0030] Structural design. The structure mainly includes fuselage skin 1, nose skin 2, front landing gear 3, main landing gear 4, memory alloy deformable wing 5, memory alloy deformable vertical tail 6, ordinary frame (22 pieces in total) 8, front landing gear reinforcement frame (2 frames) 9, wing and main landing gear reinforcement frame (2 frames) 10, groove-type reinforced long stringer (4 pieces in total) 11, right-angle ordinary long stringer (16 pieces in total) 12, large mission system cabin 13, large movable cabin door 14, small mission system cabin 15, small movable cabin door 16 and other components. A multimedia UAV structure adopts a truss type. The whole machine has a total of 22 ordinary frames 8. The ordinary frame is an integral machined part. The material is aluminum pre-stretched plate. The overall shape is similar to the "I" shape. The whole machine has a total of 2 front landing gear reinforcement frames 9. The material is aluminum pre-stretched plate. The overall shape is similar to the "I" shape. It is used for the front landing gear to bear and transmit force. See Figure 5 The whole aircraft has two wings and a main landing gear reinforcement frame 10, which is made of aluminum pre-stretched plate and has an overall shape similar to an "I" shape. It is used for bearing and transmitting force between the wings and the main landing gear. Figure 7 . The frame positioning accuracy is ensured by the tooling.

[0031] The whole machine has 16 right-angle common long stringers 12, evenly distributed, made of LY12-CZ-XC141-12 standard profile. The whole machine has 4 groove reinforced long stringers 11, evenly distributed at 90 degrees, made of LY12-CZ-XC341-6 standard profile, see Figure 6 The long stringer should be a whole piece as much as possible, with fewer sections to ensure direct and continuous force transmission. The positioning accuracy of the long stringer should be ensured by the tooling.

[0032] The whole aircraft has two skins, fuselage skin 1 and nose skin 2. The skin is the main watertight component of the whole aircraft and is butted at frame 1. The material is LY12-M-δ2, with special anti-corrosion surface treatment. In order to design the whole aircraft watertight, the fuselage skin 1 and the nose skin 2 minimize the opening and splitting operations, and the two skins are overlapped and watertight on the lower surface of the drone; the fuselage skin 1 and the nose skin 2 are cut at one time and formed as a whole. The positioning accuracy of the skin is guaranteed by the tooling.

[0033] The memory alloy deformable wing 5 and the memory alloy deformable vertical tail 6 adopt a memory alloy intelligent deformation structure. Shape memory alloy has a shape memory recovery function and has the characteristics of being non-magnetic, wear-resistant, and corrosion-resistant. It enables a multimedia UAV to maintain normal wing and vertical tail shapes when flying in the air; when it needs to sail on the water surface and in the water, the wings and vertical tail are folded to form a form similar to a fairing, ensuring that the appearance of the UAV is relatively smooth and has less resistance, just like the wings of a bird, which can be retracted freely, so that it can soar in the sky and forage in the water. Its working principle is to control the phase change temperature of its shape memory alloy material to change its shape to achieve functions such as use or control. It utilizes the physical properties of the material itself, see Figure 4 .

[0034] The front landing gear 3 and the main landing gear 4 of the multimedia UAV adopt the conventional front three-point retractable landing gear form, and the front wheels and the main wheels are both retracted forward. The landing gear doors are all single-board side-sliding type. When opening, they first move downward and then slide to one side to open the door. When closing, the action is opposite to ensure watertight requirements.

[0035] The design includes a large mission system cabin 13, a large movable cabin door 14, a small mission system cabin 15, and a small movable cabin door 16. The belly of the drone is designed with two mission cabins that can carry different mission systems.

[0036] The first mission module is between frame 7 and frame 13, with dimensions of j×g×hmm (length×width×height).

[0037] The second mission module is between frame 19 and frame 21, with dimensions of k×g×hmm (length×width×height). Figure 5 , Fig. 9The two mission cabins are designed in the equivalent section. Both mission cabin doors are single-board side-sliding. When opening, they first move downward and then slide to one side to open the cabin door. When closing, the action is opposite to ensure watertight requirements. Fig.10 .

[0038] The power system engine 7 is arranged at the tail of the multimedia drone (1 engine), and the engine power source adopts electric power or nuclear power drive mode. At the same time, it can provide power source for the control system, landing gear and other devices to meet the use requirements of the drone. When the multimedia drone needs to navigate on the water surface and in the water, before entering the water, the engine blades are retracted backward along the course and the rotation speed is reduced. Figure 4 .

[0039] Control system design. Design a multi-modal control system that adapts to flight / deformation transition / navigation, complete automatic control in different modes and automatic and accurate switching between different modes, solve complex navigation control when crossing media, and ensure high-precision flight trajectory control. Using autonomous and artificial intelligence control technology, you only need to input the specific tasks to be completed for the multi-media drone, and use advanced high-speed computer algorithms to simulate the functions of the human brain for autonomous intelligent control. There is no need to give complex instructions to control what the drone does.

[0040] The integrated avionics system of the multi-media UAV ensures the relay and data communication between air / air, air / ground, and air / sea (underwater), and completes autonomous navigation, landing, formation assembly, coordinated combat between UAVs and between UAVs and manned aircraft; information identification and friend-or-foe identification, etc. Multi-media UAVs need to adopt the form of strapdown inertial navigation system and geophysical field navigation combined navigation to meet the navigation requirements of cross-media sea and air vehicles in the air, on the surface, and under the surface. The two navigation systems are paralleled and integrated together, and different media are switched to ensure the navigation requirements of multi-media UAVs.

[0041] The mission system adopts universal, standardized, modular and integrated design, with rapid loading and unloading, and implements multi-functional mission requirements.

[0042] The multi-media unmanned machine type of the present invention has a reasonable overall layout, a multi-path force transmission structure and is relatively light in weight.

Claims

1. A multimedia unmanned machine configuration, characterized in that: The whole adopts a truss structure, the fuselage skin (1) and the nose skin (2) are watertight, the front section and the equivalent section have a smooth transition, and the slenderness ratio is 1.3; the tail section shape and the equivalent section have a smooth transition to form an upturned tail section; the first-order and second-order derivatives of the fuselage shape are continuous; The wing adopts a mid-wing layout, the tail adopts a V-shaped vertical tail form, and the wing and tail are retractable; The front three-point retractable landing gear is adopted, and the front wheels and main wheels are both retracted forward; the belly of the UAV is designed with two mission cabins, both of which are designed in the equivalent section, and both mission cabin doors are single-board side-sliding. When opening, they first move downward and then slide to one side to open the cabin door. When closing, the action is opposite to ensure watertight requirements; The power system engine (7) is arranged at the tail of the multimedia unmanned aerial vehicle. When the multimedia unmanned aerial vehicle needs to navigate on the water surface or in the water, before entering the water, the engine blades are retracted backward along the course and the rotation speed is reduced.

2. The multimedia unmanned machine configuration according to claim 1, characterized in that: The engine power source adopts electric power or nuclear power drive mode.

3. The multimedia unmanned machine configuration according to claim 1, characterized in that: The slenderness ratio of the front section to the equal section is 1.

3.

4. The multimedia unmanned machine configuration according to claim 1, characterized in that: The slenderness ratio of the tail section shape to the equivalent section is 2.

5.

5. The multimedia unmanned machine configuration according to claim 1, characterized in that: The fuselage structure comprises a plurality of common frames, two front landing gear reinforcement frames (9), two wing and main landing gear reinforcement frames (10), a plurality of right-angle common long girders and groove-shaped reinforcement long girders. The common frames are integral machined parts, made of aluminum pre-stretched plates, and have an overall shape similar to an "I" character. The front landing gear reinforcement frame (9) is made of aluminum pre-stretched plates, and has an overall shape similar to an "I" character. The wing and main landing gear reinforcement frames (10) are made of aluminum pre-stretched plates, and have an overall shape similar to an "I" character.

6. The multimedia unmanned machine configuration according to claim 1, characterized in that: The skin material is LY12-M-δ2.

7. The multimedia unmanned machine configuration according to claim 1, characterized in that: The wings are memory alloy deformable wings (5), and the tail is memory alloy deformable vertical tail (6). By controlling the phase change temperature of the shape memory alloy material, the shape of the shape memory alloy material is changed to achieve use or control.

8. The multimedia unmanned machine configuration according to claim 1, characterized in that: The landing gear doors are all of single-plate side-sliding type. When opening, they first move downward and then slide to one side to open the door. When closing, the action is opposite to ensure watertight requirements.

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