Unmanned aerial vehicle aerodynamic layout structure suitable for intensive mounting of combat aircrafts

Abstract

The invention belongs to the technical field of aircraft overall aerodynamic layout design, and particularly relates to an unmanned aerial vehicle aerodynamic layout structure suitable for intensive mounting of combat aircrafts, which comprises a fuselage, wings, a horizontal tail, a vertical tail, a first power device and a second power device, the two sets of wings are arranged on the two sides of the fuselage, the horizontal empennages are arranged on the two sides of the fuselage, the vertical empennages are arranged at the tail of the fuselage, the first power device is arranged at the top of the fuselage, and the second power device is arranged at the tail of the fuselage. The first power device is connected with the wings and the horizontal empennage and can provide force arms for the wings and the horizontal empennage; the second power device is connected with the vertical empennage and can provide a force arm for the vertical empennage; the wings, the horizontal empennage and the vertical empennage are all foldable wings and form two modes, and the two modes comprise a flight mode and a mounting mode. The unmanned aerial vehicle group can be mounted on the combat aircraft through a small space, a small number of hangers and small resistance.

Description

Technical Field

[0001] The present application belongs to the technical field of overall aerodynamic layout design of aircraft, and in particular relates to an aerodynamic layout structure of an unmanned aerial vehicle suitable for dense mounting on combat aircraft. Background Art

[0002] Drones play an important role in modern warfare. On the one hand, drones have the characteristics of fast flight speed, long flight distance and low cost. On the other hand, drones have the ability to perform tasks such as battlefield monitoring, target strike and communication relay.

[0003] Drones can start flight missions in a variety of ways, including ground takeoff, ship-borne takeoff, air launch, etc. Air-launched drones can shorten the flight distance of drones, which can reduce the flight weight of drones and reduce the manufacturing cost of drones. Air-launched drones are an ideal combat platform for long-range combat targets.

[0004] Drones have developed a relatively mature swarm combat mode, that is, a certain number of drones autonomously form a team, which can effectively deal with concentrated and dispersed combat targets. Therefore, for air-launched drones, it is necessary to have the ability to mount densely, that is, the carrier can mount multiple drones at a time, which can greatly improve the drone's continuous and flexible combat capability in the target area.

[0005] For combat aircraft, the usual way to carry air-launched devices is to mount them under the wings, and it is difficult to achieve the requirement of densely mounting drones. On the one hand, the size of the wing is limited, making it difficult to mount multiple drones; on the other hand, the wing has limited external attachment points, and if all drones are mounted, other equipment cannot be mounted; finally, external attachments will increase the aircraft's resistance and affect the aircraft's flight performance.

[0006] Comprehensive analysis shows that the existing UAV designs based on combat aircraft launch are inconsistent in design. In order to realize the UAV swarm combat mode, the aircraft needs to carry multiple UAVs at a time; carrying multiple UAVs on the aircraft will lead to insufficient space, insufficient hanging points and excessive resistance. In order to improve the comprehensive combat capability of air-launched UAVs, the overall size of the UAV swarm needs to be reduced. Therefore, under the constraints of various design conditions, reducing the mounting size of the UAV swarm is one of the key requirements; reducing the number of hanging points of the UAV swarm is one of the key requirements; reducing the drag increment of the UAV swarm is one of the key requirements. Summary of the invention

[0007] The purpose of this application is to provide an aerodynamic layout structure of UAVs suitable for dense mounting on combat aircraft, so as to solve the problems of insufficient space, insufficient mounting points and excessive resistance of UAV clusters in the prior art.

[0008] The technical solution of the present application is: an aerodynamic layout structure of a UAV suitable for dense mounting on combat aircraft, comprising a fuselage, wings, a horizontal tail, a vertical tail, a first power device and a second power device; the wings have two sets and are arranged on both sides of the fuselage, the horizontal tail is arranged on both sides of the fuselage, the vertical tail is arranged at the tail of the fuselage, the first power device is arranged on the top of the fuselage, and the second power device is arranged at the tail of the fuselage; the first power device is connected to the wings and the horizontal tail, and can provide a force arm to the wings and the horizontal tail; the second power device is connected to the vertical tail, and can provide a force arm to the vertical tail;

[0009] The wings, horizontal tail and vertical tail are all folding wings, forming two modes, namely flight mode and mounting mode; in mounting mode, the wings, horizontal tail and vertical tail are folded on the surface of the fuselage, and in flight mode, the wings, horizontal tail and vertical tail are unfolded on both sides of the fuselage.

[0010] Preferably, a first groove, a second groove and a third groove are respectively provided at positions corresponding to the wings, the horizontal tail and the vertical tail on the fuselage; the wings can swing in the first groove, the horizontal tail can swing in the second groove, and the vertical tail can swing in the third groove.

[0011] Preferably, the mounting mode includes a single-stage mounting mode and a dense mounting mode. The single-stage mounting mode is a single UAV mounting, and the dense mounting mode is a UAV group mounting.

[0012] Preferably, the drone swarm can be mounted under the aircraft rack in a longitudinal arrangement, and each rack can mount a drone swarm; the drone swarm is launched from back to front in sequence.

[0013] Preferably, a first connecting device is provided at the front end of the body, and a second connecting device is provided at the rear end, and the first connecting device on the body of one drone can be connected to the second connecting device on the body of another similar drone.

[0014] Preferably, engines are provided at both the middle and tail portions of the fuselage.

[0015] Preferably, the first connecting device and the second connecting device are connected by a snap-fit ​​structure.

[0016] Preferably, the body is a prism.

[0017] Preferably, the first power device and the second power device both include a motor and a connecting rod mechanism connected to the motor.

[0018] Preferably, a first air intake and exhaust system is provided at the middle portion of the fuselage, and a second air intake and exhaust system is provided at the tail portion of the fuselage of the UAV.

[0019] The present application is suitable for the aerodynamic layout structure of UAVs densely mounted on combat aircraft, and the UAV swarm can be mounted on combat aircraft with a smaller space, fewer hangers and less resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0021] Figure 1 This is an axonometric diagram of the single-aircraft flight mode for this application;

[0022] Figure 2 For this application, a single-machine flight mode perspective view;

[0023] Figure 3 This is a schematic diagram of the stand-alone mounting mode for this application;

[0024] Figure 4 This is a schematic diagram of the drone swarm mounting mode for this application.

[0025] 1. Fuselage; 2. Wings; 3. Horizontal tail; 4. Vertical tail; 5. First power unit; 6. Second power unit; 7. First connecting device; 8. Second connecting device; 9. First groove; 10. Second groove; 11. Third groove. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] An aerodynamic layout structure of a UAV suitable for densely mounted combat aircraft, such as Figure 1 , including a fuselage 1, wings 2, horizontal tail 3, vertical tail 4, a first power device 5 and a second power device 6. There are two sets of wings 2 and they are arranged on both sides of the fuselage 1, the horizontal tail 3 is arranged on both sides of the fuselage 1, the vertical tail 4 is arranged at the tail of the fuselage 1, the first power device 5 is arranged on the top of the fuselage 1, and the second power device 6 is arranged at the tail of the fuselage 1. The first power device 5 is connected to the wings 2 and the horizontal tail 3, and can provide a force arm to the wings 2 and the horizontal tail 3; the second power device 6 is connected to the vertical tail 4, and can provide a force arm to the vertical tail 4.

[0028] The wings 2, the horizontal tail 3 and the vertical tail 4 are all foldable wings 2, forming two modes, including a flight mode and a mounting mode. In the mounting mode, the wings 2, the horizontal tail 3 and the vertical tail 4 are folded on the surface of the fuselage 1, and in the flight mode, the wings 2, the horizontal tail 3 and the vertical tail 4 are unfolded on both sides of the fuselage 1.

[0029] In flight mode, it can provide the lift and operating torque required for the UAV to fly; in mounting mode, it can reduce the flight resistance of the aircraft.

[0030] Preferably, a first groove 9, a second groove 10 and a third groove 11 are respectively provided at positions corresponding to the wing 2, the horizontal tail 3 and the vertical tail 4 on the fuselage; the wing 2 can swing in the first groove 9, the horizontal tail 3 can swing in the second groove 10, and the vertical tail 4 can swing in the third groove 11, thereby realizing the folding and unfolding of the wing 2, the horizontal tail 3 and the vertical tail 4.

[0031] The mounting modes include single-stage mounting mode and dense mounting mode. The single-stage mounting mode is for mounting a single drone, and the dense mounting mode is for mounting a group of drones. Figure 1-Figure 2 , single-level mount mode such as Figure 3 , see dense mounting mode Figure 4 .

[0032] Among them, the folding method and folding position of the wing 2 are only for illustration. In addition to folding the wing 2 on the side of the fuselage 1, the design of folding the wing 2 on the top, bottom, front and back of the fuselage 1 is also applicable to this solution.

[0033] The folding method and folding position of the horizontal tail 3 are only for illustration. In addition to folding the horizontal tail 3 at the side of the fuselage 1, designs of folding the horizontal tail 3 on the top, bottom, front, and back of the fuselage 1 are also applicable to this solution.

[0034] The folding method and folding position of the vertical tail 4 are for illustration only. In addition to setting the vertical tail 4 at the tail of the fuselage 1, designs of folding the vertical tail 4 on the top, bottom, front, and side of the fuselage 1 are also applicable to this solution.

[0035] In addition to the design that the first power device 5 and the second power device 6 pass through the top of the fuselage 1 to the back of the fuselage 1, the design that passes through the front of the computer to the bottom of the fuselage 1 is also applicable to this solution.

[0036] Preferably, a first connecting device 7 is provided at the front end of the fuselage, and a second connecting device 8 is provided at the rear end. The first connecting device 7 on the fuselage of one drone can be connected to the second connecting device 8 on the fuselage of another similar drone, so that the fuselages 1 of different drones can be connected to each other and form a whole after being fitted front and back.

[0037] Preferably, engines are provided at the middle and tail of the UAV fuselage 1. The engines may be piston engines, turbojet engines, etc., to realize the flight of the UAV.

[0038] Preferably, the drone swarm can be mounted under the aircraft pylon in a longitudinal arrangement, and each pylon can mount a drone swarm. The drone swarm is launched from back to front. During launch, the first connecting device 7 and the second connecting device 8 between the pylon and the front drone are released, the drone gradually distances itself from the aircraft, and then the wings 2, the horizontal tail 3 and the vertical tail 4 are unfolded from the first groove 9, the second groove 10 and the third groove 11, the engine is ignited, and the single-machine launch process is completed. Other drones are launched in turn, thereby completing the transportation and launch of the drone swarm.

[0039] Preferably, the first connecting device 7 and the second connecting device 8 are connected by a snap-fit ​​structure.

[0040] Preferably, the body 1 is a prism.

[0041] Preferably, the first power device 5 and the second power device 6 both include a motor and a connecting rod mechanism connected to the motor.

[0042] Preferably, a first air intake and exhaust system is provided in the middle of the drone fuselage 1 , and a second air intake and exhaust system is provided at the tail of the drone fuselage 1 , so as to realize air supply and heat exchange inside the fuselage 1 .

[0043] Through the above design, drone swarms can be mounted on combat aircraft using a smaller space, fewer hangers and less resistance.

[0044] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0045] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aerodynamic layout structure of a UAV suitable for dense mounting of combat aircraft, characterized by: The invention comprises a fuselage (1), wings (2), a horizontal tail (3), a vertical tail (4), a first power device (5) and a second power device (6); the wings (2) have two groups and are arranged on both sides of the fuselage (1); the horizontal tail (3) is arranged on both sides of the fuselage (1); the vertical tail (4) is arranged at the tail of the fuselage (1); the first power device (5) is arranged at the top of the fuselage (1); and the second power device (6) is arranged at the tail of the fuselage (1); the first power device (5) is connected to the wings (2) and the horizontal tail (3) and can provide a force arm to the wings (2) and the horizontal tail (3); the second power device (6) is connected to the vertical tail (4) and can provide a force arm to the vertical tail (4); The wings (2), the horizontal tail (3) and the vertical tail (4) are all foldable wings (2), forming two modes, which include a flight mode and a mounting mode; in the mounting mode, the wings (2), the horizontal tail (3) and the vertical tail (4) are folded on the surface of the fuselage (1); in the flight mode, the wings (2), the horizontal tail (3) and the vertical tail (4) are unfolded on both sides of the fuselage (1).

2. The aerodynamic layout structure of the UAV suitable for dense mounting of combat aircraft according to claim 1, characterized in that: A first groove (9), a second groove (10) and a third groove (11) are respectively provided on the fuselage at positions corresponding to the wing (2), the horizontal tail (3) and the vertical tail (4); the wing (2) can swing in the first groove (9), the horizontal tail (3) can swing in the second groove (10), and the vertical tail (4) can swing in the third groove (11).

3. The aerodynamic layout structure of the unmanned aerial vehicle suitable for dense mounting on combat aircraft according to claim 1, characterized in that: The mounting modes include single-stage mounting mode and dense mounting mode. The single-stage mounting mode is for mounting a single UAV, and the dense mounting mode is for mounting a group of UAVs.

4. The aerodynamic layout structure of the UAV suitable for dense mounting of combat aircraft according to claim 3, characterized in that: The drone swarm can be mounted under the aircraft's racks in a vertical arrangement, and each rack can carry a drone swarm; the drone swarm is launched in sequence from back to front.

5. The aerodynamic layout structure of the UAV suitable for dense mounting of combat aircraft according to claim 1, characterized in that: A first connecting device (7) is provided at the front end of the body, and a second connecting device (8) is provided at the rear end. The first connecting device (7) on the body of one unmanned aerial vehicle can be connected to the second connecting device (8) on the body of another similar unmanned aerial vehicle.

6. The aerodynamic layout structure of the unmanned aerial vehicle suitable for dense mounting on combat aircraft according to claim 5, characterized in that: The middle part and the tail part of the fuselage (1) are both provided with engines.

7. The aerodynamic layout structure of the unmanned aerial vehicle suitable for dense mounting on combat aircraft according to claim 5, characterized in that: The first connecting device (7) and the second connecting device (8) are connected by a snap-fit ​​structure.

8. The aerodynamic layout structure of the unmanned aerial vehicle suitable for dense mounting on combat aircraft according to claim 1, characterized in that: The body (1) is a prism.

9. The aerodynamic layout structure of the unmanned aerial vehicle suitable for dense mounting on combat aircraft according to claim 1, characterized in that: The first power device (5) and the second power device (6) both comprise a motor and a connecting rod mechanism connected to the motor.

10. The aerodynamic layout structure of the unmanned aerial vehicle suitable for dense mounting on combat aircraft according to claim 1, characterized in that: A first air intake and exhaust system is provided at the middle of the fuselage (1), and a second air intake and exhaust system is provided at the tail of the UAV fuselage (1).

Images