CN111003145A

CN111003145A - Variable unmanned aerial vehicle

Info

Publication number: CN111003145A
Application number: CN201911356668.9A
Authority: CN
Inventors: 黎欣
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2019-12-25
Filing date: 2019-12-25
Publication date: 2020-04-14

Abstract

The embodiment of the present application provides a variable-body drone, the variable-body drone includes a fuselage 1, an inner wing 2, an outer wing 3, a tail 4, a slide rail 5, a slider 6, Rack 7, drive gear 8, tail rail 9, tail slider 10, tail rack 11, tail drive gear 12, wherein: the two sides of the middle part of the fuselage 1 are respectively fixed with inner section wings 2, inner section aircraft The inside of the wing 2 is provided with a retractable outer wing 3, and the tail of the fuselage 1 is provided with a tail 4 that can move along the axis of the fuselage; One end of the two outer wings 3 is provided with a sliding block 6, and a driving gear 8 is provided in the middle of the fuselage 1; one of the sliding blocks 6 is connected with one end of a rack 7, and the other end of the rack 7 is connected with the driving gear 8 meshing connection; another slider 6 is connected with one end of another rack 7, and the other end of the other rack 7 is meshed with the drive gear 8.

Description

Variable unmanned aerial vehicle

Technical Field

The invention belongs to the technical field of design of morphing airplanes, and relates to a morphing unmanned aerial vehicle.

Background

The variant unmanned aerial vehicle is an unmanned aerial vehicle which changes the whole configuration through materials, structures and mechanisms thereof, advanced flow and flight control so as to adapt to different task requirements and can obtain the optimal performance under different flight states. A common morphing unmanned aerial vehicle is a flexible wing morphing aircraft, the capability of changing the aspect ratio of the aircraft is very large, the influence on the endurance capability of the aircraft is obvious, and the large-scale change of the wing area is achieved through the flexible deformation of the wings so as to meet the requirements of different flight states and tasks. However, in the existing morphing aircraft with retractable wings, when the wings are unfolded or retracted, the gravity center position and the aerodynamic focus of the aircraft are changed, and the stability and the maneuverability of the aircraft are poor. In addition, most of the deformation drives are selected from hydraulic drive, screw drive and the like, and the mechanism is complex and the structure is heavy.

Disclosure of Invention

The invention designs a variable unmanned aerial vehicle. The unmanned aircraft has the advantages of simple structure, light mechanism, capability of being unfolded or contracted along the unfolding direction and the course direction according to the change of flight tasks and environments, large lifting force at low speed, good taking-off and landing performance, small aerodynamic resistance at high speed, good maneuverability and the like. And meanwhile, the retractable wing and the tail force arm are convenient for the storage of the hangar.

The embodiment of the application provides a variable unmanned aerial vehicle, variable unmanned aerial vehicle includes fuselage 1, interior section wing 2, outer section wing 3, fin 4, slide rail 5, slider 6, rack 7, drive gear 8, fin slide rail 9, fin slider 10, fin rack 11, fin drive gear 12, wherein:

inner-section wings 2 are fixedly arranged on two sides of the middle part of the fuselage 1 respectively, telescopic outer-section wings 3 are arranged inside the inner-section wings 2, and a tail wing 4 which can be telescopic along the axis of the fuselage is arranged at the tail part of the fuselage 1;

sliding rails 5 are arranged inside the wings 2 on two sides of the fuselage 1, sliding blocks 6 are arranged at one ends of the two outer-section wings 3, and a driving gear 8 is arranged in the middle of the fuselage 1; one of the sliding blocks 6 is connected with one end of a rack 7, and the other end of the rack 7 is meshed with a driving gear 8; the other sliding block 6 is connected with one end of the other rack 7, and the other end of the other rack 7 is meshed with the driving gear 8;

the middle part of the machine body 1 is provided with an empennage slide rail 9 along the axis direction of the airplane, the front end of the force arm of the empennage 4 is fixedly provided with an empennage slide block 10, the upper surface of the force arm of the empennage 4 is provided with an empennage rack 11, and the tail part of the machine body 1 is provided with an empennage driving gear 12; the tail sliding block 10 slides on the tail sliding rail 9; the tail rack 11 is meshed with the tail driving gear 12.

Preferably, the fuselage 1 is of a hollow skeleton structure.

Preferably, the inner wing section 2 is of a hollow hard shell structure.

Preferably, the tail 4 is a hollow hard shell structure.

Preferably, the outer wing section 3 is of a full-height foam sandwich structure.

Preferably, the length of the sliding rail 5 is less than or equal to the length of the wing 2.

Preferably, the length of the tail sliding rail 9 is less than or equal to the length of the body.

Preferably, the tail sliding plane is above the wing sliding plane, wherein the plane where the tail sliding rail 9, the tail sliding block 10, the tail rack 11 and the tail driving gear 12 are located is the tail sliding plane; the plane where the sliding rail 5, the sliding block 6, the rack 7 and the driving gear 8 are located is a wing sliding plane.

In conclusion, the unmanned aircraft has a simple structure and a light mechanism, can be unfolded or contracted along the unfolding direction and the heading direction according to the change of the flight task and the environment, can better give consideration to high-low speed and high-low altitude flight performance, and can effectively solve the contradiction between the endurance and the maneuverability.

Drawings

Fig. 1 is a schematic structural diagram of a variable unmanned aerial vehicle according to an embodiment of the present invention;

wherein: 1-fuselage, 2-inner section wing, 3-outer section wing, 4-empennage, 5-sliding rail, 6-sliding block, 7-rack, 8-driving gear, 9-empennage sliding rail, 10-empennage sliding block, 11-empennage rack and 12-empennage driving gear.

Detailed Description

The invention belongs to the technical field of design of morphing airplanes, and relates to a morphing unmanned aerial vehicle. The unmanned aircraft has simple structure and light mechanism, and can be unfolded or contracted along the unfolding direction and the heading direction according to the change of flight tasks and environments. During takeoff, wings and a tail arm are unfolded, the lift force is large, and the takeoff performance of the airplane is good; the wings and the tail arm are contracted during high-speed flight, the aerodynamic resistance is small, and the maneuverability of the airplane is good; when landing, the wings and the tail force arm are unfolded again, the lift-drag ratio is large, and the landing distance of the airplane is short; when the hangar is stored, the wings and the tail force arm are contracted again, and the storage space required by the airplane is small.

The technical scheme of the invention is further illustrated by specific examples.

The variant unmanned aerial vehicle comprises a body 1, an inner section wing 2, an outer section wing 3, a tail wing 4, a sliding rail 5, a sliding block 6, a rack 7, a driving gear 8, a tail wing sliding rail 9, a tail wing sliding block 10, a tail wing rack 11 and a tail wing driving gear 12.

The fuselage 1 is a hollow framework structure, and is provided with an inner section wing 2, a driving gear 8, a tail wing sliding rail 9 and a tail wing driving gear 12.

The inner section of the wing 2 is a hollow hard shell structure, and a slide rail 5 is arranged in the inner section of the wing. The outer section of the wing 3 is of a full-height foam sandwich structure, and a sliding block 6 and a rack 7 are fixed on the inner side of the outer section of the wing. The driving gear 8 drives the outer section wing 3 to slide through the driving rack 7, so that the outer section wing 3 is unfolded or contracted, and the wing has the characteristics of large lifting force at low speed, good lifting and landing performance, small aerodynamic resistance at high speed, good maneuverability and the like. And meanwhile, the retractable wings are convenient for the storage of the hangar.

4 is a tail wing, a hollow hard shell structure, a tail wing sliding block 10 is fixed at the front end of the force arm, and a tail wing rack 11 is arranged on the upper surface of the force arm. The tail driving gear 12 drives the tail 4 to slide by driving the tail rack 11, so that the front and back movement of the tail 4 is realized, and the airplane still has better pitching stable back and maneuverability after being modified. Meanwhile, the movable tail 4 is convenient for the storage of the hangar.

Claims

1. The utility model provides a variable unmanned aerial vehicle, its characterized in that, variable unmanned aerial vehicle includes fuselage (1), interior section wing (2), outer section wing (3), fin (4), slide rail (5), slider (6), rack (7), drive gear (8), fin slide rail (9), fin slider (10), fin rack (11), fin drive gear (12), wherein:

inner-section wings (2) are respectively fixedly arranged on two sides of the middle part of the fuselage (1), telescopic outer-section wings (3) are arranged inside the inner-section wings (2), and a tail wing (4) which can be telescopic along the axis of the fuselage is arranged at the tail part of the fuselage (1);

sliding rails (5) are arranged inside the wings (2) on the two sides of the fuselage (1), sliding blocks (6) are arranged at one ends of the two outer-section wings (3), and a driving gear (8) is arranged in the middle of the fuselage (1); one of the sliding blocks (6) is connected with one end of one rack (7), and the other end of the rack (7) is meshed with a driving gear (8); the other sliding block (6) is connected with one end of the other rack (7), and the other end of the other rack (7) is meshed with the driving gear (8);

a tail wing sliding rail (9) is arranged in the middle of the machine body (1) along the axis direction of the airplane, a tail wing sliding block (10) is fixedly arranged at the front end of the force arm of the tail wing (4), a tail wing rack (11) is arranged on the upper surface of the force arm of the tail wing (4), and a tail wing driving gear (12) is arranged at the tail part of the machine body (1); the tail wing sliding block (10) slides on the tail wing sliding rail (9), and the tail wing rack (11) is meshed and connected with the tail wing driving gear (12).

2. The unmanned aerial vehicle of claim 1, wherein the fuselage (1) is a hollow skeletal structure.

3. The unmanned aerial vehicle of claim 1, wherein the inner wing section (2) is of a hollow hard shell structure.

4. Variable-bodied unmanned aerial vehicle according to claim 1, characterized in that the tail fin (4) is of hollow hard-shell structure.

5. The unmanned aerial vehicle of claim 1, wherein the outer wing section (3) is of full height foam sandwich construction.

6. Variable-body unmanned aerial vehicle according to claim 1, characterized in that the length of the sliding rail (5) is less than or equal to the length of the wing (2).

7. Variable unmanned aerial vehicle according to claim 1, characterized in that the empennage slide rail (9) is less than or equal to the length of the fuselage.

8. The unmanned variable body airplane according to claim 1, wherein a tail sliding plane is above a wing sliding plane, wherein the planes of the tail sliding rail (9), the tail sliding block (10), the tail rack (11) and the tail driving gear (12) are tail sliding planes; the planes where the sliding rail (5), the sliding block (6), the rack (7) and the driving gear (8) are located are wing sliding planes.