CN212530067U

CN212530067U - Solar unmanned aerial vehicle with tilting wings

Info

Publication number: CN212530067U
Application number: CN202020660952.7U
Authority: CN
Inventors: 谢晋东
Original assignee: Hefei Innovation Research Institute of Beihang University
Current assignee: Hefei Innovation Research Institute of Beihang University
Priority date: 2020-04-26
Filing date: 2020-04-26
Publication date: 2021-02-12
Anticipated expiration: 2030-04-26

Abstract

The utility model discloses a wing solar energy unmanned aerial vehicle verts, including fuselage, vertical fin, symmetric connection at the wing of fuselage both sides, the fin of symmetric connection in the fuselage both sides to and set up the rotor on wing and fin, its characterized in that: the wings and the empennage are connected to the machine body in a mode of rotating around the respective long side directions; the wing comprises a fixed part close to the fuselage and a rotating part which is far away from the fuselage and is connected to one end, far away from the fuselage, of the fixed part in a rotatable mode, and a solar cell piece capable of providing electric energy for the unmanned aerial vehicle is fixedly arranged on the surface of the rotating part; the wings of the unmanned aerial vehicle have a two-degree-of-freedom tilting function, the solar cell pieces are arranged on the surfaces of the wings, an optimal sun irradiation angle is obtained by adjusting the rotation angles of the two degrees of freedom of the wings, and the comprehensive energy circulation efficiency of the aircraft is improved.

Description

Solar unmanned aerial vehicle with tilting wings

Technical Field

The utility model relates to an unmanned aerial vehicle field, concretely relates to wing solar energy unmanned aerial vehicle verts.

Background

With the further improvement of the aircraft layout research and the continuous innovation of researchers on airborne equipment, the future special aircraft is necessarily a comprehensive flight platform integrating multiple layouts, multiple functions, cooperation and load aircraft integration.

The unmanned aerial vehicle with the tilting wings in the prior art is poor in endurance, and the surface of the unmanned aerial vehicle is provided with the solar cell pieces to provide electric energy for the unmanned aerial vehicle in the advanced prior art, but the unmanned aerial vehicle switches the process at different flight attitudes, so that the solar irradiation angle changes, the power supply capacity of the solar cell pieces is unstable, and the further development of the technology is limited.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model provides a wing solar energy unmanned aerial vehicle verts.

In order to solve the technical problem, the utility model adopts the following technical scheme:

a solar unmanned aerial vehicle with tilting wings comprises a fuselage, a vertical fin, wings symmetrically connected to two sides of the fuselage, empennages symmetrically connected to two sides of the fuselage, and rotors arranged on the wings and the empennages, wherein the wings and the empennages are connected to the fuselage in a manner of rotating around the respective long edge directions; the wing is including the fixed part that is close to the fuselage to and keep away from the fuselage and be connected to the rotation portion that fuselage one end was kept away from to the fixed part with rotatable mode, the surface of rotation portion sets firmly the solar wafer that can provide the electric energy for unmanned aerial vehicle.

Furthermore, the empennage is fixedly provided with horizontal flight tail rotors, and the horizontal flight tail rotors on the empennages on the two sides are symmetrically arranged around the fuselage; the inboard of wing has set firmly first anterior rotor and the outside has set firmly the anterior rotor of second, and first anterior and the anterior rotor of second on the wing of both sides all are about fuselage symmetrical arrangement, the head that tail rotor, first anterior rotor and the anterior rotor of second all towards the fuselage is flown to the tie.

Furthermore, first anterior rotor includes the rotor body that sets firmly on the wing, sets up the interior motor of rotor body and the fin of being connected with the working portion of motor with the mode of can buckling.

Compared with the prior art, the utility model has the advantages that:

1. the wings of the unmanned aerial vehicle have a two-degree-of-freedom tilting function, the solar cell pieces are arranged on the surfaces of the wings, an optimal sun irradiation angle is obtained by adjusting the rotation angles of the two degrees of freedom of the wings, and the comprehensive energy circulation efficiency of the aircraft is improved.

2. The rotation angle of accessible adjustment wing reduces the air resistance that unmanned aerial vehicle climbed the in-process fast, improves the aerodynamic efficiency is synthesized to the aircraft.

3. Under each flight state, the aircraft body is always kept horizontal, can carry some special loads, and high-altitude low-speed target reconnaissance, locking, tracking and disposal are efficiently completed.

Drawings

Fig. 1 is a schematic view of the unmanned aerial vehicle in a high-altitude high-speed cruising state;

fig. 2 is a schematic diagram of the unmanned aerial vehicle in a fast vertical climbing state and a high altitude fixed point hovering state;

fig. 3 is a schematic diagram of the relative position of each rotor when the unmanned aerial vehicle of the present invention is in the fast vertical climbing state and the high altitude fixed point hovering state;

fig. 4 is the utility model discloses unmanned aerial vehicle is in the schematic diagram of big angle of attack low-speed level flight state.

In the figure: 1. a body; 2. an airfoil; 3. a tail wing; 4. hanging a tail; 5. a low-speed rotor; 6. a high-speed rotor; 7. a flat tail rotor; 8. provided is a solar cell.

Detailed Description

A preferred embodiment of the present invention will be described in detail below with reference to the accompanying drawings.

As shown in fig. 1, a wing solar unmanned aerial vehicle verts, including fuselage 1, vertical fin 4, symmetric connection wing 2, the symmetric connection fin 3 in the fuselage both sides to and set up the rotor on wing and fin, its characterized in that: the wings and the empennage are connected to the machine body in a mode of rotating around the respective long side directions; the wing includes the fixed part 2-1 that is close to the fuselage to and keep away from the fuselage and be connected to the fixed part with rotatable mode and keep away from the rotation portion 2-2 of fuselage one end, the surface of rotation portion sets firmly solar wafer 8 that can provide the electric energy for unmanned aerial vehicle.

The fuselage has a large slenderness ratio and has a small resistance coefficient in the vertical direction and the forward flying direction.

The wings are symmetrically arranged on two sides of the fuselage and positioned in the front part of the fuselage, and the empennages are symmetrically arranged on two sides of the fuselage and positioned in the rear part of the fuselage.

The wing can rotate relative to the fuselage, and the rotating shaft of the wing is parallel to the long edge direction of the wing; the tail wing can rotate relative to the body, and the rotating shaft of the tail wing is parallel to the long edge direction of the tail wing.

As shown in fig. 1, the tail wing is fixedly provided with a horizontal tail rotor wing 7, and the horizontal tail rotor wings on the tail wings on the two sides are symmetrically arranged about the fuselage; the inboard of wing has set firmly first anterior rotor 5 and the outside has set firmly anterior rotor 6 of second, and first anterior rotor and the anterior rotor of second on the wing of both sides all are about fuselage symmetrical arrangement, the head that tail rotor, first anterior rotor and the anterior rotor of second all towards the fuselage is flown to the tie.

In this embodiment, 2 low-speed rotors and 4 high-speed rotors are specifically adopted, wherein the first front rotor is a low-speed rotor, and the second front rotor is a high-speed rotor; the horizontal flying tail rotor wing is a high-speed rotor wing; the rotor wings are driven by the motor, the motor is located in the motor short cabin, and in the process of tilting of the rotor wings and the tail wings, the pulling force direction of the rotor wings is always parallel to the wing chord direction or the tail wing chord direction, so that the propelling efficiency of the rotor wings can be fully exerted, and meanwhile, the pressure difference resistance generated by the rotor wings or the tail wings can be reduced in the fast climbing stage.

The first front rotor on the wing on one side of the fuselage and the first front rotor on the wing on the other side of the fuselage are symmetrically arranged around the fuselage; the second front rotor on the wing on one side of the fuselage and the second front rotor on the wing on the other side of the fuselage are symmetrically arranged around the fuselage; the plane flight tail rotor wing on the empennage at one side of the fuselage and the plane flight tail rotor wing on the empennage at the other side of the fuselage are symmetrically arranged around the fuselage.

The solar cell pieces are arranged on the upper surface of the rotating part of the wing and the upper surface of the tail wing, the rotating part is connected with the fixed part in a rotating mode, and the specific implementation mode can be that the rotating part is connected with the fixed part through a rotating motor; the optimum sun irradiation angle can be found by changing the tilt angle of the wings, the rotation angle of the rotating portion, and the tilt angle of the empennage.

The dynamic adjustment of the solar cell does not need an additional control mechanism, and can be realized only by adjusting the tilting angle of the wings.

The three angles can be changed randomly in a small range to compare the maximum power supply efficiency of the solar cell, and the optimal solar irradiation angle is searched; other existing ways of finding the optimum sun illumination angle may also be used.

As shown in fig. 1, the first front rotor 5 includes a rotor body fixed on the wing, a motor disposed in the rotor body, and a wing panel connected with a working portion of the motor in a bendable manner.

The utility model discloses the aircraft can climb perpendicularly fast, hover, big angle of attack low-speed level flies and high altitude four basic flight states of cruising at a high speed.

As shown in fig. 2 and 3, when the unmanned aerial vehicle is in a fast vertical climbing state and a high altitude fixed point hovering state, the wings and the empennage rotate, so that all the rotors face upward; under the state of fast vertical climbing, all rotors of the unmanned aerial vehicle run at full speed to realize fast climbing, at the moment, the rotating speeds of the first front rotors on the wings on two sides are the same, and the rotating directions are opposite, so that the respective generated counter torques in the vertical flying state are balanced.

As shown in fig. 4, in the climbing process, the tilt angle of the wings and the empennage can be changed according to the solar radiation angle to find the optimal solar radiation angle, so that the solar power generation amount is maximally improved.

As shown in fig. 1, in the high-altitude high-speed cruising state, the unmanned aerial vehicle is typically arranged in a normal manner with a large aspect ratio, and the second front rotor 6 and the flat tail rotor 7 provide forward flight power for the unmanned aerial vehicle.

The rotation angle of the rotation part can be changed to realize the up-turning and down-turning of the wing, so that the solar irradiation angle of the solar cell can be dynamically adjusted under the condition of not influencing the flat flight stability, and the comprehensive energy circulation efficiency of the airplane is improved.

In the high altitude, high speed cruise condition, the low speed rotor 5 inboard of the drone wing should stop working while remaining in a folded condition to reduce flight resistance.

Of course, the distribution and number of the rotors in this embodiment do not limit the scope of the present invention, and in different embodiments, the aircraft may also be designed to combine four rotors or arrange the rotors outside the wing, and the specific layout and the number of the rotors depend on the specific overall design scheme.

In this embodiment, the wing 2 should be designed with a left aileron and a right aileron, and the vertical fin 4 should be designed with a rudder, so as to realize attitude control of the unmanned aerial vehicle in a flat flight state.

As shown in fig. 4, when the wings and the empennage have a certain tilting angle, the unmanned aerial vehicle can fly at a low speed, and tracking and locking of a high-altitude low-speed target are realized.

No matter what kind of angle of verting is in with the empennage that can vert, can not influence the fuselage gesture, the fuselage is at whole VTOL, the low-speed flat in-process that flies and high-speed flat, and the fuselage can remain same gesture throughout, provides stable mounting platform for some special load.

The core of the utility model lies in the combination of the layout of the tilting wings and the solar power generation management; the tilting wings provide an actuating mechanism for the solar cell to find the optimal irradiation angle while improving the pneumatic efficiency, and the solar cell provides an energy basis for the high-altitude long-term cruise of the aircraft, so that the flight time can be effectively prolonged.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides a wing solar energy unmanned aerial vehicle verts, includes fuselage (1), vertical fin (4), symmetric connection wing (2) in the fuselage both sides, symmetric connection fin (3) in the fuselage both sides to and set up the rotor on wing and fin, its characterized in that: the wings and the empennage are connected to the machine body in a mode of rotating around the respective long side directions; the wing is including fixed part (2-1) that is close to the fuselage to and keep away from the fuselage and be connected to the fixed part with rotatable mode and keep away from rotation portion (2-2) of fuselage one end, the surface of rotation portion sets firmly solar wafer (8) that can provide the electric energy for unmanned aerial vehicle.

2. The tiltrotor wing solar drone of claim 1, wherein: the empennage is fixedly provided with horizontal flight tail rotors (7), and the horizontal flight tail rotors on the empennages on the two sides are symmetrically arranged around the fuselage; the inboard of wing has set firmly first anterior rotor (5) and the outside has set firmly anterior rotor (6) of second, and first anterior and the anterior rotor of second on the wing of both sides all are about fuselage symmetrical arrangement, the head that tail rotor, first anterior rotor and the anterior rotor of second all towards the fuselage is flown to the tie.

3. The tiltrotor wing solar drone of claim 2, wherein: first anterior rotor (5) including set firmly the rotor body on the wing, set up the motor in the rotor body and with the blade that the working portion of motor is connected with the mode of can buckling.