CN113788138A

CN113788138A - Variable-angle solar wing structure suitable for unmanned aerial vehicle

Info

Publication number: CN113788138A
Application number: CN202111214948.3A
Authority: CN
Inventors: 武明建; 张瑞洁; 吴志林; 李忠新
Original assignee: Nanjing University of Science and Technology
Current assignee: Nanjing University of Science and Technology
Priority date: 2021-10-19
Filing date: 2021-10-19
Publication date: 2021-12-14

Abstract

The invention discloses a variable-angle solar wing mechanism suitable for an unmanned aerial vehicle, and particularly comprises an inner wing, an outer wing and a structural design of a wing adjusting mechanism. When the variable-angle solar wing works, the servo steering engine fixed on the middle wing can drive the swing rod and the connecting rod to rotate, so that the angle of the outer wing can be adjusted, sunlight can irradiate the solar cell panel on the outer wing at a larger angle, and the cruising ability of the unmanned aerial vehicle is enhanced. This patent adopts the mode of split wing, installs solar cell panel on the wing of outside, realizes the regulation to the certain angle of wing of outside through the steering wheel, has solved the power consumption problem of unmanned aerial vehicle when the flight, has creatively provided a variable angle solar energy wing design method suitable for unmanned aerial vehicle.

Description

Variable-angle solar wing structure suitable for unmanned aerial vehicle

Technical Field

The invention relates to a variable-angle solar wing structure design of an unmanned aerial vehicle, in particular to a variable-angle solar wing structure suitable for the unmanned aerial vehicle.

Background

With the increasing demand for airborne surveillance, it is desirable that unmanned aircraft be able to achieve longer flights than manned aircraft, yet it is difficult to achieve continuous flights of several months or even years for performing reconnaissance surveillance and communication relay tasks, relying solely on fuel. The solar aircraft converts solar energy into electric energy in the middle of daytime flight, one part of the electric energy is directly used for flight, redundant electric energy is stored in the storage battery for use at night or when solar radiation is weak, and the operation mode can be continuously circulated when the sun rises the next day. The key technology of the solar aircraft for realizing uninterrupted continuous flight is that the energy converted in the daytime can meet the flight consumption in the daytime and the flight requirement at night.

Due to the factors of strong solar illumination, long illumination time, high solar altitude angle and the like near summer, the solar aircraft can convert to obtain more electric energy in the daytime flight process, so that most solar aircraft can only continuously fly near summer. In winter, the solar aircraft obtains less electric energy through conversion due to factors such as small solar altitude angle and short illumination time in northern latitude and high latitude areas, so that day and night continuous flight is difficult to realize.

Disclosure of Invention

The invention aims to provide a variable-angle solar wing structure suitable for an unmanned aerial vehicle, so that the adjustment work of the relative angle between wings in the flying process of the unmanned aerial vehicle is completed, the sunlight irradiation angle of a solar panel on the wings is adjusted, and the flight endurance time is improved.

The technical solution for realizing the purpose of the invention is as follows:

a variable-angle solar wing structure suitable for an unmanned aerial vehicle,

the wing is divided into three sections: comprises a middle wing and outer wings positioned on two sides of the middle wing;

the middle wing is hinged with the outer wing through a wing morphing mechanism and is symmetrical in morphing configuration;

the wing morphing mechanism is used for driving the outer wing to rotate relative to the middle wing;

the outer wing is provided with a solar cell panel and an illumination acquisition module;

the illumination acquisition module is used for acquiring illumination intensity and controlling the movement of the wing variant mechanism through the navigation system to realize the control of the angle of the outer wing.

Compared with the prior art, the invention has the following remarkable advantages:

(1) the skin that has solar cell panel is installed on the unmanned aerial vehicle wing, makes the aircraft usable solar energy as the flight energy when flying, is favorable to improving duration to the environmental protection.

(2) The outer wing is split from the wing of the unmanned aerial vehicle, when the angle of the solar cell panel irradiated on the outer wing of the aircraft by sunlight is small, the sunlight irradiation angle can be adjusted by adjusting the angle of the outer wing on the premise of not changing the overall flight attitude of the aircraft, and the utilization rate of solar energy is improved.

(3) The outer wings and the middle wings of the unmanned aerial vehicle can be firmly connected through the wing adjusting mechanism of the servo steering engine-connecting rod, and the angle of the outer wings can be effectively controlled. The whole design layout is uniform and balanced, and the wings can realize expected actions.

Drawings

FIG. 1 is a schematic view of a variable angle solar wing mounted to a fuselage of an unmanned aerial vehicle;

FIG. 2 is a schematic view of an intermediate wing structure;

FIG. 3 is a schematic view of a left side wing configuration;

FIG. 4 is a schematic view of a wing adjustment mechanism;

fig. 5 is an operational schematic diagram of the unmanned aerial vehicle adjusting the angle of the outboard wing.

Detailed Description

The invention is further described with reference to the following figures and embodiments.

The invention relates to a variable-angle solar wing mechanism suitable for an unmanned aerial vehicle. The relative positional relationship of the mechanisms is as follows:

with reference to fig. 1, the whole set of adjustable wing is composed of a middle wing B and outer wings (a left wing a and a right wing D) arranged on the left and right sides of the middle wing B, and the two wings are symmetrically arranged. The middle wing B is hinged with the outer wings (a left wing A and a right wing D) through a wing morphing mechanism E, the wing morphing mechanism E is driven by a servo steering engine 10 fixed on the middle wing B, and the deflection angles and the directions of the left wing A and the right wing D in the sun tracking process are the same and can be the same or opposite, so that the wing morphing mechanism is symmetrical.

Referring to fig. 2, the middle wing B includes a first front spar 1, a main spar 2, a first rear spar 3, a series of first ribs 4, and a first skin 5 on which a solar panel is mounted. The first front beam 1, the main beam 2 and the first rear beam 3 penetrate through a series of prefabricated holes in first ribs 4, the first ribs 4 are arranged at a certain distance (equal interval), and a first skin 5 is covered outside the first ribs.

With reference to fig. 3, the outboard wing structure includes a second front spar 6, a second rear spar 7, a series of second ribs 8 and a second skin 9 with a solar panel. The second front beam 6 and the second rear beam 7 pass through a series of prefabricated holes on second ribs 8, the second ribs 8 are arranged at a certain distance (equal interval), and a second skin 9 is covered outside.

Referring to fig. 4, the wing morphing mechanism includes a servo steering engine 10, a swing link 11, a connecting rod 12, a bearing set 13, and a rotating shaft 14. The first front beam 1 of the middle wing and the second front beam 6 of the outer wing are connected through a bearing group 13, so that free rotation can be realized; similarly, the first rear beam 3 of the middle wing and the second rear beam 7 of the outer wing are connected through a bearing set, and free rotation can be realized. The servo steering engine 10 is fixed on a first front beam 1 of the middle wing, the middle of the swing rod 11 is fixed on an output shaft of the servo steering engine 10, the upper end and the lower end of the swing rod 11 are respectively connected with one end of a connecting rod 12 through a rotating shaft 14, and the other end of the connecting rod 12 is rotatably connected with a second front beam 6 of the outer wing through the rotating shaft 14.

When the wings keep a fixed angle, the servo steering engine 10 controls the swing rod 11 to be fixed at a constant position and not to rotate, the swing rod 11 is connected with the connecting rod 12, and the outer wings are supported by the connecting rod 12 to keep the fixed angle.

With reference to fig. 5, in the flight process of the airplane, when the solar rays obliquely irradiate the solar cell panel on the second skin 9 of the wing, the servo steering engine 10 is controlled, the servo steering engine 10 rotates to drive the swing rod 11 to rotate, so that the swing rod 11 drives the upper connecting rod 12 and the lower connecting rod 12 to rotate by a certain angle, the second front beam 6 is pulled to rotate around the bearing set 13, the angle of the outer wings (the left wing a and the right wing D) is adjusted, and the solar cell panel on the outer wings (the left wing a and the right wing D) can be vertically irradiated by the solar rays, so that the endurance time of the airplane is prolonged. Be equipped with light sensor on left side wing A and the right side wing D for detect illumination intensity, the control of outside wing angle is realized to servo steering wheel 10 turned angle of unmanned aerial vehicle navigation system according to illumination intensity control.

During the process of adjusting the wings of the airplane, the deflection angles of the left wing A and the right wing D are the same, and the directions are the same or opposite, so that the symmetrical variant configuration is maintained. The configuration can increase the aspect ratio, reduce the induced resistance, reduce the electric energy consumption and increase the flight time.

Claims

1. A variable-angle solar wing structure suitable for an unmanned aerial vehicle is characterized in that,

2. The variable angle solar wing structure suitable for unmanned aerial vehicles of claim 1, wherein the wing morphing mechanism comprises a servo steering engine, a swing link, a connecting rod;

the middle wing and the outer wings are both provided with a front beam and a rear beam; the front beam of the middle wing is rotationally connected with the front beam of the outer wing; the rear beam of the middle wing is rotationally connected with the rear beam of the outer wing;

the servo steering engine is arranged in the middle wing, and an output shaft of the servo steering engine is connected with the middle of the swing rod;

and the upper end and the lower end of the swing rod are respectively and rotatably connected with a connecting rod, and the connecting rod is rotatably connected with a front beam of the outer wing.

3. The variable angle solar wing structure suitable for unmanned aerial vehicles of claim 1, wherein a solar panel is also provided on the middle wing.

4. The variable angle solar wing structure for unmanned aerial vehicles of claim 1, wherein outboard wing deflection angles of the left and right sides are the same.

5. The variable angle solar wing structure suitable for unmanned aerial vehicles of claim 1, wherein wing ribs are provided in the middle wing and the outer wing at equal intervals.