CN216660278U - Solar sensor unmanned aerial vehicle - Google Patents

Abstract

The present application belongs to the technical field of aircraft design, and in particular relates to a solar sensor drone. The UAV includes a fuselage, a wing, a flat tail and a power system. The wings include an inner wing and an outer wing. The inner wing is supported on the abdomen of the fuselage by a truss. The inner wing is rectangular and the outer wing is trapezoidal. The longer bottom side of the trapezoid is butted on the short rectangular side of the inner wing, and the outer wing is bent upward relative to the inner wing to a set angle. Multiple thrust electric propellers on the trailing edge of the wing. The electric propellers are powered by an energy system based on a solar array. The trailing edge of the wing is provided with ailerons. The ailerons include rolling ailerons away from the fuselage and elevators close to the fuselage. wing. The configuration of the truss-supported wing in the present application has good anti-bending properties, the deformation of the wing is significantly reduced, and the aerodynamic performance and safety of the flexible wing are greatly improved.

Description

A solar sensor drone

technical field

The present application belongs to the technical field of aircraft design, and in particular relates to a solar sensor drone.

Background technique

In the prior art, large aspect ratio solar-powered UAVs are designed with flexible wings. Because of the strength, stiffness and aeroelasticity of the wings, when subjected to large longitudinal gust disturbances, the aircraft is likely to experience pitch oscillations and enter a stall. The angle of attack will cause the wing to break and the plane to crash. For example, the "Helios" solar drone in the United States is very prone to accidents for solar drones with an aspect ratio greater than 30.

Utility model content

In order to solve the above technical problems, the present application provides a solar sensor UAV, which adopts the truss support wing technology to effectively improve the strength and stiffness of the large aspect ratio UAV wing, reduce the structural weight, and ensure that the aircraft has good performance. Aerodynamic performance and flight safety.

The solar sensor UAV of the present application mainly includes a fuselage, a wing, a flat tail and a power system. The wing includes an inner wing and an outer wing. The inner wing is supported on the abdomen of the fuselage by a truss, and the inner wing is rectangular. , the outer wing is a trapezoid, the longer bottom edge of the trapezoid is butted on the rectangular short side of the inner wing, the outer wing is bent upward relative to the inner wing to a set angle, and the power system includes a set of components installed on the leading edge of the wing. A plurality of pulling electric propellers and a plurality of thrust electric propellers installed on the trailing edge of the wing, the electric propellers are powered by an energy system based on a solar cell array, the trailing edge of the wing is provided with ailerons, and the ailerons include remote The roll aileron on the fuselage and the elevator aileron close to the fuselage.

Preferably, the set angle is 12°.

Preferably, the airfoil adopts a high-lift airfoil, and the high-lift airfoil is designed so that the lift coefficient is not less than 0.96, the maximum lift coefficient is not less than 1.85, the wing aspect ratio is not less than 30, and the wing load is not more than 9kg /m ² .

Preferably, one end of the truss connecting the wing is set at a position of 68% of the half-span of the wing from the root of the wing, and at a position of 52% of the chord of the leading edge of the wing.

Preferably, an elastic buffer device is arranged between the truss and the fuselage.

Preferably, the elastic buffer means includes a buffer.

Preferably, 10 pulling electric propellers are installed on the leading edge of the wing, and 2 thrust electric propellers are installed on the trailing edge of the wing.

Preferably, the energy system includes an energy storage battery, and the energy storage battery adopts a lithium-sulfur battery.

Preferably, the outer side of the roll aileron is located at 78% of the half-span of the wing from the wing root, and the inner side of the roll aileron is located at 58% of the wing from the wing root. In the half-span position, the outer side of the elevon is connected to the inner side of the roll aileron, and the inner side of the elevon is located at a position of 38% of the half-span of the wing from the wing root.

Preferably, the horizontal tail is arranged at the rear of the fuselage, and the two ends are respectively provided with vertical tails, the inner side of each vertical tail is the stabilizer surface of the horizontal tail, and the outer side is a full-motion flat tail that can be differentially deflected. The control system is arranged to receive data from a normal overload sensor mounted on the support truss to make adjustments to the full motion flat tail.

The configuration of the truss-supported wing in the present application has good anti-bending properties, the deformation of the wing is significantly reduced, and the aerodynamic performance and safety of the flexible wing are greatly improved.

Description of drawings

FIG. 1 is a top view of a preferred embodiment of the solar sensor drone of the present application.

FIG. 2 is a front view of a preferred embodiment of the solar sensor drone of the present application.

FIG. 3 is a side view of a preferred embodiment of the solar sensor drone of the present application.

Among them, 1: fuselage; 2: inner wing; 3: outer wing; 4: roll aileron; 5: elevon; 6: airfoil support truss; 7: vertical tail; 8: rudder; 9: Horizontal tail stabilizer; 10: full-motion horizontal tail; 11: heading control motor; 12: front landing gear; 13: rear landing gear.

Detailed ways

In order to make the objectives, technical solutions and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to be used to explain the present application, but should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application. The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The purpose of this application is to provide a type of solar sensor UAV aerodynamic layout, so that the aircraft has a large mission load and good high-altitude, day and night flight capability, and can perform tasks such as reconnaissance, early warning and communication relay in subcritical space .

The solar sensor UAV of the present application includes a fuselage, a wing, a flat tail and a power system. The wing includes an inner wing 2 and an outer wing 3. The inner wing 2 is supported on the abdomen of the fuselage by a truss 6, and the inner wing 2 is supported on the abdomen of the fuselage. The wing 2 is a rectangle, the outer wing is a trapezoid, the longer bottom edge of the trapezoid is butted on the short side of the rectangle of the inner wing 2, and the outer wing 3 is bent upward relative to the inner wing to a set angle, the power system Including a plurality of pulling electric propellers installed on the leading edge of the wing and a plurality of thrust electric propellers installed on the trailing edge of the wing, the electric propellers are powered by an energy system based on a solar cell array, and the trailing edge of the wing is provided with ailerons, The ailerons include roll ailerons away from the fuselage and elevons close to the fuselage.

The truss-supported wing solar sensor UAV type provided by this application can significantly reduce the structural weight, improve the task load, the stiffness and aerodynamic efficiency of the wing, and realize high-altitude and long-endurance flight. The aerodynamic layout is shown in Figure 1-Figure 3 . This configuration UAV can perform tasks such as reconnaissance, early warning and communication relay in subcritical space. Its key technologies include truss-supported wing design, power system design, horizontal tail configuration design, aileron configuration design, and three-axis attitude. It consists of seven parts: control system design, anti-stall design and mission system design.

1. Truss-supported wing design

The high-lift airfoil with good stall performance is adopted, the design lift coefficient is not less than 0.96, and the maximum lift coefficient is not less than 1.85. The wing aspect ratio is not less than 30, and the wing load is not more than 9kg/m2. The inner wing 2 is rectangular, the outer wing 3 is trapezoidal, and is turned upward by 12°, and the connection between the inner and outer wings is located at 85% of the half-span.

The truss-supported wing design effectively solves the problems of poor flexural strength and heavy structural weight of wings with large aspect ratios. Compared with the conventional wing, the truss-supported wing configuration reduces the structural weight by about 6% and increases the flight time performance by more than 20%.

The cross section of the truss 6 (the cross section of the rod) is a symmetrical laminar airfoil. The connection between the truss and the wing is located at 68% of the half span of the wing and 52% of the chord length of the wing (from leading edge to trailing edge). An elastic buffer device is installed at the connection between the truss and the fuselage. When a load occurs, the truss will move to the inside of the fuselage to reduce the compressive load of the truss. In an alternative embodiment, the trusses are connected to the fuselage by means of bumpers.

2. Power system design

The power of the aircraft comes from 12 electric propellers, the motors are brushless permanent magnet DC motors, and the propellers use double-blade wide-chord laminar flow composite blades. The distributed power system can use the propeller slip flow to increase the maximum lift coefficient and stall angle of attack of the wing. Ten pull electric propellers are installed on the leading edge of the outer wing, and two thrust electric propellers are installed on the trailing edge as heading control motors.

The energy system consists of solar array, energy storage battery and energy control system. The absorption of solar energy uses high-efficiency, ultra-thin, ultra-light, and highly flexible crystalline silicon solar cells. The energy storage battery adopts lithium-sulfur battery with high energy density. The energy system control adopts the distributed cooperative control method to realize the cooperative work among each module, and then achieve the control goal of system balance and energy supply and demand balance.

In a specific embodiment, the power of the aircraft comes from 12 electric propellers, each with a power of 3.55KW, and the motors and propellers weigh 141kg. The energy system consists of solar array, energy storage battery and energy control system. The collection of solar energy uses high-efficiency, ultra-thin, ultra-light, and highly flexible crystalline silicon solar cells. The solar panel area is 326m ² and weighs 93kg. The energy storage battery adopts a lithium-sulfur battery with an energy density of 300wh/kg, and the energy storage battery weighs 717kg.

In a specific embodiment, the cross section of the fuselage is a vertical ellipse, the front part of the fuselage is an equipment bay and a front landing gear bay, and the middle part is a battery bay.

3 Flat tail configuration design

The horizontal tail 10 is installed at the tail of the fuselage, and the vertical tail 7 is installed at the 52% half-span of the horizontal tail. The inner side of the vertical tail is the stabilizer of the horizontal tail, and the outer side is the full-motion horizontal tail that can be differentially deflected.

In a specific embodiment, the flat tail has a capacity of 0.77 and a flat tail area of 36 m ² , and is installed at the rear of the rear fuselage. The airfoil adopts NACA63 symmetrical laminar airfoil with a thickness of 0.11. The flat tail area of the stabilizer is 20m ² , the area of the full-motion flat tail is 18m ² , and the declination angle is -20°～13°. The vertical tail capacity is 0.07, and the vertical tail area is 68m ² . Two rectangular vertical tails are installed on the outer side of the inner horizontal tail respectively. The vertical tail below the horizontal tail is the heading stabilizer, which doubles as the rear landing gear. The organic wheel is installed below it, which can be stored in the vertical tail after take-off. A rudder is installed on the trailing edge of the upper vertical tail, and the maximum deflection angle of the rudder is 22°.

4. Aileron configuration design

In order to solve the problem of poor bending and torsional stiffness of the outer wing with a large aspect ratio, the aileron is composed of inner and outer sections. The outside aileron is called roll aileron 4, its outside is located at 78% of the half span of the wing, and the inside is at 58% of the half span of the wing; the inside aileron is called elevon 5, and its inside is located at the half span of the wing. 38% of the extension. The inboard ailerons are deflected in the same direction to realize pitch control, and the opposite-direction deflection realizes roll control.

In a specific embodiment, the aileron area is 20.8m ² , wherein the roll aileron area is 10m ² and the elevon area is 10.8m ² . The outer side of the roll aileron is 78% of the half-span of the tail, and the inner side of the elevon is located at 38% of the half-span of the wing, and the aileron declination angle is not greater than 18°.

5. Design of three-axis attitude control system

The pitch control system is composed of the outer full-motion horizontal tail and the elevons on the inner side of the wing. The roll control system is composed of two ailerons and the outer differential horizontal tail. The heading and attitude control system is composed of the upper rudder of the vertical tail and the heading of the outer side of the wing. Control the motor configuration.

6. Gust mitigation and anti-stall control design

The normal overload sensor is installed on the wing, fuselage and supporting truss. In the flight control system, according to the normal overload information input, the full-motion horizontal tail can be adjusted to prevent the aircraft from entering the stall angle of attack and reduce the normal direction generated by the gust. Overload varies greatly. In this embodiment, the deflection of the horizontal tail is controlled, the attitude of the aircraft is adjusted, the overload of the wing is reduced, the deformation of the wing is minimized, and the aircraft is prevented from entering a stall state.

7. Mission system design

The mission system consists of electro-optical, infrared sensors and synthetic aperture radar, which can conduct situational surveillance over a wide area, and can focus on specific targets for threat assessment, target location and bombing damage assessment. The sensor systems are connected by a bus and share a processor. The synthetic aperture radar is installed on the inner surface of the inner wing under the skin, and the photoelectric and infrared sensors and information processing machines are installed in the equipment bay of the fuselage.

The configuration of the truss-supported wing in the present application has good anti-bending properties, the deformation of the wing is significantly reduced, and the aerodynamic performance and safety of the flexible wing are greatly improved.

The above are only specific embodiments of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed in the present application, All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims (10)

1. a solar sensor unmanned aerial vehicle, comprising fuselage, wing, horizontal tail and power system, it is characterized in that, described wing comprises inner wing (2) and outer wing (3), inner wing (2) ) is supported on the belly of the fuselage by a truss (6), the inner wing (2) is rectangular, the outer wing is trapezoidal, the longer bottom edge of the trapezoid is butted on the short rectangular side of the inner wing (2), and the outer wing (2) is rectangular. The wing (3) is upwardly bent at a set angle relative to the inner wing, and the power system includes a plurality of pulling electric propellers installed on the leading edge of the wing and a plurality of thrust electric propellers installed on the trailing edge of the wing. The energy system of the solar cell array supplies power, and the trailing edge of the wing is provided with ailerons, and the ailerons include a roll aileron away from the fuselage and an elevator aileron close to the fuselage. 2 . The solar sensor drone of claim 1 , wherein the set angle is 12°. 3 . 3. The solar sensor drone of claim 1, wherein the wing adopts a high-lift airfoil, and the high-lift airfoil is designed to have a lift coefficient of not less than 0.96 and a maximum lift coefficient of not less than 1.85 , the wing aspect ratio is not less than 30, and the wing load is not more than 9kg/m ² . 4. The solar sensor drone according to claim 1, characterized in that, one end of the truss (6) connected to the wing is arranged at a position of 68% of the half-span of the wing from the root of the wing, and 52% of the wing chord length from the leading edge of the wing. 5. The solar sensor drone according to claim 1, characterized in that, an elastic buffer device is arranged between the truss (6) and the fuselage. 6. The solar sensor drone of claim 5, wherein the elastic buffer device comprises a buffer. 7 . The solar sensor UAV of claim 1 , wherein 10 pulling electric propellers are installed on the leading edge of the wing, and 2 thrust electric propellers are installed on the trailing edge of the wing. 8 . 8 . The solar sensor drone according to claim 7 , wherein the energy system comprises an energy storage battery, and the energy storage battery adopts a lithium-sulfur battery. 9 . 9 . The solar sensor UAV of claim 1 , wherein the outer side of the roll aileron is located at a position of 78% of the half span of the wing from the wing root, and the roll aileron The inner side of the wing is located at 58% of the half-span of the wing from the wing root, the outer side of the elevon is connected to the inner side of the roll aileron, and the inner side of the elevon is located at the distance of the wing. The 38% half-span position of the wing root. 10. The solar sensor drone according to claim 1, wherein the horizontal tail is arranged at the rear of the fuselage, and the two ends are respectively provided with vertical tails. A differentially deflected full-motion fin, the control system of which is arranged to receive data from a normal overload sensor mounted on the support truss to make adjustments to the full-motion fin.

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