Multipurpose civil unmanned aerial vehicle based on solar power supply and control method

Abstract

The invention relates to a multipurpose civil unmanned aerial vehicle based on solar power supply and a control method, and belongs to the technical field of unmanned aerial vehicles, the multipurpose civil unmanned aerial vehicle comprises a fuselage, an energy management system is arranged on a wing assembly of the fuselage, the energy management system comprises a solar panel, and a power system is driven by solar energy to achieve take-off, landing and flight of the unmanned aerial vehicle. The wing assembly comprises a main wing, the main wing is fixed on the fuselage, the main wing comprises a left side wing and a right side wing, the left side wing and the right side wing are respectively fixed with a fuselage tail pipe of the fuselage through plug pin assemblies and are symmetrically distributed on two sides of the fuselage, and the solar panel is made of a semi-flexible monocrystalline silicon material. And uniformly spreading on the upper surfaces of the left wing and the right wing. According to the multipurpose civil unmanned aerial vehicle based on solar power supply and the control method, the cruising ability is improved through continuous solar power supply, and operation requirements of various civil scenes are met.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a multi-purpose civilian UAV powered by solar energy and a control method thereof. Background Art

[0002] Drone applications are becoming increasingly widespread. For example, environmental protection departments need to regularly monitor rivers and forests around cities. However, traditional fuel-powered drones have short flight times and pollute the environment, while battery-powered drones require frequent charging, making them difficult to operate for extended periods. In agriculture, farmers use drones for pesticide spraying and crop growth monitoring, but the flight time of existing drones often limits the area they can cover at any one time. Emergency communications in remote areas or after natural disasters require drones to remain in the air for extended periods to establish temporary communication relays, but energy supply issues for traditional drones pose a major bottleneck.

[0003] In addition, in the field of short-distance logistics and distribution, for the delivery of small packages within a range of 3-5 kilometers, existing drones need multiple round trips for charging due to insufficient battery life, which is inefficient. Summary of the Invention

[0004] In response to the shortcomings of the existing technology, the present invention provides a multi-purpose civilian UAV and a control method based on solar power supply, which improves the endurance through continuous solar power supply and adapts to the operational needs of various civilian scenarios.

[0005] A solar-powered multi-purpose civilian UAV comprises a fuselage, a wing assembly of which is provided with an energy management system. The energy management system comprises solar panels, and a power system driven by solar energy is used to achieve take-off, landing and flight of the UAV.

[0006] The fuselage includes a fuselage tail pipe, which is a carbon fiber tube.

[0007] The wing assembly includes a main wing, which is fixed to the fuselage. The root rib connecting the main wing and the fuselage is an airfoil-shaped part carved from carbon fiber to increase strength.

[0008] The main wing comprises a left wing and a right wing, which are respectively fixed to the fuselage tail pipe of the fuselage through a latch assembly and symmetrically distributed on both sides of the fuselage. Kevlar fiber is wrapped at the latch connection.

[0009] The main wing adopts a double-beam structure, in which each beam comprises an upper and lower layer of carbon fiber sheets, with PMI foam sandwiched between the two layers of carbon fiber sheets; at the same time, balsa wood strips are provided between the upper and lower layers of carbon fiber sheets as support.

[0010] Ailerons are arranged on the outside of the main wing, the right aileron is arranged on the outside of the right wing, and the left aileron is arranged on the outside of the left wing; the root rib connecting the left wing and the left aileron is an airfoil-shaped part carved from carbon fiber, and the root rib connecting the right wing and the right aileron is an airfoil-shaped part carved from carbon fiber; the right aileron and the left aileron have elliptical wingtips, which are installed at the end of the main wing to reduce wingtip vortices.

[0011] The tail assembly installed at the tail end of the fuselage is connected to the fuselage through a connecting box, and includes a vertical tail, vertical tail rudders and a horizontal tail; the horizontal tail is horizontally installed below the tail of the fuselage tail pipe, and the vertical tail is vertically installed above the tail of the fuselage, and works together with the horizontal tail to ensure the flight stability and maneuverability of the UAV; the vertical tail rudders are arranged at the rear of the vertical tail.

[0012] The power system includes a trolley, a motor, a servo, and a propeller. The motor is fixed to the front end of the fuselage, and the propeller is installed at the output end of the motor. The servo includes four servos, which are respectively connected to the ailerons, the vertical tail control surface, and the horizontal tail to adjust the flight attitude.

[0013] The taxiing trolley adopts an integrated structure, including a frame built with carbon fiber, and Kevlar and resin are used to reinforce the joints; running wheels are provided at the bottom of the frame, and the tires of the running wheels adopt a structure of balsa wood sandwiched between double-sided carbon plates; the top of the taxiing trolley is provided with a trolley wing top pad for supporting the wing assembly; the top of the taxiing trolley is also provided with a fuselage and main wing connector and a fuselage and trolley connector for connection with the fuselage.

[0014] The solar panels are made of semi-flexible single crystal silicon and are evenly spread on the upper surface of the main wing.

[0015] It also includes a control system, including a receiver and a remote control. The power system and energy management system are electrically connected to the control system respectively. The receiver receives the command signal from the remote control and takes corresponding actions according to the signal to realize the take-off and landing, autonomous flight and operation of the UAV.

[0016] A control method for the solar-powered multi-purpose civilian drone includes the following steps:

[0017] S1: Pre-flight preparation and site selection:

[0018] S1.1: Choose a flat and open area;

[0019] S1.2: Check weather conditions;

[0020] S1.3: Check the status of each component of the drone:

[0021] S2: UAV assembly and debugging;

[0022] S2.1: Connect the wing assembly to the fuselage, ensuring there is no relative shaking between the wing assembly and the fuselage:

[0023] S2.2: Install the horizontal and vertical stabilizers, and adjust the horizontal and vertical stabilizers to their designed angles.

[0024] S2.3: Unfold the solar panels and check that the panel surface is in contact with the wing assembly surface, ensuring there are no wrinkles or warping.

[0025] S2.4: Manually test the control system: Test the remote controller to see if the left and right ailerons, vertical stabilizer rudders, and horizontal stabilizer are deflected, and whether the deflection angles are as expected.

[0026] S3: System check;

[0027] S4: Place the drone and start the power system:

[0028] S5: take-off operation;

[0029] S6: Air flight control;

[0030] S7: Landing preparation and operations;

[0031] S8: Post-flight cleanup.

[0032] By means of the above technical solution, the present invention has at least the following beneficial effects:

[0033] The present invention provides a multi-purpose civilian UAV powered by solar energy and a control method. By optimizing the aerodynamic layout through a high lift-to-drag ratio airfoil and a large aspect ratio wing, and by using a carbon fiber fuselage and a lightweight composite wing structure, combined with an efficient solar power system, clean energy flight is achieved. This can meet the needs of long-term low-altitude flight, break away from the endurance limitations of traditional aircraft, and achieve the goals of improving practicality and reducing usage costs.

[0034] The present invention belongs to a portable solar-powered UAV, which combines efficient aerodynamic layout with solar power technology to achieve long-term autonomous flight of the UAV. It is suitable for daily aerial photography, environmental monitoring in daily life, short-distance logistics distribution, agricultural plant protection, emergency communications and other scenarios.

[0035] The invention has reasonable design, is easy to implement and has good practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 A schematic diagram of a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0037] Figure 2A top view of a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0038] Figure 3 A side view of a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0039] Figure 4 A front view of a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0040] Figure 5 A schematic diagram of a trolley in a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0041] Figure 6 A front view of a trolley in a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0042] Figure 7 A left side view of a trolley in a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0043] Figure 8 A top view of a trolley in a solar-powered multi-purpose civilian drone provided by an embodiment of the present invention;

[0044] In the picture:

[0045] 1-trolley wing top pad, 2-fuselage and main wing connection, 3-trolley rear wheel, 4-trolley front wheel, 5-fuselage and trolley connection, 6-right wing, 7-solar panel, 8-right aileron, 9-fuselage tail pipe, 10-vertical tail control surface, 11-horizontal tail, 12-vertical tail, 13-left aileron, 14-left wing, 15-motor frame, 16-motor, 17-propeller. DETAILED DESCRIPTION

[0046] In order to better explain the present invention and facilitate understanding, the technical solutions and effects of the present invention are described in detail below with reference to the accompanying drawings through specific implementation methods.

[0047] like Figures 1 to 8 As shown, a multi-purpose civilian UAV powered by solar energy includes a fuselage, wing assemblies, tail assemblies, a power system, and an energy management system 7.

[0048] The fuselage is the core load-bearing component of the drone, and the wing assembly, tail assembly, power system, energy management system, and control system are each mounted on this fuselage structure. The wing and tail assemblies form a complete aerodynamic layout, providing lift and flight stability for the drone; the power system provides flight propulsion; the energy management system provides electrical energy for the entire drone's operation; and the control system coordinates the coordinated operation of various components.

[0049] In this embodiment, the total length of the fuselage is 1500mm to meet the UAV's center of gravity balance and operational stability requirements. The fuselage includes a tail pipe 9 with an outer diameter of 20mm and an inner diameter of 19mm. The tail pipe 9 is a carbon fiber tube, which reduces manufacturing workload while ensuring the fuselage's structural strength and torsional resistance.

[0050] The wing assembly includes a main wing, which is fixed to the fuselage tail pipe 9 of the fuselage. The main wing adopts a large wingspan design with a total wingspan of 3.895m and an aspect ratio of 14.62 to provide a larger laying area for the solar panels 7 and provide greater power for the flight of the drone.

[0051] Furthermore, the main wing comprises a left wing 14 and a right wing 6, which are secured to the fuselage tail tube 9 via a latch assembly. The latch connection is wrapped with Kevlar fiber to prevent structural instability and damage to the wings when subjected to high torque. In this embodiment, the latch assembly is made of carbon tubes. The left wing 14 and the right wing 6 are symmetrically located on either side of the fuselage tail tube 9. The main wing utilizes a double-beam structure, offering enhanced torsional resistance and lightweight advantages. Each beam in the double-beam structure comprises two layers of carbon fiber sheets, specifically 0.6mm thick, with PMI foam sandwiched between them. Furthermore, a 5mm x 5mm balsa wood strip is placed between the two layers to provide support and enhance torsional resistance.

[0052] Ailerons are provided on the outside of the main wings. Specifically, a right aileron 8 is provided on the outside of the right wing 6 via a latch assembly, and a left aileron 13 is provided on the outside of the left wing 14 via a latch assembly. The right aileron 8 and the left aileron 13 have elliptical wingtips mounted at the ends of the main wings. This design reduces wingtip vortices, improves gliding performance, and increases the area covered by the solar panels 7 to increase power.

[0053] The tail assembly is mounted at the tail end of the fuselage tail tube 9 and connected to the fuselage via a connection box. It includes a vertical tail 12, vertical tail control surfaces 10, and a horizontal tail 11. The horizontal tail 11 is a fully movable horizontal tail, mounted horizontally below the tail of the fuselage tail tube 9 and used to control the pitch attitude of the UAV. The vertical tail 12 is mounted vertically above the tail of the fuselage, and the vertical tail control surfaces 10 are located behind the vertical tail 12 to control the UAV's heading. The vertical tail 12 and the horizontal tail 11 work together to ensure the UAV's flight stability and maneuverability.

[0054] The root ribs connecting the main wing and the fuselage, the left wing 14 and the left aileron 13, and the right wing 6 and the right aileron 8 are made of airfoil-shaped parts carved from carbon fiber to increase strength; the connecting box used to connect the tail assembly to the fuselage is made of paulownia wood and glass fiber composite materials. The original carbon fiber parts are replaced with paulownia wood and glass fiber composite materials, reducing weight by more than 40%.

[0055] The power system includes a trolley, a motor 16, a servo, and a propeller 17. The motor 16 is secured to the front end of the fuselage tail tube 9 via a motor mount 15, providing power for the drone's flight. The propeller 17 is mounted at the output end of the motor 16. In this embodiment, the motor 16 uses a MAD4006 brushless motor, which is lighter, has greater pulling force, and is more efficient. The propeller 17 is 18 inches in size. The trolley is used to support the fuselage and assist in the drone's takeoff. There are four servos. The first servo is mounted at the intersection of the two beams of the right wing 6 and the tip rib behind it to drive the rotation of the right aileron 8. The second servo is mounted at the intersection of the two beams of the left wing 14 and the tip rib behind it to drive the rotation of the left aileron 13. The third servo is mounted at the center of the rear rear wall of the vertical tail 12 to drive the rotation of the vertical tail control surface 10. The fourth servo is mounted at the intersection of the rear rear wall of the vertical tail 11 and the root rib behind it to drive the rotation of the horizontal stabilizer 11. The four servos are connected to the controlled components (right aileron 8, left aileron 13, vertical tail control surface 10, horizontal tail 11) through a connecting rod mechanism to control the rotation of the controlled components and adjust the flight attitude.

[0056] In this embodiment, the trolley adopts a one-piece structure, including a carbon fiber frame with Kevlar and resin reinforcement at the joints. The frame is equipped with running wheels at the bottom, including front wheels 4 and rear wheels 3. The tires are constructed of double-sided carbon fiber plates sandwiched with balsa wood, weighing a total of 200g. The top of the trolley is equipped with a wing top pad 1 to support the wing assembly. Furthermore, the top of the trolley is equipped with a fuselage-to-main wing connector 2 for connecting to the front of the fuselage tail tube 9, specifically a snap-fit ​​connection. A fuselage-to-trolley connector 5 is also provided for connecting to the middle of the fuselage tail tube 9, specifically a snap-fit ​​connection, ensuring a secure connection with the fuselage structure.

[0057] The solar-powered multi-purpose civilian drone also includes a control system, consisting of a receiver and a remote control. The receiver is electrically connected to the motor 16 and the servo via DuPont cables. The power system and energy management system are each electrically connected to the control system. The receiver receives command signals from the remote control and responds accordingly, adjusting the speed of the motor 16 and the servo, enabling the drone's takeoff and landing, maneuvering, cruising, and operational functions. The control system coordinates with the energy management system to coordinate the flow of electrical energy, precisely supplying power to the power system and ensuring stable operation of all components.

[0058] The energy management system includes the solar panel 7, which is electrically connected to the motor and receiver via an electrical controller. The solar panel 7 is made of semi-flexible monocrystalline silicon and has the advantages of high power generation efficiency, good flexibility, strong adaptability, and high damage resistance. In this embodiment, the size of a single solar panel 7 is 125mm x 125mm, and it is evenly laid flat on the upper surface of the left wing 14 and the right wing 6. A total of 44 solar panels are laid and connected in series using soldering. The voltage of a single solar panel 7 is 0.6V, and when all are connected in series, the output voltage is 26.4V, which is directly supplied to the motor 16. This uses solar energy to power the drone and reduce carbon emissions.

[0059] On the other hand, the present invention provides a control method for a multi-purpose civilian UAV based on solar power supply, which is applicable to the multi-purpose civilian UAV based on solar power supply, and specifically includes the following steps:

[0060] S1: Pre-flight preparation and site selection.

[0061] S1.1: Choose a flat, open area with no tall obstacles (such as trees or buildings) around it. Avoid crowded areas and dangerous facilities such as high-voltage power lines.

[0062] S1.2: Check weather conditions. Fly only in an environment with sufficient sunlight (recommended illumination of at least 50,000 LUX) and wind speeds below level 3. Avoid operations in rainy, foggy, or windy weather.

[0063] S1.3: Check the status of each component of the drone:

[0064] S1.3.1: Main structure: Confirm that the fuselage tail tube 9 is not bent or broken, the latch assembly between the wing assembly and the fuselage tail tube 9 is secure, and the Kevlar fiber wrapping is not loose;

[0065] S1.3.2: Aerodynamic structure: The main wing, horizontal stabilizer 11, and vertical stabilizer 12 have no surface damage, and the ailerons are flexible and not stuck;

[0066] S1.3.3: Power system: The solar panel surface is clean and unobstructed, the wires are securely connected, the motor 16 and propeller 17 are tightly installed, and the propeller 17 is free of cracks;

[0067] S1.3.4: Control system: The left aileron 13, right aileron 8, all-moving horizontal stabilizer and vertical stabilizer control surfaces 10 deflect smoothly, and the linkage mechanism is not loose.

[0068] S2: UAV assembly and debugging.

[0069] S2.1: Connect the wing assembly to the fuselage through the latch assembly, ensuring that there is no relative shaking between the wing assembly and the fuselage.

[0070] S2.2: Install the horizontal stabilizer 11 and the vertical stabilizer 12. Connect the horizontal stabilizer 11 and the vertical stabilizer 12 to the tail of the fuselage through the connecting box. Adjust the horizontality of the horizontal stabilizer 11 and the verticality of the vertical stabilizer 12 so that they meet the designed angles.

[0071] S2.3: Unfold the solar panels and check whether the panel surface is in contact with the wing assembly surface. Ensure there are no wrinkles or warping to avoid affecting aerodynamic performance.

[0072] S2.4: Manually test the control system: Test the remote control by gently moving the remote control joystick to observe whether the left aileron 13, right aileron 8, vertical tail control surface 10, and all-movable horizontal stabilizer deflect and whether the deflection angle is as expected.

[0073] S3: System check.

[0074] Check the connection of the control system, the condition of the connectors at the connection of the wing assembly, the connection contact surface between the wing assembly and the fuselage, the ailerons and the servo.

[0075] In terms of the power system, pay attention to the fastening of the propeller 17 and the nuts, the fixing screws and motor wires of the motor 16, and the condition of the electric control connection wires.

[0076] The control system includes the fixation and connection of the receiver, as well as the inspection of the DuPont pins and remote control.

[0077] Regarding the center of gravity, make sure it is near the wing spar.

[0078] During the power-on inspection, the center position and response of the control surfaces, the direction of the propeller 17, and the tension and calibration of the motor 16 should be confirmed. The appearance and voltage of the battery should be checked.

[0079] In terms of appearance, check the skin and membrane of the fuselage, wing components, aileron and rudder surface membranes, and elevator surface membranes.

[0080] In terms of takeoff environment, the runway must be flat and free of debris, pedestrians and vehicles. The airspace must be cleared 1 minute before takeoff. The wind speed must be below level 5 and takeoff and landing must be against the wind.

[0081] Only after the inspection is completed can you fly.

[0082] S4: Place the drone and start the power system.

[0083] Place the drone body onto the trolley, then place the drone at the take-off point on the site, with the fuselage axis aligned with the preset take-off direction; wait for 3-5 minutes to allow the solar panels to fully receive sunlight and accumulate electrical energy; turn on the power system switch, and the motor 16 will start running at a low speed. Observe whether the propeller 17 is rotating in the correct direction (clockwise when viewed from the nose of the aircraft). If the direction is incorrect, turn off the switch and adjust the wiring of the motor 16.

[0084] S5: Take-off operation.

[0085] Slowly push the remote control joystick to increase the throttle, the speed of the motor 16 gradually increases, and the propeller 17 generates a forward pulling force; the aircraft begins to glide along the ground, and keep the fuselage stable during the glide. If yaw occurs, use the remote control joystick to fine-tune the vertical tail control surface 10 to correct the direction; when the glide speed reaches the critical takeoff speed, gently pull the joystick backward to make the fuselage tilt up when the angle with the ground is about 1.5 degrees. The wing assembly generates sufficient lift, and the aircraft lifts off the ground.

[0086] S6: Air flight control.

[0087] After the aircraft takes off, keep the throttle steady and gradually adjust the power to cruise power (approximately 60%-70% of maximum output power) to achieve a smooth climb. When turning, gently push the remote control joystick in the target direction to slowly tilt the aircraft in a turn by deflecting the ailerons. At the same time, increase the throttle appropriately to compensate for altitude loss.

[0088] If the power drops due to changes in light, you need to reduce the flight speed and use the gliding performance of the wings to maintain altitude. Adjust the throttle after the light is restored.

[0089] During flight, the aircraft's attitude must be continuously monitored and the pitch angle must be controlled using the 11 control surfaces of the horizontal tail to ensure smooth flight and avoid stalling due to a large angle of attack.

[0090] S7: Landing preparation and operations.

[0091] When the mission is nearing completion or a landing is required, plan the landing route in advance, ensuring that it is clear of obstacles and personnel. Gradually approach the landing point. Slowly lower the throttle and reduce power output until the aircraft begins a steady descent, maintaining a descent rate between 0.5 and 1 meter per second. Once the aircraft is 1 meter above the ground, maintain a level surface and increase the throttle by 10% to reduce the descent rate. After the aircraft touches the ground, slowly return the throttle to its minimum setting. This will cause the motor 16 to stop, and the aircraft will glide for a short distance before stopping.

[0092] S8: Post-flight cleanup.

[0093] Turn off the power system and disconnect the solar panels from the motor 16. Remove the wing assembly and organize the aircraft components to avoid damage. Clean the solar panel surface to remove dust and stains to ensure efficient photoelectric conversion before next use. Inspect all components for wear and damage. If you notice cracks in the propeller 17 or slight deformation of the wing assembly, repair or replace them immediately before your next flight.

Claims

1. A solar-powered multi-purpose civilian drone, characterized by: The drone comprises a fuselage, and an energy management system is provided on the wing assembly of the fuselage. The energy management system comprises solar panels, and a power system is driven by solar energy to realize the take-off, landing and flight of the drone.

2. The solar-powered multi-purpose civilian UAV according to claim 1, characterized in that: The fuselage includes a fuselage tail pipe, which is a carbon fiber tube.

3. The solar-powered multi-purpose civilian UAV according to claim 1, characterized in that: The wing assembly includes a main wing, which is fixed to the fuselage. The root rib connecting the main wing and the fuselage is an airfoil-shaped part carved from carbon fiber to increase strength. The main wing comprises a left wing and a right wing, which are respectively fixed to the fuselage tail pipe of the fuselage through a latch assembly and symmetrically distributed on both sides of the fuselage. Kevlar fiber is wrapped at the latch connection.

4. The solar-powered multi-purpose civilian UAV according to claim 3, characterized in that: The main wing adopts a double-beam structure, in which each beam comprises an upper and lower layer of carbon fiber sheets, with PMI foam sandwiched between the two layers of carbon fiber sheets; at the same time, balsa wood strips are provided between the upper and lower layers of carbon fiber sheets as support.

5. The solar-powered multi-purpose civilian UAV according to claim 3, characterized in that: The outer side of the main wing is provided with an aileron, the outer side of the right wing is provided with a right aileron, and the outer side of the left wing is provided with a left aileron; the root rib connecting the left wing and the left aileron is an airfoil-shaped part carved from carbon fiber, and the root rib connecting the right wing and the right aileron is an airfoil-shaped part carved from carbon fiber; The right aileron and the left aileron have elliptical wingtips, which are installed at the ends of the main wings to reduce wingtip vortices.

6. The solar-powered multi-purpose civilian UAV according to claim 5, characterized in that: The tail assembly installed at the tail end of the fuselage is connected to the fuselage through a connecting box, and includes a vertical tail, vertical tail rudders and a horizontal tail; the horizontal tail is horizontally installed below the tail of the fuselage tail pipe, and the vertical tail is vertically installed above the tail of the fuselage, and works together with the horizontal tail to ensure the flight stability and maneuverability of the UAV; the vertical tail rudders are arranged at the rear of the vertical tail.

7. The solar-powered multi-purpose civilian UAV according to claim 6, characterized in that: The power system includes a trolley, a motor, a servo, and a propeller. The motor is fixed to the front end of the fuselage, and the propeller is installed at the output end of the motor. The servo includes four servos, which are respectively connected to the ailerons, the vertical tail control surface, and the horizontal tail to adjust the flight attitude. The taxiing trolley adopts an integrated structure, including a frame built with carbon fiber, and Kevlar and resin are used to reinforce the joints; running wheels are provided at the bottom of the frame, and the tires of the running wheels adopt a structure of balsa wood sandwiched between double-sided carbon plates; the top of the taxiing trolley is provided with a trolley wing top pad for supporting the wing assembly; the top of the taxiing trolley is also provided with a fuselage and main wing connector and a fuselage and trolley connector for connection with the fuselage.

8. The solar-powered multi-purpose civilian UAV according to claim 3, characterized in that: The solar panels are made of semi-flexible single crystal silicon and are evenly spread on the upper surface of the main wing.

9. The solar-powered multi-purpose civilian UAV according to claim 1, characterized in that: It also includes a control system, including a receiver and a remote control. The power system and energy management system are electrically connected to the control system respectively. The receiver receives the command signal from the remote control and takes corresponding actions according to the signal to realize the take-off and landing, autonomous flight and operation of the UAV.

10. A control method for a multi-purpose civilian UAV based on solar power supply according to claim 9, characterized in that: The following steps are involved: S1: Pre-flight preparation and site selection: S1.1: Choose a flat and open area; S1.2: Check weather conditions; S1.3: Check the status of each component of the drone: S2: UAV assembly and debugging; S2.1: Connect the wing assembly to the fuselage, ensuring there is no relative shaking between the wing assembly and the fuselage: S2.2: Install the horizontal and vertical stabilizers, and adjust the horizontal and vertical stabilizers to their designed angles. S2.3: Unfold the solar panels and check that the panel surface is in contact with the wing assembly surface, ensuring there are no wrinkles or warping. S2.4: Manually test the control system: Test the remote controller to see if the left and right ailerons, vertical stabilizer rudders, and horizontal stabilizer are deflected, and whether the deflection angles are as expected. S3: System check; S4: Place the drone and start the power system: S5: take-off operation; S6: Air flight control; S7: Landing preparation and operations; S8: Post-flight cleanup.

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