A solar-powered multi-purpose civilian drone

Abstract

The utility model relates to a multi -purpose civilian unmanned plane based on solar power supply belongs to unmanned plane technical field, including fuselage, the wing assembly of fuselage is provided with energy management system, and energy management system includes solar panel, drives power system through solar energy, to realize the take -off and landing and flight of unmanned plane. Wing assembly includes main wing, and the main wing is fixed on the fuselage of fuselage, and the main wing includes left wing and right wing, is fixed with the fuselage tail pipe of fuselage respectively through the bolt assembly, is symmetrically distributed in the both sides of fuselage, and solar panel adopts semi -flexible monocrystalline silicon material, and is evenly laid on the left wing and right wing upper surface. The multi -purpose civilian unmanned plane based on solar power supply and control method provided by the utility model improve the endurance ability through the continuous power supply of solar energy, and adapt to the operation demand of a variety of civilian scene.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and in particular relates to a multi-purpose civilian UAV powered by solar energy. Background Technology

[0002] The applications of drones are becoming increasingly widespread. For example, environmental protection departments need to regularly monitor rivers and forests around cities, but traditional fuel-powered drones have short flight times and pollute the environment, while battery-powered drones require frequent charging and cannot meet the needs of long-term operations. In agricultural production, farmers use drones for pesticide spraying and crop growth monitoring, but the flight time of existing drones often limits the area covered in a single operation. In emergency communications in remote areas or after natural disasters, drones are needed to stay airborne for extended periods to establish temporary communication relays, and the energy supply problem of traditional drones has become a major bottleneck.

[0003] In addition, in the field of short-distance logistics delivery, for the delivery of small packages within a range of 3-5 kilometers, existing drones have to make multiple trips to recharge due to insufficient battery life, resulting in low efficiency. Utility Model Content

[0004] In view of the shortcomings of existing technologies, this utility model provides a multi-purpose civilian drone based on solar power, which improves the endurance through continuous solar power supply and is suitable for the operational needs of various civilian scenarios.

[0005] A multi-purpose civilian unmanned aerial vehicle (UAV) powered by solar energy includes a fuselage. An energy management system is installed on the wing assembly of the fuselage. The energy management system includes solar panels and drives a power system through solar energy to enable the UAV to take off, land, and fly.

[0006] The fuselage includes a tailpipe, 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 to the fuselage is made of airfoil-shaped parts carved from carbon fiber to increase strength.

[0008] The main wing includes a left wing and a right wing, which are respectively fixed to the fuselage tailpipe of the fuselage by a pin assembly, and are symmetrically distributed on both sides of the fuselage. Kevlar fiber is wrapped at the pin connection.

[0009] The main wing adopts a double-beam structure. Each beam in the double-beam structure contains two layers of carbon fiber sheets, with PMI foam sandwiched between the two layers of carbon fiber sheets. At the same time, balsa wood strips are set between the upper and lower layers of carbon fiber sheets as support.

[0010] The main wing has an aileron on its outer side, the right wing has a right aileron on its outer side, and the left wing has a left aileron on its outer side. The root rib connecting the left wing and the left aileron is made of an airfoil-shaped part carved from carbon fiber, and the root rib connecting the right wing and the right aileron is also made of an airfoil-shaped part carved from carbon fiber. The right aileron and the left aileron have elliptical wingtips and are installed at the ends 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 via a connecting box, including a vertical tail, a vertical tail control surface, and a horizontal tail; the horizontal tail is installed horizontally below the tail of the fuselage tail tube, and the vertical tail is installed vertically above the tail of the fuselage, working together with the horizontal tail to ensure the flight stability and maneuverability of the UAV; the vertical tail control surface is located at the rear of the vertical tail.

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

[0013] The taxiing car adopts a one-piece structure, including a frame built with carbon fiber and reinforced with Kevlar and resin at the joints; the bottom of the frame is equipped with wheels, and the tires of the wheels are made of carbon fiber plates with balsa wood sandwiched inside on both sides; the top of the taxiing car is equipped with a wing pad to support the wing assembly; the top of the taxiing car is also equipped with fuselage-to-main wing connectors and fuselage-to-cart connectors for connecting with the fuselage.

[0014] The solar panel is made of semi-flexible monocrystalline silicon and is evenly laid on the upper surface of the main wing.

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

[0016] By employing the above technical solution, this utility model application has at least the following beneficial effects:

[0017] This invention provides a multi-purpose civilian unmanned aerial vehicle (UAV) and control method based on solar power. By optimizing the aerodynamic layout with a high lift-to-drag ratio airfoil and a large aspect ratio wing, and through a lightweight structure design with a carbon fiber fuselage and composite wings, combined with a high-efficiency solar power system, it can achieve clean energy flight, meet the needs of long-term low-altitude flight, get rid of the endurance limitations of traditional aircraft, and achieve the purpose of improving practicality and reducing operating costs.

[0018] This utility model belongs to the portable solar-powered type of drone, which combines efficient aerodynamic layout with solar power technology to achieve long-term autonomous flight of the drone. It is suitable for various scenarios such as daily aerial photography, environmental monitoring in daily life, short-distance logistics delivery, agricultural plant protection, and emergency communication.

[0019] This utility model is reasonably designed, easy to implement, and has great practical value. Attached Figure Description

[0020] Figure 1 A schematic diagram of a solar-powered multi-purpose civilian unmanned aerial vehicle (UAV) provided for an embodiment of this utility model;

[0021] Figure 2 A top view of a solar-powered multi-purpose civilian unmanned aerial vehicle (UAV) provided for an embodiment of this utility model;

[0022] Figure 3 A side view of a solar-powered multi-purpose civilian unmanned aerial vehicle (UAV) provided for an embodiment of this utility model;

[0023] Figure 4 A front view of a solar-powered multi-purpose civilian unmanned aerial vehicle provided for an embodiment of this utility model;

[0024] Figure 5 A schematic diagram of the glider in a solar-powered multi-purpose civilian drone provided for an embodiment of this utility model;

[0025] Figure 6 A front view of the glider in a solar-powered multi-purpose civilian unmanned aerial vehicle provided in an embodiment of this utility model;

[0026] Figure 7 A left view of the glider in a solar-powered multi-purpose civilian drone provided for an embodiment of this utility model;

[0027] Figure 8 A top view of the glider in a solar-powered multi-purpose civilian unmanned aerial vehicle provided in an embodiment of this utility model;

[0028] In the picture:

[0029] 1-Trolley wing top pad, 2-Fuselage and main wing connector, 3-Trolley rear wheel, 4-Trolley front wheel, 5-Fuselage and trolley connector, 6-Right wing, 7-Solar panel, 8-Right aileron, 9-Fuselage tailpipe, 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 Implementation

[0030] To better explain and facilitate understanding of this utility model, the technical solution and effects of this utility model will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0031] like Figures 1-8 As shown, a multi-purpose civilian unmanned aerial vehicle (UAV) powered by solar energy is disclosed. The UAV includes a fuselage, wing assembly, tail assembly, power system, and energy management system.

[0032] The fuselage is the core load-bearing component of the UAV, with the wing assembly, tail assembly, power system, energy management system, and control system respectively mounted on the fuselage structure. The wing assembly and tail assembly form a complete aerodynamic layout, providing lift and flight stability for the UAV; the power system provides flight propulsion for the UAV; the energy management system provides electrical energy for the entire operation; and the control system coordinates the collaborative work of all components.

[0033] In this embodiment, the total length of the fuselage is 1500mm to meet the requirements for center of gravity balance and operational stability of the UAV. The fuselage includes a tail tube 9 with an outer diameter of 20mm and an inner diameter of 19mm. The tail tube 9 is made of carbon fiber to reduce manufacturing workload while ensuring the structural strength and torsional resistance of the fuselage.

[0034] The wing assembly includes a main wing, which is fixed to the fuselage tailpipe 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 area for the solar panels 7 and provide greater power for the drone's flight.

[0035] Furthermore, the main wing includes a left wing 14 and a right wing 6, which are fixed to the fuselage tailpipe 9 of the fuselage via a pin assembly. Kevlar fibers are wrapped around the pin connections to prevent structural instability and damage under high torque. In this embodiment, the pin assembly is made of carbon fiber. The left wing 14 and right wing 6 are symmetrically distributed on both sides of the fuselage tailpipe 9. The main wing employs a double-beam structure, offering superior torsional resistance and lightweight advantages. Each beam in the double-beam structure comprises two layers of carbon fiber sheets, specifically 0.6mm carbon fiber sheets, with PMI foam sandwiched between the two layers. Additionally, 5mm × 5mm balsa wood strips are placed between the two layers of carbon fiber sheets as support to enhance torsional resistance.

[0036] The outer side of the main wing is provided with ailerons. Specifically, the outer side of the right wing 6 is provided with a right aileron 8 via a pin assembly, and the outer side of the left wing 14 is provided with a left aileron 13 via a pin assembly. The right aileron 8 and the left aileron 13 have elliptical wingtips and are installed at the tip of the main wing. This design reduces wingtip vortices, improves gliding performance, and increases the coverage area of ​​the solar panel 7 to increase power.

[0037] The tail assembly is mounted at the tail end of the fuselage tailpipe 9 and connected to the fuselage via a connecting box. It includes a vertical stabilizer 12, a vertical stabilizer control surface 10, and a horizontal stabilizer 11. The horizontal stabilizer 11 is an all-moving horizontal stabilizer, horizontally mounted below the tail of the fuselage tailpipe 9, used to control the pitch attitude of the UAV. The vertical stabilizer 12 is vertically mounted above the tail of the fuselage, and the vertical stabilizer control surface 10 is located at the rear of the vertical stabilizer 12, used to control the yaw of the UAV. The vertical stabilizer 12 and the horizontal stabilizer 11 work together to ensure the flight stability and maneuverability of the UAV.

[0038] The root ribs connecting the main wing to the fuselage, the left wing 14 to the left aileron 13, and the right wing 6 to the right aileron 8 use airfoil-shaped parts carved from carbon fiber to increase strength; the connecting box for connecting the tail assembly to the fuselage is made of paulownia wood and fiberglass composite material, replacing the original carbon fiber parts with paulownia wood and fiberglass composite material, reducing weight by more than 40%.

[0039] The power system includes a trolley, a motor 16, servos, and a propeller 17. The motor 16 is fixed to the front end of the tailpipe 9 of the fuselage via a motor bracket 15, providing power for the drone's flight. The propeller 17 is installed at the output end of the motor 16. In this embodiment, the motor 16 is a lighter, stronger, and more efficient MAD4006 brushless motor, and the propeller 17 is 18 inches in size. The trolley is used to mount the fuselage and assist the drone in takeoff. The servos include four: the first servo is installed behind the two spars of the right wing 6 at the intersection with the tip rib to drive the rotation of the right aileron 8; the second servo is installed behind the two spars of the left wing 14 at the intersection with the tip rib to drive the rotation of the left aileron 13; the third servo is installed in the middle of the rear of the vertical tail aft wall of the vertical tail 12 to drive the rotation of the vertical tail control surface 10; and the fourth servo is installed behind the rear wall of the vertical tail at the intersection with the root rib to drive the rotation of the horizontal tail 11. The four servos are connected to the controlled components (right aileron 8, left aileron 13, vertical tail control surface 10, and horizontal tail 11) via a linkage mechanism to control the rotation of the controlled components and adjust the flight attitude.

[0040] In this embodiment, the trolley adopts an integrated structure, including a frame constructed of carbon fiber, reinforced with Kevlar and resin at the joints. The bottom of the frame is equipped with wheels, including front wheels 4 and rear wheels 3. The tires of the wheels have a double-sided carbon fiber plate structure with balsa wood sandwiched inside, with a total weight 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 also features a fuselage-to-wing connector 2 for connecting to the front of the fuselage tailpipe 9 (specifically, a snap-fit ​​connection); and a fuselage-to-trolley connector 5 for connecting to the middle of the fuselage tailpipe 9 (specifically, a snap-fit ​​connection), ensuring a stable connection with the fuselage structure.

[0041] The solar-powered multi-purpose civilian drone also includes a control system, comprising a receiver and a remote controller. The receiver is electrically connected to motor 16 and servo motors via DuPont wires. The power system and energy management system are electrically connected to the control system. The receiver receives command signals from the remote controller and performs corresponding actions, including adjusting the speed of motor 16 and the movement of the servo motors, to achieve the drone's takeoff, landing, yaw, cruise, and operational functions. The control system works in conjunction with the energy management system to allocate power flow, precisely supplying electricity to the power system and ensuring stable operation of all components.

[0042] The energy management system includes the solar panel 7, which is electrically connected to the motor and receiver via an electronic speed controller (ESC). The solar panel 7 is made of semi-flexible monocrystalline silicon, offering advantages such as high power generation efficiency, good flexibility, strong adaptability, and high resistance to damage. In this embodiment, each solar panel 7 measures 125mm × 125mm and is evenly laid on the upper surfaces of the left wing 14 and right wing 6, with a total of 44 panels connected in series by solder. Each solar panel 7 has a voltage of 0.6V, and the combined output voltage after series connection is 26.4V, directly supplying power to the motor 16. This utilizes solar energy to power the drone, reducing carbon emissions.

[0043] On the other hand, this utility model proposes a control method for a multi-purpose civilian drone powered by solar energy, applicable to the aforementioned multi-purpose civilian drone powered by solar energy, specifically including the following steps:

[0044] S1: Pre-flight preparation and site selection.

[0045] S1.1: Choose a flat and open site, ensuring that there are no tall obstacles (such as trees or buildings) around, and avoid densely populated areas and dangerous facilities such as high-voltage power lines.

[0046] S1.2: Check the weather conditions. Flights must be conducted in environments with sufficient sunlight (ideally no less than 50,000 LUX) and wind force less than level 3. Avoid operating in cloudy, rainy, foggy, or windy weather.

[0047] S1.3: Check the status of each component of the drone:

[0048] S1.3.1: Main structure: Confirm that the fuselage tail tube 9 is not bent or broken, the wing assembly and the pin assembly of the fuselage tail tube 9 are secure, and the Kevlar fiber wrapping is not loose.

[0049] S1.3.2: Aerodynamic structure: The surfaces of the main wing, horizontal stabilizer 11, and vertical stabilizer 12 are undamaged, and the ailerons move flexibly without jamming;

[0050] S1.3.3: Power system: The surface of the solar panel is clean and unobstructed, the wire connection is firm, the motor 16 and the propeller 17 are tightly installed, and the propeller 17 has no cracks;

[0051] 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.

[0052] S2: Unmanned Aerial Vehicle (UAV) assembly and debugging.

[0053] S2.1: Connect the wing assembly to the fuselage via a pin assembly to ensure that there is no relative sway between the wing assembly and the fuselage.

[0054] 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 design angle.

[0055] S2.3: Deploy the solar panels and check whether the surface of the panels is in contact with the surface of the wing components, ensuring that there are no wrinkles or warping, so as to avoid affecting aerodynamic performance.

[0056] S2.4: Manual test of the control system: Test the remote control, gently move the remote control joystick, and observe whether the left aileron 13, right aileron 8, vertical tail control surface 10 and all-moving horizontal stabilizer deflect, and whether the deflection angle meets the expectations.

[0057] S3: System check.

[0058] Check the connections of the control system, the condition of the connectors at the wing assembly joints, the contact surfaces between the wing assembly and the fuselage, and the condition of the ailerons and servos.

[0059] Regarding the power system, attention should be paid to the forward and reverse propellers of propeller 17 and the tightness of the nuts, the fixing screws and motor wires of motor 16, and the condition of the ESC connection wires.

[0060] Regarding the control system, this includes fixing and connecting the receiver, as well as checking the DuPont pins and remote control.

[0061] In terms of center of gravity, ensure that it is near the wing spars.

[0062] During the power connection check, confirm the center point position of the control surface, response, propeller 17 steering, and motor 16 thrust and calibration. The battery needs to be checked for appearance and voltage.

[0063] In terms of appearance, check the condition of the skin coatings on the fuselage, wing components, aileron control surfaces, and elevator surfaces.

[0064] Regarding the takeoff environment, the runway must be flat and free of debris, pedestrians, and vehicles. The airspace must be cleared one minute before takeoff, and the wind force must be below level 5, with takeoff and landing against the wind.

[0065] Flight is permitted only after all checks are completed.

[0066] S4: Place the drone and start the power system.

[0067] Place the drone's fuselage onto the trolley, then place the drone at the takeoff point on the field, aligning the fuselage axis with the preset takeoff direction. Wait 3-5 minutes to allow the solar panels to receive sufficient sunlight and accumulate electrical energy. Turn on the power system switch, and motor 16 will start running at low speed. Observe whether the propeller 17 is rotating in the correct direction (clockwise when viewed from the nose of the drone). If the direction is incorrect, turn off the switch and adjust the wiring of motor 16.

[0068] S5: Takeoff operation.

[0069] Slowly push the remote control stick to increase the throttle, the speed of motor 16 gradually increases, and propeller 17 generates forward thrust; the aircraft begins to taxi along the ground, maintaining stability during taxiing. If yaw occurs, the direction is corrected by finely adjusting the vertical tail control surface 10 through the remote control stick; when the taxiing speed reaches the takeoff critical speed, gently pull the control stick back to make the angle between the fuselage and the ground about 1.5 degrees, and the aircraft pitches up. The wing assembly generates sufficient lift, and the aircraft takes off.

[0070] S6: Airborne Flight Control.

[0071] After the aircraft takes off, maintain a stable throttle and gradually adjust it to cruise power (approximately 60%-70% of maximum output power) to achieve a smooth climb. When turning, gently push the remote control stick in the direction of the target to tilt the aircraft slowly and turn by deflecting the ailerons, while appropriately increasing the throttle to compensate for altitude loss.

[0072] If changes in lighting cause a decrease in power, the flight speed should be reduced, and the gliding performance of the wings should be used to maintain altitude. The throttle should be adjusted again after the lighting returns to normal.

[0073] During flight, the attitude must be continuously observed, and the pitch angle should be controlled through the horizontal stabilizer 11 control surface to ensure stable flight and avoid stall due to high angle of attack.

[0074] S7: Landing preparation and operations.

[0075] When the flight mission is nearing completion or landing is required, plan the landing path in advance, ensuring it is free of obstacles and personnel, and gradually approach the landing point. Slowly reduce the throttle to decrease power output, allowing the aircraft to begin a smooth descent, maintaining a descent rate between 0.5 m / s and 1 m / s. When 1 m above the ground, keep the fuselage level and increase the throttle by 10% to reduce the descent speed. After the aircraft touches the ground, slowly reduce the throttle to minimum, motor 16 will stop operating, and the aircraft will taxi for a short distance before coming to a stop.

[0076] S8: Post-flight preparation.

[0077] Turn off the power system switch and disconnect the solar panels from motor 16; disassemble the wing assembly and sort and store the aircraft components to avoid damage from compression. Clean the surface of the solar panels to remove dust and stains to ensure photoelectric conversion efficiency for the next use. Inspect all components for wear or damage. If cracks are found in propeller 17 or slight deformation of the wing assembly, repair or replace them promptly before the next flight.

Claims

1. A multi-purpose civilian drone powered by solar energy, characterized in that: The device includes a fuselage, and an energy management system is installed on the wing assembly of the fuselage. The energy management system includes solar panels, which drive the power system through solar energy to enable the drone to take off, land, and fly.

2. A multi-purpose civilian drone powered by solar energy according to claim 1, characterized in that: The fuselage includes a tailpipe, which is a carbon fiber tube.

3. The multi-purpose civilian drone powered by solar energy according to claim 1, wherein: The wing assembly includes a main wing, which is fixed to the fuselage. The root rib connecting the main wing to the fuselage is made of airfoil-shaped parts carved from carbon fiber to increase strength. The main wing includes a left wing and a right wing, which are respectively fixed to the fuselage tailpipe of the fuselage by a pin assembly, and are symmetrically distributed on both sides of the fuselage. Kevlar fiber is wrapped at the pin connection.

4. The multi-purpose civilian drone powered by solar energy according to claim 3, characterized in that: The main wing adopts a double-beam structure. Each beam in the double-beam structure contains two layers of carbon fiber sheets, with PMI foam sandwiched between the two layers of carbon fiber sheets. At the same time, balsa wood strips are set between the upper and lower layers of carbon fiber sheets as support.

5. The multi-purpose civilian drone powered by solar energy 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 made of airfoil-shaped parts carved from carbon fiber, and the root rib connecting the right wing and the right aileron is made of airfoil-shaped parts carved from carbon fiber. The right and left ailerons have elliptical wingtips and are installed at the ends of the main wing to reduce wingtip vortices.

6. The multi-purpose civilian drone powered by solar energy according to claim 5, characterized in that: The tail assembly installed at the tail end of the fuselage is connected to the fuselage via a connecting box, including a vertical tail, a vertical tail control surface, and a horizontal tail; the horizontal tail is installed horizontally below the tail of the fuselage tail tube, and the vertical tail is installed vertically above the tail of the fuselage, working together with the horizontal tail to ensure the flight stability and maneuverability of the UAV; the vertical tail control surface is located at the rear of the vertical tail.

7. The multi-purpose civilian drone powered by solar energy according to claim 6, characterized in that: The power system includes a trolley, a motor, servos, and a propeller. The motor is fixed to the front of the fuselage, and the propeller is installed at the output end of the motor. There are four servos, which are connected to the ailerons, vertical tail control surfaces, and horizontal tail respectively to adjust the flight attitude. The taxiing car adopts a one-piece structure, including a frame built with carbon fiber and reinforced with Kevlar and resin at the joints; the bottom of the frame is equipped with wheels, and the tires of the wheels are made of carbon fiber plates with balsa wood sandwiched inside on both sides; the top of the taxiing car is equipped with a wing pad to support the wing assembly; the top of the taxiing car is also equipped with fuselage-to-main wing connectors and fuselage-to-cart connectors for connecting with the fuselage.

8. The multi-purpose civilian drone powered by solar energy of claim 3, wherein: The solar panel is made of semi-flexible monocrystalline silicon and is evenly laid on the upper surface of the main wing.

9. The multi-purpose civilian drone powered by solar energy of claim 1, wherein: It also includes a control system, including a receiver and a remote controller. The power system and energy management system are electrically connected to the control system. The receiver receives command signals from the remote controller and performs corresponding actions based on the signals to realize the take-off and landing, autonomous flight and operation of the UAV.

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