Fixed-wing unmanned aerial vehicle based on flexible perovskite solar cell

Abstract

The utility model discloses a fixed-wing unmanned aerial vehicle based on flexible perovskite solar cells, which adopts a wing body fusion design and comprises an equipment compartment in the middle of a vehicle body and wings on two sides, and a pair of ailerons with rolling and pitching control functions is arranged on the rear edge of the outer section of each wing; a pair of vertical stabilizers are arranged at the tips of the wings so as to enhance the course stability during flight; two flexible perovskite solar cells which accord with the shapes of the wings and are tightly attached to the wings are mounted on the surfaces of the fuselage and the wings, and power is provided for the unmanned aerial vehicle. According to the utility model, the sweepback wing flying wing type layout is adopted, so that the effective lift area of the wings and the laying area of the solar cells are increased while the structural weight is reduced; the battery is laid on the surface of the wing, damage to the battery in the laying process can be reduced, and the installation difficulty is lowered; meanwhile, the flexible perovskite solar cell has the advantages of low cost, good folding and bending performance and the like, so that the flight efficiency of the unmanned aerial vehicle is improved, the effective load is increased, and the endurance is prolonged.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a fixed-wing UAV based on flexible perovskite solar cells. Background Technology

[0002] Fixed-wing drones, with their superior aerodynamic efficiency and endurance, play a crucial role in long-endurance missions such as remote sensing mapping, border patrol, and disaster monitoring. However, traditional fixed-wing drones rely on lithium-ion batteries or fuel engines for power, resulting in energy density bottlenecks that severely limit their continuous operational capabilities. Given these shortcomings, solar-powered aircraft have gradually come into focus. Current solar-powered drones primarily utilize monocrystalline / polycrystalline silicon solar cells, whose inherent rigid structure presents a significant challenge in integrating with streamlined wings: on the one hand, rigid components require additional supports for installation, disrupting the aerodynamic shape and adding extra weight, increasing flight drag, and reducing flight economy; on the other hand, insufficient surface fit significantly reduces the effective light-receiving area. Therefore, flexible perovskite solar cells, with their unique mechanical properties and lightweight characteristics, offer a new path for aerospace photovoltaic integration. Furthermore, existing solar-powered drones mostly use conventional layout designs, resulting in significant structural weight, small payload, and limited fuselage space, which is unfavorable for equipment placement and center of gravity adjustment. Utility Model Content

[0003] To address the aforementioned problems, this invention provides a fixed-wing unmanned aerial vehicle (UAV) based on flexible perovskite solar cells. Using flexible perovskite solar cells as a power source allows the cells to be tightly fitted to the wing surface, ensuring accurate aerodynamic shape. Simultaneously, the UAV adopts a blended wing-body flying wing configuration, which significantly increases payload and greatly improves flight economy.

[0004] A fixed-wing unmanned aerial vehicle (UAV) based on flexible perovskite solar cells includes an equipment bay with a blended wing-body design and swept wings on both sides. The trailing edge of the outer section of the wing is provided with a pair of ailerons that provide both roll and pitch control functions. A pair of vertical stabilizers are provided at the wingtips, which are flush with the trailing edge of the wing and have a trapezoidal outward expansion structure. A DC brushless motor is provided at the front of the equipment bay to drive a forward-pulling propeller to generate forward thrust. Two flexible perovskite solar cells are covered and installed on the surface of the equipment bay and part of the wing to provide energy. The cells adopt a multi-layer structure with a PET substrate and are directly bonded to the skin surface.

[0005] Furthermore, the UAV's airfoil adopts the CLARK YS airfoil, with a maximum thickness of 11.70% and a maximum camber of 2.35%, both located at the 30.3% chord line, and the mid-curve is S-shaped.

[0006] Furthermore, the flexible perovskite solar cell adopts a nip planar structure and uses a PET substrate. On the substrate, from top to bottom, a metal electrode, a Spiro-OMeTAD hole transport layer, a PEAI interface modification layer, a perovskite light-absorbing layer, a SnO2 electron transport layer, and an ITO transparent electrode layer are sequentially arranged. At the same time, a parylene thin film protective layer is introduced, which has good mechanical bending performance.

[0007] Furthermore, each flexible perovskite solar cell is connected to a branch circuit, and each branch circuit is equipped with a DG7512 anti-reverse-current ideal diode, so that the two solar cells will not charge or reverse-current when their power generation voltages are different. The two branches are connected in parallel and then connected to a TPS54560 step-down module. After obtaining a reasonable voltage value, the module is connected to an electronic speed controller. One end of the electronic speed controller is connected to a brushless motor to power it, and the other end is connected to a radio receiver and two servo motors. The two servo motors are used to control the up and down deflection of the left and right ailerons, respectively. At the same time, a 2S model aircraft lithium battery is connected to the circuit to power the radio receiver and the two servo motors.

[0008] Furthermore, the aileron (3) is connected to the trailing edge of the wing via paper hinges, and the vertical stabilizer (4) is made of KT foam board and fixed with hot melt adhesive and fiber tape, and is attached to the outer side of the wingtip; its installation position is 8.6% ± 0.5 wingspan away from the leading edge of the wingtip, with no installation angle.

[0009] Furthermore, the wing and fuselage adopt a beam structure, including a main beam, secondary beam, mask, wing ribs and wing strips. The main beam is arranged along the 30% chord line, and a continuous curved surface is formed between the leading edge mask and the wing rib.

[0010] Furthermore, the wing sweep angle is 25.2°±1.5°, the aspect ratio is 1.79±0.05, and the chord length at the wingtip is reduced to 87.3%±1.5% of the wing root chord length.

[0011] Furthermore, the wing-fuselage junction is provided with a gradient fusion section, the radius of curvature of which is 105mm±5mm, and the length of the fusion section accounts for 4.33%±0.5% of the UAV's wingspan.

[0012] Furthermore, the front end of the vertical stabilizer is 78mm ± 5mm from the leading edge of the wingtip, and the trailing edge extends beyond the trailing edge of the wing by 15mm ± 2mm. The height of the stabilizer is 30% ± 2% of the wingtip chord.

[0013] Furthermore, a DC brushless motor is installed at the front of the equipment compartment to drive the propeller and generate forward thrust. It is also equipped with two movable aileron control surfaces and two fixed vertical stabilizers, forming a new form of UAV structure.

[0014] Furthermore, the equipment compartment is equipped with three longitudinally arranged detachable covers, which allow the equipment inside the compartment to move freely along the chord direction to balance the center of gravity of the machine. The edges of the covers are provided with wedge-shaped interlocking structures. The bottom of the equipment compartment (1) is provided with a replaceable skid structure. The front section of the skid is integrally formed with the motor bracket, and the rear section is fixed by dovetail groove insertion.

[0015] Based on the above technical solution, the embodiments of this utility model can produce at least the following technical effects:

[0016] (1) The fixed-wing UAV disclosed in this utility model adopts a blended wing-body design, which is different from conventional layout aircraft. It uses a flying wing layout with a sweep angle, which reduces the structural weight while increasing the effective lift area of ​​the wing and the solar cell laying area. While increasing the lift area, the wingspan is reduced, which reduces the structural weight, thereby improving the power-to-weight ratio of the perovskite solar cells, reducing the wing surface load and increasing the overall effective load.

[0017] (2) This utility model directly glues the encapsulated flexible perovskite solar cells to the surface of the wing after they are connected in parallel. There is no need for additional encapsulation and protection film structure, which helps to reduce the structural weight, thereby improving the power-to-weight ratio of the solar cells, reducing the risk of damage to the solar cells, reducing the manufacturing difficulty, and saving the later maintenance cost. It makes up for the defects of the previous solar aircraft that were encapsulated after installation.

[0018] (3) The shape and airfoil of the UAV disclosed in this utility model are not constrained by the solar cells during the design process. Because the solar cells have flexible and bendable characteristics, there is no need to straighten the airfoil, which greatly reduces the impact on the aerodynamic characteristics of the UAV and significantly improves aerodynamic efficiency. It solves the problem that rigid solar cells cannot be tightly attached to the wing surface and changes the previous phenomenon of designing aircraft based on existing solar cells. Since the aircraft design and battery form are simultaneous and integrated, other forms, especially rigid solar cells, are not suitable for the fixed-wing UAV based on flexible perovskite solar cells disclosed in this utility model.

[0019] (4) The flexible perovskite solar cell used in this utility model has good flexibility and mechanical bending performance. It can be closely attached to the wing surface without changing the aerodynamic shape of the UAV. This makes the wing shape and airfoil not restricted by the solar cell during the design process, solving the problem that rigid solar cells cannot be closely attached to the wing surface and changing the previous phenomenon of designing aircraft based on existing solar cells; (5) The UAV structure disclosed in this utility model is a single engine, two movable aileron control surfaces, and two fixed vertical stabilizers. The structure has fewer components, and the flight attitude is stable and easy to control. It is easy to operate and maintain, has high reliability, and low cost of use.

[0020] (6) The flexible perovskite solar cell used in this utility model is a finished product that has been encapsulated. It can be directly glued to the surface of the wing without additional encapsulation or protective film structure, which helps to reduce the structural weight and thus improve the power-to-weight ratio of the solar cell. At the same time, encapsulating the battery before installation helps to reduce the risk of damage to the solar cell, reduce manufacturing difficulty, and save on later maintenance costs. It makes up for the defects of previous solar aircraft that were encapsulated after installation. It has advantages such as low cost, good folding and bending performance, light weight, high theoretical photoelectric conversion efficiency, and mass production capability. It can improve the flight efficiency of UAVs, increase the effective payload, and extend the flight time. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model, the accompanying drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without any creative effort.

[0022] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the energy system composition and wiring connections according to one embodiment of the present invention;

[0024] Figure 3 This is a complete three-view drawing of one embodiment of the present invention.

[0025] Reference numerals: 1-Fuselage equipment bay, 2-Wing, 3-Aileron, 4-Vertical stabilizer, 5-Brushless motor, 6-Propeller, 7-Flexible perovskite solar cell, 8-Ideal diode, 9-Step-down module, 10-Electronic speed controller, 11-Radio receiver, 12-Model aircraft lithium battery. Detailed Implementation

[0026] The technical solutions in the embodiments of this utility model will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model. In addition, the technical solutions of various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the protection scope claimed by this utility model.

[0027] This invention provides a fixed-wing unmanned aerial vehicle (UAV) based on a flexible perovskite solar cell.

[0028] 1. Overall Structure

[0029] like Figures 1 to 3 As shown in this application, the UAV structure includes a fuselage equipment bay 1 and two swept wings 2, employing a blended wing-body design. The UAV's attitude control surfaces are a pair of ailerons 3 on the outer trailing edge of the wing section, providing both roll and pitch control functions. Two vertical stabilizers 4 are located at the mid-section of the wingtip to enhance directional stability during flight. The vertical stabilizers 4 are flush with the wingtip trailing edge and have a trapezoidal, outward-flaring structure. Their installation position is 8.6% ± 0.5 wingspan from the wingtip leading edge, with no installation angle. The leading edge of the vertical stabilizer 4 is 78mm from the wingtip leading edge, and its trailing edge extends 15mm beyond the wingtip trailing edge. The stabilizer height is 30% of the wingtip chord length.

[0030] The wing 2 and fuselage adopt a beam structure, including a main beam, secondary beam, mask, wing ribs, and flanges. The main beam is arranged along the 30% chord line, and the leading edge mask and wing ribs form a continuous curved surface. Furthermore, the junction between the wing 2 and the fuselage has a gradient blending section with a curvature radius of 105mm. The length of the blending section accounts for 4.33% of the UAV's wingspan.

[0031] The front section of the equipment compartment 1 is equipped with a DC brushless motor 5 to drive a forward-pull propeller 6 to generate forward thrust. Two flexible perovskite solar cells 7 are installed on the wing surface to provide energy. The cells adopt a multi-layer structure with a PET substrate and are directly bonded to the skin surface.

[0032] The UAV's structural features include a single engine, two movable aileron control surfaces 3, and two fixed vertical stabilizers 4. It has relatively few structural components and its flight attitude is stable and easy to control.

[0033] Equipment compartment 1 is equipped with three longitudinally arranged detachable covers, allowing the equipment inside to move freely along the chord to balance the machine's center of gravity. The edges of the covers are equipped with wedge-shaped interlocking structures. The bottom of equipment compartment 1 is also equipped with a replaceable skid structure. The front section of the skid is integrally formed with the motor bracket, and the rear section is fixed by a dovetail joint.

[0034] The control surfaces are connected to the wings and fuselage via hinges. The vertical stabilizer is made of KT board and is fixed to the wingtips using hot melt adhesive and fiber tape.

[0035] Preferably, all airfoils adopt the CLARK YS airfoil, with a maximum thickness of 11.70% and a maximum camber of 2.35%, all located at the 30.3% chord line. The mid-curve is S-shaped, which can provide longitudinal trim moment for the aircraft. At the same time, its high camber and large lift coefficient give it good aerodynamic characteristics.

[0036] In this embodiment, the fuselage span is 910 mm, the average aerodynamic chord length is 502 mm, the aspect ratio is 1.793, the sweep angle is 25.2°, and the chord length at the wingtip is reduced to 87.3% of the wing root chord length.

[0037] 2. Energy and Power Systems

[0038] The front of the fuselage equipment bay is equipped with a DC motor 5 and a thrust propeller 6. A flexible perovskite solar cell 7 is laid on the upper surface of the wing, providing power to the drone. In this embodiment, the flexible perovskite solar cell 7 includes a PET film substrate. From top to bottom, a metal electrode, a hole transport layer, a perovskite light-absorbing layer, an electron transport layer, and a transparent electrode are sequentially arranged on the PET film substrate. The flexible perovskite solar cell using the PET film substrate is a pre-encapsulated finished product, which can be directly bonded to the wing surface without additional encapsulation or protective film structures. This helps reduce structural weight, thereby improving the power-to-weight ratio of the solar cell. Simultaneously, due to the solar cell's excellent flexibility, it can closely adhere to the wing surface, reducing aerodynamic drag caused by protruding components, improving the drone's aerodynamic efficiency, and thus extending its flight time.

[0039] Two flexible perovskite solar cells are each connected to a branch circuit, and each branch circuit is equipped with a DG7512 anti-reverse-current ideal diode 8 to prevent the two solar cells from charging or reversing when their power generation voltages are different. The two branches are connected in parallel and then connected to a TPS54560 step-down module 9. After obtaining a reasonable voltage value, the module is connected to an electronic speed controller 10. One end of the electronic speed controller is connected to a brushless motor 5 to supply power, and the other end is connected to a radio receiver 11 and two servo motors. The two servo motors are used to control the up and down deflection of the left and right ailerons, respectively. At the same time, a 2S model aircraft lithium battery is connected to the circuit to supply power to the radio receiver and the two servo motors.

[0040] How this solar-powered fixed-wing drone works:

[0041] The flexible perovskite solar-powered fixed-wing UAV disclosed in this application takes off manually by hand-launching. After the device is powered on, it accelerates to take off using a running start and propeller thrust. During takeoff and climb, the battery outputs maximum power; upon reaching a predetermined altitude of 50m, the UAV reduces its output power and switches to level flight cruise mode. After completing the cruise mission, the UAV enters its landing path and cushions the impact load upon landing using foam blocks on the underside of its wings.

[0042] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A fixed-wing drone based on a flexible perovskite solar cell, characterized in that, The device cabin (1) includes a wing-body fusion design and two rear-swept wings (2), the outer section of the wings is provided with a pair of ailerons (3) with roll and pitch control functions; the wing tips are provided with a pair of vertical stabilizers (4) flush with the wing trailing edge and in trapezoidal outward expansion structure; the front section of the device cabin (1) is provided with a brushless direct-current motor (5) to drive a forward-pull propeller (6) to generate forward-pull power; The device cabin (1) and part of the wing (2) are covered with two flexible perovskite solar cells (7) for providing energy, the cells adopt a PET-based multilayer structure and are directly glued to the skin surface.

2. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The airfoil of the unmanned aerial vehicle adopts a CLARK YS airfoil, the maximum thickness is 11.70%, and the maximum camber is 2.35%, both of which are located at 30.3% chord line, and the median camber line is S-shaped.

3. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The flexible perovskite solar cell (7) adopts an n-i-p planar structure, and the PET substrate is sequentially provided with a metal electrode, a Spiro-OMeTAD hole transport layer, a PEAI interface modification layer, a perovskite light absorption layer, a SnO2 electron transport layer and an ITO transparent electrode layer from top to bottom.

4. The flexible perovskite solar cell based fixed-wing drone according to claim 1 or 3, wherein, The two flexible perovskite solar cells (7) are respectively connected to a branch, each branch is connected with a DG7512 anti-inrush ideal diode (8), and is connected to an electronic speed regulator (10) through a TPS54560 voltage reduction module (9) in parallel; one end of the electronic speed regulator (10) is connected to the brushless motor (5), and the other end is connected to a radio receiver (11) and two steering gears for controlling the ailerons; the circuit further includes a 2S model airplane lithium battery for supplying power to the radio receiver and the steering gears.

5. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The ailerons (3) are connected to the wing trailing edge through paper hinges, the vertical stabilizers (4) are made of KT foam board and are fixed by hot melt glue and fiber adhesive tape, and are attached to the outside of the wing tips; the installation position is 8.6%±0.5 wingspan length away from the wing tip leading edge, and there is no installation angle.

6. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The wing (2) and the fuselage as a whole adopt a beam structure, including a main beam, a secondary beam, a skin, a wing rib and a margin strip, the main beam is arranged along the 30% chord line position, and a continuous curved surface is formed between the leading edge skin and the wing rib.

7. The flexible perovskite solar cell based fixed-wing drone according to claim 1 or 6, wherein, The wing (2) has a sweepback angle of 25.2°±1.5°, and an aspect ratio of 1.79±0.05, and the chord length at the wing tip is reduced to 87.3%±1.5% of the chord length at the wing root.

8. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The wing (2) and the fuselage combination part is provided with a gradual fusion section, the curvature radius of the gradual fusion section is 105mm±5mm, and the length of the fusion section accounts for 4.33%±0.5% of the wingspan length of the unmanned aerial vehicle.

9. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The front end of the vertical stabilizer (4) is 78mm±5mm away from the wing tip leading edge, the trailing edge extends beyond the wing trailing edge by 15mm±2mm, and the height of the stabilizer is 30%±2% of the wing tip chord length.

10. The flexible perovskite solar cell based fixed-wing drone according to claim 1, wherein, The device cabin (1) is provided with three detachable cabin covers arranged longitudinally, so that the equipment in the cabin can move freely along the chord to balance the center of gravity of the whole machine, and the edges of the cabin covers are provided with wedge-shaped engagement structures; the bottom of the device cabin (1) is provided with a replaceable skid structure, the front section of the skid is integrally formed with the motor support, and the rear section is fixed by dovetail slot insertion.

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