Full-lifting body perovskite solar unmanned aerial vehicle

Abstract

The utility model discloses a full-lifting-body perovskite solar unmanned aerial vehicle which comprises a large-chord-length lifting body fuselage and wings on the two sides, ailerons are arranged on the rear edges of the outer sections of the wings to serve as rolling control faces, and an elevator is arranged on the rear edge of the fuselage to serve as a pitching control face. A pair of vertical stabilizers are arranged on the outer side surface of the rear edge of the fuselage to enhance the course stability; perovskite solar cells with flexible substrates are distributed on the surfaces of the fuselage and the wings in an array mode and provide power for the unmanned aerial vehicle. The large-chord-length lifting body fuselage is adopted, the lifting area of the unmanned aerial vehicle is increased, meanwhile, the wingspan length of the unmanned aerial vehicle is reduced, loads borne by wings of the unmanned aerial vehicle are reduced, the weight of the wing structure is reduced, and effective loads are increased; the flexible perovskite solar cells are adopted for array, the damage rate of the cells in the installation process is reduced, and meanwhile due to the advantages of low cost, excellent flexibility, foldability, light weight and mass production of the perovskite solar cells, the service life of the unmanned aerial vehicle is prolonged, the cost is reduced, and mass production of the unmanned aerial vehicle is facilitated.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft design, and in particular relates to a full-lift body perovskite solar-powered UAV. Background Art

[0002] With the development of economy and the progress of society, the utilization of new energy has become a hot field, and it is developing continuously in the direction of green, clean, safe, efficient and low cost. Among them, the conversion and utilization of solar energy is the most convenient and popular. As a relatively successful case in the field of solar energy application, solar aircraft has a wide range of uses in high-altitude reconnaissance, wireless communication, environmental monitoring and early warning.

[0003] Conventional solar aircraft use solar radiation as a propulsion energy source, and its power unit consists of a solar cell group, a DC motor, a reducer, a propeller, and a control device. At present, the mainstream of solar panels is crystalline silicon solar cells that work by the photovoltaic effect. They power the motor by directly converting light energy into electrical energy. Among them, the structure disclosed in the patent application (CN105416565B) is the most representative. The structure includes a module main wing and a pair of relatively large module winglets attached to the lateral ends of the main wing. In order to collect solar radiation including relatively low-angle radiation, solar panels are installed on both sides of the main wing and the winglet. This structure can maintain the desired altitude for an indefinite period of time in a wide range of latitudes and weather conditions, but because the power system mainly uses traditional silicon-based solar cells, its energy density and photoelectric conversion efficiency are relatively low, which cannot meet the needs of long-term and high-efficiency flight; in addition, silicon-based solar cells have poor flexibility and cannot be folded, and are easily broken during use, and their weight needs to be further reduced. Therefore, the main shortcomings of existing solar drones are summarized as follows:

[0004] 1. Most existing solar drones have large aspect ratio wings, large turning radius, large storage area, and the wing root needs to bear a large load, which is not conducive to reducing the weight of the wing;

[0005] 2. Existing solar drones almost all use crystalline silicon solar cells, which have problems such as poor flexibility, easy breakage, high cost, large raw material consumption, low conversion efficiency limit, and weight that needs to be reduced;

[0006] 3. Existing solar drones have small payloads and small fuselage space, which is not conducive to equipment placement and center of gravity adjustment. Utility Model Content

[0007] In view of the above-mentioned defects, the utility model provides a full-lift body perovskite solar drone, which uses perovskite solar cells on a flexible substrate as a power source, and can achieve lower costs and higher conversion efficiency.

[0008] A full-lifting perovskite solar-powered UAV comprises a long-chord lifting body fuselage (i.e., a lifting body with a chord length exceeding twice the chord length of the wing) and wings arranged on both sides of the fuselage, wherein the trailing edge of the outer section of the wing is provided with ailerons as roll control surfaces, the trailing edge of the fuselage is provided with elevators as pitch control surfaces, and a pair of vertical stabilizers are provided on the outer side surface of the trailing edge of the fuselage to enhance heading stability; the fuselage and wing surfaces are arrayed with perovskite solar cells with a flexible substrate to provide power for the UAV.

[0009] Preferably, the UAV adopts the fold line design airfoil of S5020, and modifies the upper edge of the airfoil into a straight line so that the solar cell array is in the same plane. That is, a point is taken at 19.249% of the chord length on the upper edge of the S5020 airfoil, and a point is taken at 89.854% of the chord length on the upper edge, and the two points are connected by a straight line segment; its maximum thickness is 6.528%, and at 19.249% of the chord length, the solar cell array is in the same plane.

[0010] Preferably, a pair of propellers are provided at the leading edge of the fuselage, and a dual brushless motor is provided at the nacelle at the leading edge of the fuselage to directly drive the propellers forward.

[0011] Preferably, the perovskite solar cell comprises a pet film substrate, on which a metal electrode, a hole transport layer, a perovskite light absorption layer, an electron transport layer and a transparent electrode layer are sequentially arranged from top to bottom.

[0012] Preferably, the perovskite solar cell includes two branches in parallel, one branch is connected to the battery array on the surface of the wing, and the other branch is connected to the battery array on the surface of the fuselage; each branch is connected to a DG7512 ideal diode for backflow prevention, and the two branches are connected to an mppt controller, which is then connected to the power and control system of the drone to supply power.

[0013] Preferably, the power and control system includes a power system and a control system, wherein the power system includes a brushless motor for driving a propeller, and the control system includes an electronic speed regulator connected to the brushless motor, a radio receiver, a flight control board and four servos, and the four servos respectively control the left aileron, the right aileron, the up and down deflection of the elevator, and the steering of the front landing gear.

[0014] Preferably, the wing is a beam structure, including ribs, main beams, leading edge wood strips, rear masts and leading edge panels that are glued to each other; the fuselage and the wing are connected by a main beam sleeve and two locating pins.

[0015] The beneficial effects of the utility model are:

[0016] 1. The new type of UAV disclosed herein adopts a long-chord lifting body fuselage, which increases the lift area of ​​the UAV while reducing its wingspan, reduces the load on its wings, reduces the weight of the wing structure and increases the effective load. The long-chord fuselage increases the internal volume of the fuselage, increases the possibility of load distribution, and is conducive to the adjustment of the center of gravity and the placement and installation of equipment;

[0017] 2. This new model uses a fold line design airfoil based on S5020, so that the solar cell array is in the same plane. In most flight conditions, the sunlight has a uniform incident angle, which effectively avoids the situation where the current of some solar cells is small due to the small solar altitude angle, thereby limiting the current of the entire branch.

[0018] 3. This new type of flexible perovskite solar cell array using PET film substrate can reduce the breakage rate of the cell during installation. At the same time, due to the advantages of low cost, light weight, foldability and mass production of perovskite solar cells, it is conducive to the cost reduction and mass production of solar drones. And due to its high designability and high theoretical efficiency, it is conducive to the improvement of the payload and endurance of solar drones. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model, the drawings required for use in the embodiments are briefly introduced below.

[0020] Figure 1 It is a structural schematic diagram of an embodiment of the utility model;

[0021] Figure 2 It is a schematic diagram of an energy system of an embodiment of the utility model;

[0022] Figure 3 It is an overall three-view diagram of the device of one embodiment of the utility model.

[0023] Figure numerals: 1-left wing, 2-right wing, 3-fuselage, 4-aileron, 5-elevator, 6-brushless motor, 7-vertical stabilizer, 8-power and control system, 9-MPPT, 10-ideal diode, 11-perovskite solar cell, 12-lithium battery. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0025] The embodiment of the utility model provides a full-lift body perovskite solar drone.

[0026] 1. Overall structure: Figures 1 to 3 As shown, the UAV is divided into a lifting body fuselage 3 and a left wing 1 and a right wing 2. The fuselage 3 and the left wing 1 and the right wing 2 are connected through a main beam sleeve and two positioning pins. The control surfaces include ailerons 4 at the trailing edges of the left and right wing outer sections and elevators 5 at the trailing edge of the fuselage. Two vertical stabilizers 7 are arranged at the trailing edge of the side of the fuselage 3 to enhance the heading stability. The surface of the fuselage 3 and the left wing 1 and the right wing 2 are arrayed with perovskite solar cells 11 with a flexible substrate.

[0027] The wing is a wooden beam structure, which is composed of wing ribs, main beams, leading edge wood strips, rear masts and leading edge panels. The wing and fuselage are sheathed with carbon tubes and connected with two dowel pins.

[0028] The overall fuselage is a multi-beam structure, consisting of multiple beams, wing ribs and panels that run through the fuselage.

[0029] The rudder surface is connected to the wing and fuselage through hinges. The vertical stabilizer is made of KT board material and is fixed to the rear edge of the fuselage through hot melt adhesive. The carbon fiber landing gear and the fuselage main beam are fixed to all the wing ribs, wing beams, panels and other wooden materials and KT board materials through epoxy resin, and processed by laser cutting. The carbon fiber landing gear is mainly processed by CNC milling machine and connected with epoxy resin.

[0030] The fuselage and wing airfoils are modified airfoils based on the S5020 airfoil, that is, take a point at 19.249% of the chord length on the upper edge of the S5020 airfoil, take a point at 89.854% of the chord length on the upper edge, and connect the two points with a straight line segment. Its maximum thickness is 6.528%. At 19.249% of the chord length, the solar cell array is in the same plane. In most flight conditions, the sunlight has a uniform incident angle, which effectively avoids the situation where the current of some solar cells is small due to the small solar altitude angle, thereby limiting the current of the entire branch. In this embodiment, the fuselage span is 550mm and the chord length is 1300mm; the wing span is 1535mm and the chord length is 530mm.

[0031] The present application adopts a long-chord lifting body fuselage directly connected to the wing without a horizontal tail, which increases the lift area of ​​the UAV while reducing its wingspan, reduces the load on its wing, reduces the weight of the wing structure and increases the effective load. The long-chord fuselage increases the internal volume of the fuselage, increases the possibility of load distribution, and is conducive to the adjustment of the center of gravity and the placement and installation of equipment.

[0032] 2. Power: A power and control system 8 is provided at the leading edge of the fuselage, and a flexible perovskite solar cell 11 is arrayed on the upper surface of the left wing 1, the right wing 2 and the fuselage 3 to provide energy and power for the drone. In this embodiment, the perovskite solar cell 11 includes a pet film substrate, and the pet film substrate described in this application is sequentially provided with an Au 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. The use of a flexible perovskite solar cell array with a pet film substrate can reduce the breakage rate of the battery during its installation. At the same time, due to the advantages of low cost, excellent flexibility, foldability, light weight and mass production of perovskite solar cells, it is conducive to cost reduction and mass production of solar drones. And due to its high designability and high theoretical efficiency, it is conducive to the improvement of the payload and endurance of solar drones.

[0033] The perovskite solar cell array includes two parallel branches, one branch is connected to the battery array on the wing surface, and the other branch is connected to the battery array on the fuselage surface. Each branch is connected to a DG7512 anti-backflow ideal diode 10. After parallel connection, an MPPT controller 9 (Maximum Power Point Tracking solar controller) is connected. In this embodiment, a ZK-SJ20mppt controller is selected, and then the ZK-SJ20mppt controller is connected to the power and control system to power it. At the same time, a lithium battery 12 is set to be directly connected in parallel with the power system.

[0034] Power and control system: The power system consists of two brushless motors installed on the nacelles at the leading edge of the fuselage that directly drive the propellers to pull forward. The control system includes two electronic speed regulators directly connected to the brushless motors, a radio receiver, a flight control board with fixed climb angle, stabilization and autonomous cruise functions, and four servos. The four servos control the left aileron, right aileron, the up and down deflection of the elevator, and the steering of the front landing gear.

[0035] How this solar powered drone works:

[0036] The full-lift body perovskite solar drone disclosed in this application is placed on the runway and accelerated to take off by means of a propeller. In the climbing stage, the maximum power climbing mode of the flight control board is turned on, that is, the aircraft climbing angle is set according to the solar altitude angle obtained in the ground test to obtain the climbing mode with maximum illumination. When reaching an altitude of 100m, switch to the autonomous cruise mode.

[0037] When the power of the solar cell array is higher than the power consumed by the power and control system, the excess power will charge the battery; when the power of the solar cell array is lower than the power consumed by the power and control system, the battery will intervene to provide additional power.

[0038] After the cruise mission is completed, the aircraft enters the landing route and the flight control board switches to the stabilization mode.

[0039] Finally, it should be noted that the above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. Although the utility model is described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions recorded in the above embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A full-lift body perovskite solar drone, characterized in that: It comprises a long-chord lifting body fuselage and wings arranged on both sides of the fuselage, wherein the trailing edge of the outer section of the wing is provided with ailerons as a roll control surface, the trailing edge of the fuselage is provided with elevators as a pitch control surface, and a pair of vertical stabilizers are provided on the outer side surface of the trailing edge of the fuselage to enhance the heading stability; The fuselage and wing surfaces are arrayed with perovskite solar cells on a flexible substrate to provide power for the drone.

2. The full-lift body perovskite solar drone according to claim 1, characterized in that: The UAV adopts a modified airfoil based on the S5020 airfoil, and the upper edge of the airfoil is a straight line, that is, a point is taken at 19.249% of the chord length of the upper edge of the S5020 airfoil, and a point is taken at 89.854% of the chord length of the upper edge, and the two points are connected by a straight line segment, the maximum thickness of which is 6.528%. At 19.249% of the chord length, the solar cell arrays are in the same plane.

3. The full-lift body perovskite solar drone according to claim 1, characterized in that: The front edge of the fuselage is provided with a pair of propellers, and the nacelle at the front edge of the fuselage is provided with dual brushless motors to directly drive the propellers forward for power.

4. The full-lift body perovskite solar drone according to any one of claims 1-3, characterized in that: The perovskite solar cell adopts a nip planar structure, and the cell includes a pet film substrate, on which 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 are arranged in sequence from top to bottom.

5. The full-lift body perovskite solar drone according to claim 3, characterized in that: The perovskite solar cell includes two parallel branches, one branch is connected to the battery array on the wing surface, and the other branch is connected to the battery array on the fuselage surface; each branch is connected to a DG7512 anti-backflow ideal diode, and the two branches are connected to an mppt controller, which is then connected to the power and control system of the drone to supply power.

6. The full-lift body perovskite solar drone according to claim 5, characterized in that: The power and control system includes a power system and a control system, wherein the power system includes a brushless motor for driving a propeller, and the control system includes an electronic speed regulator connected to the brushless motor, a radio receiver, a flight control board and four servos, and the four servos respectively control the left aileron, the right aileron, the up and down deflection of the elevator, and the steering of the front landing gear.

7. The full-lift body perovskite solar drone according to claim 1, characterized in that: The wing is a beam structure, including mutually glued ribs, main beams, leading edge wood strips, rear masts and leading edge panels; The fuselage and wing are connected by means of a main spar sleeve and two dowel pins.

8. The full-lift body perovskite solar drone according to claim 1 or 7, characterized in that: The fuselage is a multi-beam structure, including a plurality of beams, wing ribs and panels that penetrate the fuselage.

9. The full-lift body perovskite solar drone according to claim 1 or 7, characterized in that: The control surface of the elevator is connected with the wing and the fuselage through hinges, and the vertical stabilizer is a KT plate, which is fixedly connected with the rear edge of the fuselage through hot melt adhesive.

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