CN-117416520-B - Design method of solar unmanned aerial vehicle

CN117416520BCN 117416520 BCN117416520 BCN 117416520BCN-117416520-B

Abstract

The application discloses a solar unmanned aerial vehicle design method, which comprises the steps of firstly constructing an energy balance design feasible region and a weight balance feasible region of a solar unmanned aerial vehicle according to the weight and the wing area of the solar unmanned aerial vehicle, then constructing a full-power expression of the solar unmanned aerial vehicle under climbing rate constraint, steady-disc overload constraint, maximum flying height constraint and maximum flying speed constraint according to the weight and the wing area of the solar unmanned aerial vehicle, and finally taking a public area formed by the relational expression as the design feasible region of the solar unmanned aerial vehicle.

Inventors

LIU NING
YANG YANHAN
XIAO LIANGHUA
LI GUANXIONG
ZHANG BIN

Assignees

成都飞机工业（集团）有限责任公司

Dates

Publication Date: 20260512
Application Date: 20230724

Claims (6)

1. The solar unmanned aerial vehicle design method is characterized by comprising the following steps of: Constructing an energy balance design feasible region according to the weight and wing area of the solar unmanned aerial vehicle; comprises the steps of calculating the solar irradiation energy of whole day of unit area According to the solar irradiation energy And wing area calculation of the power generation of a solar panel Calculating daytime energy consumption of the solar unmanned aerial vehicle according to the weight of the solar unmanned aerial vehicle Calculating night energy consumption of the solar unmanned aerial vehicle according to the weight of the solar unmanned aerial vehicle According to the formula Constructing a solar unmanned aerial vehicle energy balance design feasible region; and constructing a weight balance feasible region according to the weight and the wing area of the solar unmanned aerial vehicle, wherein the expression of the weight balance feasible region is as follows: wherein Representing the total weight of the unmanned aerial vehicle, Is the weight of the energy storage battery, The weight of the solar panel, Is MPPT weight, Is of the structure weight, Is the weight of the motor, Is the weight of the cable, Is of DC-DC weight, For the task load weight Is the weight of the airborne equipment; The method comprises the steps of establishing a full-power expression of a solar unmanned aerial vehicle under climbing rate constraint, stable disc overload constraint, maximum flying height constraint and maximum flying speed constraint according to the weight and wing area of the solar unmanned aerial vehicle, setting a climbing rate constraint initial value of the solar unmanned aerial vehicle, obtaining the full-power expression of the climbing rate constraint according to the full-power expression, setting a stable disc overload constraint initial value of the solar unmanned aerial vehicle, obtaining the full-power expression under the stable disc overload constraint according to the full-power expression, setting the maximum flying height constraint initial value of the solar unmanned aerial vehicle, obtaining the full-power expression under the maximum flying height constraint according to the full-power expression, setting the maximum flying speed constraint initial value of the solar unmanned aerial vehicle, and obtaining the full-power expression under the maximum flying speed constraint according to the full-power expression, wherein the full-power expression of the solar unmanned aerial vehicle is as follows: wherein For the mean radiation intensity of daytime sun, satisfy The proportion of the solar cell is paved for the solar cell, For the conversion efficiency of the solar cell array, For the purpose of the MPPT efficiency, For the purpose of motor efficiency, For the purpose of the efficiency of the propeller, For the solar array to motor cable transmission efficiency, For the purpose of dynamic pressure in flight, For the area of the wing of the aircraft, 、、 For the quadratic coefficient and the first-order coefficient in the resistance pole curve equation and the zero-liter resistance coefficient, For the rate of ascent of an aircraft, For the overload factor of the aircraft, 、 The task load power consumption and the on-board electronic device power consumption are respectively, In order to achieve a DC-DC efficiency, For solar array to on-board equipment cable transmission efficiency, The weight margin coefficient of the electronic equipment on the solar unmanned aerial vehicle, The power density of the onboard electronic equipment of the solar unmanned aerial vehicle, The daytime flight time of the solar unmanned aerial vehicle is; and drawing boundary curve clusters in the energy balance design feasible region and the weight balance feasible region according to the full-power expression of the solar unmanned aerial vehicle under the climbing rate constraint, the steady-disc overload constraint, the maximum flying height constraint and the maximum flying speed constraint, so as to obtain the design feasible region of the solar unmanned aerial vehicle.
2. The solar unmanned aerial vehicle design method of claim 1, wherein the calculated unit area of solar irradiation energy is the whole day Comprising the following steps: Calculating the solar radiation intensity SI outside the atmosphere; Calculating a solar altitude; Calculating the radiation power of sunlight in unit area on the earth according to the solar radiation intensity SI outside the atmosphere and the solar altitude; calculating the whole-day solar irradiation energy of the unit area according to the radiation power of the unit area 。
3. A method of designing a solar unmanned aerial vehicle according to claim 1 or 2, wherein the unit area of solar irradiation energy is the whole day Satisfy the following requirements Where P sc represents the radiant power per unit area of sunlight on earth.
4. The solar unmanned aerial vehicle design method of claim 1, wherein the power generation amount of the solar panel Satisfy the following requirements Wherein The proportion of the solar cell is paved for the solar cell, For the conversion efficiency of the solar cell array, Is MPPT efficiency.
5. The solar unmanned aerial vehicle design method of claim 1, wherein the daytime energy consumption Satisfy the following requirements Wherein the method comprises the steps of The plane flying power of the solar unmanned plane is obtained, , 、 The resistance coefficient and the lift coefficient of the solar unmanned aerial vehicle are; The night energy consumption Satisfy the following requirements Wherein the method comprises the steps of 、 For the transmission efficiency of the energy storage battery to the motor and the energy storage battery to the on-board equipment cable, For solar panel to energy storage cell cable transmission efficiency, 、 For the discharging and charging efficiency of the energy storage battery, The solar unmanned aerial vehicle is the daytime flight time length, The night flight time length of the solar unmanned aerial vehicle is long.
6. The solar unmanned aerial vehicle design method of claim 1, wherein the energy storage battery weighs , Is the energy density of the energy storage battery, and the weight of the solar panel , The solar cell array area density is; the expression of MPPT weight is , For the maximum irradiance within one day of the sun, Is MPPT power-weight ratio, structural weight , The weight of the motor is equal to the structural surface density of the solar unmanned aerial vehicle , Is the overload coefficient of the motor and is used for controlling the motor to be in a state of being in a state of, Is the power-weight ratio of the motor and the weight of the cable , As a weight coefficient of the cable, Is the wing aspect ratio, DC-DC weight , Is the power-to-weight ratio of the DC-DC voltage reducer.

Description

Design method of solar unmanned aerial vehicle Technical Field The application relates to the technical field of aircraft design, in particular to a solar unmanned aerial vehicle design method. Background The solar unmanned aerial vehicle is a novel aircraft which uses solar energy as the only energy source, converts the solar energy into electric energy through a solar cell and supplies power for airborne equipment and a propulsion system. The solar unmanned aerial vehicle has high flying height and long endurance time, and is an ideal platform for executing a reconnaissance task at high altitude; Compared with the traditional fuel power unmanned aerial vehicle, the design target of the solar unmanned aerial vehicle pursues energy balance across the day and night, the determination of the overall parameters is indistinguishable from factors such as the weight of the whole unmanned aerial vehicle, meanwhile, the energy source of the solar unmanned aerial vehicle is the power generation of a solar battery, the problem of rapid weight change caused by continuous fuel consumption is avoided, and therefore the method for designing the unmanned aerial vehicle based on the function curve of the airplane takeoff thrust ratio relative to the wing load in the prior art is not suitable for the design of the solar unmanned aerial vehicle. Disclosure of Invention The application mainly aims to provide a solar unmanned aerial vehicle design method, which aims to solve the defect that the solar unmanned aerial vehicle design method is not suitable for solar unmanned aerial vehicle design in the prior art. The application realizes the aim through the following technical scheme: the design method of the solar unmanned aerial vehicle comprises the following steps: Constructing an energy balance design feasible region according to the weight and wing area of the solar unmanned aerial vehicle; constructing a weight balance feasible region according to the weight and the wing area of the solar unmanned aerial vehicle; constructing a full-power expression of the solar unmanned aerial vehicle under climbing rate constraint, steady disc overload constraint, maximum flying height constraint and maximum flying speed constraint according to the weight and wing area of the solar unmanned aerial vehicle; and drawing boundary curve clusters in the energy balance design feasible region and the weight balance feasible region according to the full-power expression of the solar unmanned aerial vehicle under the climbing rate constraint, the steady-disc overload constraint, the maximum flying height constraint and the maximum flying speed constraint, so as to obtain the design feasible region of the solar unmanned aerial vehicle. Optionally, the energy balance design feasible region is constructed according to the weight and the wing area of the solar unmanned aerial vehicle, and the method comprises the following steps: calculating the solar irradiation energy of whole day of unit area ; According to the solar irradiation energyAnd wing area calculation of the power generation of a solar panel; Day energy consumption of solar unmanned aerial vehicle is calculated according to weight of solar unmanned aerial vehicle; Night energy consumption of solar unmanned aerial vehicle is calculated according to weight of solar unmanned aerial vehicle; According to the formulaAnd constructing an energy balance design feasible region of the solar unmanned aerial vehicle. Alternatively, the total daily solar irradiation energy per unit area is calculatedComprising the following steps: Calculating the solar radiation intensity SI outside the atmosphere; Calculating a solar altitude; Calculating the radiation power of sunlight in unit area on the earth according to the solar radiation intensity SI outside the atmosphere and the solar altitude; calculating the whole-day solar irradiation energy of the unit area according to the radiation power of the unit area 。 Alternatively, the energy is radiated by the sun per unit areaSatisfy the following requirementsWhere P sc represents the radiant power per unit area of sunlight on earth. Alternatively, the power generation amount of the solar cell panelSatisfy the following requirementsWhereinThe proportion of the solar cell is paved for the solar cell,For the conversion efficiency of the solar cell array,Is MPPT efficiency. Alternatively, daytime energy consumptionSatisfy the following requirementsWherein the method comprises the steps ofThe plane flying power of the solar unmanned plane is obtained,,、The method comprises the steps of designing a solar unmanned aerial vehicle, wherein rho represents the air density of the solar unmanned aerial vehicle at the designed flight height, T represents the thrust required by the flat flight of the solar unmanned aerial vehicle, and V represents the designed flat flight speed of the solar unmanned aerial vehicle; The night energy consumption Satisfy the following requirem