The implementation of the present invention will be further explained below in conjunction with the drawings:
 The invention relates to a method for controlling a shock-absorbing airbag of a fixed-wing unmanned target drone, and specifically includes the following steps:
 1) After the fixed-wing UAV receives the landing signal, the UAV collects the parameter information at this time;
 2) Process the collected information to calculate the optimal internal pressure value of the shock-absorbing airbag;
 3) Collect the actual pressure inside the shock-absorbing airbag and operate the inflatable fan to make the shock-absorbing airbag reach the optimal internal pressure;
 4) When the fixed-wing UAV landed, stop the fan.
 The parameter information includes the height, temperature, fuel consumption, speed and acceleration of the fixed-wing unmanned target drone.
 Specifically, the damping airbag control device of the fixed-wing unmanned target aircraft receives the altitude signal collected by the altitude sensor and the temperature signal collected by the temperature sensor, and inputs these flight status and environmental signals into the internal pressure calculation of the damping airbag. The algorithm comprehensively judges the height, temperature, fuel consumption, speed, acceleration and other information of the fixed-wing unmanned target aircraft to obtain real-time recovery of the flight status and environmental conditions. The shock absorption airbag can produce the best shock absorption effect. Excellent internal pressure value. Since the air pressure level is different at different altitudes and different temperatures, the internal pressure of the corresponding shock-absorbing airbag also needs to be adjusted accordingly to ensure that the shock-absorbing airbag is recovered and landed at different altitudes, and the internal pressure of the shock-absorbing airbag is always maintained at best value. The optimal internal pressure value of the shock-absorbing airbag is output as the target pressure to the shock-absorbing airbag control algorithm. At the same time, the inflating fan speed signal collected by the speed sensor and the internal pressure of the shock-absorbing airbag collected by the air pressure sensor are input to the shock-absorbing airbag control algorithm , The control signal of the inflatable fan is calculated by the control algorithm of the shock-absorbing airbag. The collected umbrella opening signal and the acceleration signal collected by the inertial sensor are used as the input of the output control algorithm to realize the output control of the control signal. The control signal output by the output control algorithm drives the inflation fan to inflate the shock-absorbing airbag.
 More specifically, the pressure optimization algorithm needs to collect information such as the height, temperature, fuel consumption, speed and acceleration of the fixed-wing unmanned target drone in real time. In order to obtain the optimal internal pressure of the shock-absorbing airbag, it is first necessary to obtain the atmospheric pressure around the fixed-wing UAV. The specific relationship between atmospheric pressure and altitude and temperature is shown in formula (1). Where H is the pressure altitude relative to sea level, Is the atmospheric static pressure at that altitude, Is the standard atmospheric pressure, Is the atmospheric temperature at height H, Is the temperature decline rate, and R is the gas constant (29.27m/K).
 From formula (1), it can be seen that the air pressure changes with changes in altitude and temperature. According to the altitude and temperature information of the fixed-wing unmanned target drone, the real-time air pressure data can be obtained by formula (1).
 Then, calculate the real-time mass M of the target drone based on the collected fuel consumption. The specific calculation formula is as shown in formula (2);
 Where Is the initial mass of the drone, and t is the actual flight time of the fixed-wing unmanned drone.
 Finally, the collected fixed-wing unmanned target drone's landing speed, acceleration, real-time mass and ambient air pressure of the target drone are brought into the speed and acceleration equations of the buffer object at the stroke, such as formulas (3) and (4), The internal pressure value of the shock-absorbing airbag when the fixed-wing unmanned target aircraft has the best shock absorption effect when landing is obtained through calculation, as the optimal internal pressure of the shock-absorbing airbag, and as the given value of the internal pressure of the shock-absorbing airbag.
 among them, Is the speed of the drone, Is the landing speed of the drone, Is the volume when the airbag is full, M is the mass of the target aircraft, Is the initial height of the airbag, Is the actual height of the airbag, , Is the ratio of the actual volume of the airbag to the initial volume, , Is the adiabatic index, Is the acceleration during the landing of the target aircraft, A is the ground contact area of the shock-absorbing airbag, It is the initial pressure and the best internal pressure when the shock-absorbing airbag is full.
 In the present invention, it is judged whether the fixed-wing unmanned target drone has opened the umbrella by the parachute opening signal, and if the parachute is not opened, the parachute opening signal is continuously detected. When the parachute opening signal of the fixed-wing drone is detected, the control signal of the inflation fan is output to the inflation fan, so that the inflation fan can quickly rotate to inflate the shock-absorbing airbag until the internal pressure of the shock-absorbing airbag reaches the optimal internal pressure and remains constant . During the landing process of the fixed-wing unmanned drone, the shock-absorbing airbag control device is constantly searching for the best internal pressure. Therefore, the internal pressure of the shock-absorbing airbag also changes with the change of the optimal internal pressure until the fixed-wing drone is unmanned. The drone landed. According to the acceleration signal, it is judged whether the fixed-wing unmanned target aircraft has landed. If it does not land, the control signal of the air-filling fan is always output to maintain the control of the air-filling fan. After judging that the fixed-wing unmanned target aircraft has landed, the output control algorithm quickly cuts off the control signal and stops the control of the inflation fan to prevent damage to the damping airbag control device.