Throw Type Foldable Rotor UAV Design And Simulation Analysis

With the rapid development of UAV industry,more and more industries began to appear UAV figure.In the military field,small UAVs,with their low cost,simple operation and powerful all-weather,all-airspace reconnaissance and strike capability,have become an important support for the “surgical” strike tactics,which are highly dependent on continuous and real-time battlefield situation information for rapid decision-making and killing.At the same time,the rotorwing UAV itself has the characteristics of short range,short navigation time,low flight height,slow speed and so on.These factors make the UAV have problems such as low survival ability,poor penetration ability and easy to be shot down in the battlefield.In order to meet the needs of the complex battlefield environment and the diversified combat tasks in the future,this paper proposes a way of shooting UAV by parent bullet,which makes it have the characteristics of strong penetration ability and large combat radius.According to the combat characteristics and requirements of UAV,a foldable rotor UAV with a scattering type that can be loaded in parent bullet is studied.Combining the kinematics and dynamics equations of the UAV,the aerodynamic model based on momentum theory and blade element theory is established,and the three-dimensional model of the rotor blade is established,and the lift force of the rotor is calculated through fluid simulation.According to the structure layout of parent bullet,the aerodynamic model of the parent bullet is established,and the aerodynamic parameters of the parent bullet under different firing angles and initial velocity are simulated by CFD fluid.The trajectory of the outside flight ballistic of the parent bullet is simulated by Adams,and the height and distance of the parent bullet are analyzed.At the same time,for the separation of the parent bullet and submunitions(UAV),the final scheme is determined to be the backtoss propellant driven spraying by gas after comprehensive comparison of various spraying methods.The dropping device and the deceleration parachute are designed,and the decelerating process of the deceleration parachute is analyzed dynamically.According to the principle and composition of the rotor UAV,a test prototype was built,and the lift and power of the UAV were tested by the semi-physical test bench.The performance of the UAV was analyzed according to the obtained data.Conduct physical flight,analyze flight data,and test the stability of flight control algorithm;Anti-overload impact test was carried out to verify the feasibility of gun-launched UAV.