Structural Test And Analysis On Launching And Recovery System Of Uav

Launching and recovery system are key component parts of Unmanned Aerial Vehicle(UAV), this thesis focus on verification job about local structural strength under these two distinct working conditions by Finite Element(FE) simulation and testing.First, Analysis of UAV under the boosting of rocket, the recovery system lids under aerodynamic load and the suspension structure under the pull of parachute lines once the parachute is released are completed upon established FE model. Testing is also done such as static load tests under the above three working conditions and wind tunnel tests of releasing parachuted. It proves out that all the structural design can satisfy the strength demand and performance demand of releasing parachute.In addition, impact of inflation and deflation pressure and the vent area on air bag cushion is researched through parameter analysis of a single air bag. Then, a set of reasonable parameter is picked, FE simulation of hard landing and landing with air bags of UAV is done. The testing process adopts a simplified UAV model and focused mainly on the effect of vent area and air bag shape. The results point out that the air bag can effectively deduce the acceleration overload and protect the fuselage. Furthermore, FE simulation is adoptable in UAV air bag design.