Design And Analysis Of Near Space Travel Vehicle Landing System

Near space tourism project has broad market prospects and the design of near space travel vehicle has become one of the hot spots in near space aircraft research. A near space travel project uses aerostat balloons equipped with space travel capsule. Its landing system can be used repeatedly. Due to the complicated landing environment and harsh working conditions which make the landing mechanism design very important, this paper is to carry out the design and analysis of near space travel vehicle landing system. The landing shock absorber mechanism is used for near space travel vehicle to land on the ground. Considering the high sinking speed of the capsule which can be recycled, it is necessary to guarantee the security and stability of landing process for the safety of passengers.Based on the overall parameters of the near space travel vehicle, preliminary design of the landing device is conducted. Then the virtual prototype of space travel vehicle is established. A variety of landing conditions of the near space travel vehicle are simulated and atrocious working conditions are selected to obtain the landing responses. Then the dynamic model is parameterized and relevant filling parameters are chosen as design variables to optimize the overload of the space travel vehicle using surrogate model. Landing performance of near space travel vehicle is studied. Based on rigid-flexible coupled dynamics theory, the rigid-flexible coupled dynamic model is established through the use of multi-body dynamics software and finite element analysis software. Effects of parameters such as soil friction coefficient, horizontal attitude angle of landing and horizontal landing speed are considered. Finally, drop test bed, including lifting and release device, force measuring platform and sensors, is designed for the single landing device of near space travel vehicle, which can also be applied to aircraft landing gears.