Multi Objective Optimization Design Of Mars Landing Airbag System Under Parallel Environment Of Super Computing Platform

For the obvious advantages of airbag such as good energy absorption characteristics, light weight, foldable, production and processing convenience, it is widely used in aviation, aerospace, defense industry and other fields. At present, the airbag cushion structure has been successfully applied in deep space exploration, such as the Mars Pathfinder, "spirit" and "opportunity" Mars probe, "Orion spacecraft. According to the cushion solution of the Pathfinder airbag, the impact test and test verification of 1:3 model has been carried out in this thesis. Based on the "Tianhe-1" super computing platform and finite element simulation technology, we engaged in the multi-objective optimization design of Mars landing airbag system. The main research results are summarized as follows:(1) Based on the "Tianhe-1" super computing platform, the analysis of finite element simulation of airbag landing system has been Carried out. Then introduced the "Tianhe-1" super computing platform and job submission process, simultaneously, the introduction and comparative analysis of automatic partitioning algorithm for parallel LS-DYNA has been done. Through the research we found that the speedup ratio and parallel efficiency of RCB algorithm is better than greedy algorithm, at the same time, we selected suitable cores for parallel computing through the comparative analysis of parallel computing efficiency under different cores.(2) Based on the airbag landing system, the method about scaled model test to verify the finite element model is proposed. First, according to the structure of "Mars Pathfinder" airbag buffer system, the 3D modeling and experimental prototyping is established by Solidworks 3D design software, and the finite element analysis model of Mars landing airbag system is established by Hyperworks and LS-Prepost. Then, based on the experimental prototype, we finished the ground impact test and experimental verification of finite element model.(3) Based on the experimental verified finite element model of the Mars landing airbag system, the parameters affect system cushion performance is studied by univariate methods. By analyzing the influence of various parameters on cushion performance, the design parameters meeting the cushion performance has been selection.(4) Based on polynomial agent model and Multi-objective Particle Swarm Optimization algorithm, conduct the multi-objective optimization of Mars landing airbag system, and obtained the pareto optimal of objective function SEA and ap. According to the design requirements of the peak acceleration, we obtain the optimal design to meet the design requirements of the Mars landing airbag system.