基于超算平台并行环境下气囊式着陆缓冲系统的耐撞性优化设计

发布时间：2018-11-14 08:35

【摘要】：缓冲气囊具有吸能特性好、质量轻、可折叠、生产加工便捷等优点,广泛地应用于航空、航天和国防工业等领域中。目前,气囊缓冲结构已经成功应用于“火星探路者”号、“勇气”号和“机遇”号火星探测器、“猎户座”飞船等深空探测领域。本文针对“探路者”号气囊缓冲方案,进行了1:3缩放模型冲击试验与试验验证。基于“天河一号”超算平台与有限元仿真技术,开展了气囊式火星着陆系统的多目标优化设计工作。主要研究工作和成果如下:(1)基于“天河1号”超算平台,进行了气囊式火星着陆系统的有限元仿真分析。介绍了“天河1号”超算平台及作业提交流程,同时针对LS-DYNA并行自动分区算法做了介绍和对比分析。通过研究发现,RCB并行分区算法比“贪婪”分区算法具有更好的加速比和并行效率,同时,通过不同计算核数的并行效率对比分析选取了较为适合的核数进行并行计算。(2)基于气囊式火星着陆系统,提出了采用缩比模型进行试验验证的方法。首先,参照“火星探路者号”气囊缓冲系统结构,使用Solidworks三维设计软件完成了气囊式火星着陆系统的三维建模与试验样机制作,并基于Hyperworks与LS-Prepost建立了气囊式火星着陆系统有限元分析模型。然后,基于试验样机完成了地面冲击试验并完成有限元模型试验验证。(3)基于试验验证了的气囊式火星着陆系统有限元模型,运用单变量法对影响系统缓冲性能的参数进行了研究,通过分析各参数对系统缓冲性能的影响,选取了一组满足缓冲性能要求的优选设计参数。(4)基于多项式函数代理模型与多目标粒子群优化算法对气囊式着陆缓冲系统缓冲过程进行多目标优化,得到了目标函数SEA与ap的Pareto最优解集,根据加速度峰值设计要求,获得了满足设计要求的气囊式火星着陆系统的最优设计。
[Abstract]:Buffer airbags have the advantages of good energy absorption, light weight, foldable, convenient production and processing, and are widely used in aviation, aerospace and national defense industries. At present, airbag buffer structures have been successfully used in deep space exploration such as Mars Pathfinder, Spirit and opportunity, Orion spacecraft and so on. In this paper, the shock test and test verification of 1:3 scaling model are carried out for the air bag buffer scheme of Pathfinder. Based on the "Tianhe 1" supercomputing platform and finite element simulation technology, the multi-objective optimization design of the airbag Mars landing system is carried out. The main work and results are as follows: (1) based on the Tianhe 1 platform, the finite element simulation of the airbag Mars landing system is carried out. This paper introduces the "Tianhe 1" supercomputing platform and the process of job submission. At the same time, the parallel automatic partition algorithm of LS-DYNA is introduced and compared. It is found that the RCB parallel partition algorithm has better speedup and parallel efficiency than the greedy partition algorithm. By comparing and analyzing the parallel efficiency of different computations, the more suitable kernel numbers are selected for parallel computation. (2) based on the airbag Mars landing system, a method is proposed to test and verify by using the scaling model. First of all, referring to the structure of Mars Pathfinder airbag buffer system, the 3D modeling and test prototype of the airbag Mars landing system are completed by using Solidworks 3D design software. Based on Hyperworks and LS-Prepost, the finite element analysis model of airbag Mars landing system is established. Then, the ground impact test and the finite element model test are completed based on the prototype test. (3) based on the test verification, the finite element model of the airbag Mars landing system is verified. The single variable method is used to study the parameters that affect the buffer performance of the system, and the influence of each parameter on the buffer performance of the system is analyzed. A set of optimal design parameters are selected to meet the requirements of buffer performance. (4) based on polynomial function agent model and multi-objective particle swarm optimization algorithm, the buffer process of airbag landing buffer system is optimized by multi-objective. The Pareto optimal solution set of the objective function SEA and ap is obtained. According to the design requirements of the peak acceleration, the optimal design of the airbag Mars landing system satisfying the design requirements is obtained.
【学位授予单位】：湖南大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V445

【参考文献】