多腔体气囊式回收系统的着陆冲击动力学建模与分析  

Modeling and Simulation of Landing Procedure of Multi-cavity Airbag Cushion Recovery System

作　　者：何欢[1,2] 孙东阳[1] 马常亮 陈国平[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [2]南京航空航天大学振动工程研究所,南京210016 [3]洪都航空工业集团飞机设计研究所,南昌330024

出　　处：《南京航空航天大学学报》2013年第1期8-13,共6页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家高技术研究发展计划("八六三"计划)(2008AA12A205)资助项目;南京航空航天大学基本科研业务费专项科研(NJ2010009;XAA12033;XAA12015)资助项目

摘　　要：首先对深空探测气囊式回收系统的结构特性进行了分析,讨论了多腔体气囊系统动力学分析模型的构造思路。然后引入一维流管理论描述子气囊之间气体流动的通气孔。最后通过气囊式回收系统着陆冲击过程的仿真分析了通气孔面积对系统着陆缓冲性能的影响,验证了通气孔模型的有效性。分析结果表明,本文建立的动力学分析模型能够较为全面地反映出气囊式回收系统的着陆冲击过程,分析出回收系统的各项工作参数或环境因素对系统着陆缓冲性能的影响。Firsty, the structure characteristics of the deep space exploration airbag recovery system are analyzed, as well as the constitutive method of the dynamic model of the multi-cavity airbag cushion recovery system. Secondly, the model of the vent hole inside the airbag is introduced to simulate the flowing of the gas between each part of the airhag. Finally, soft landing of the multi-cavity airbag cushion recovery system is simulated to determine the influence of vent area on the landing buffer performance. Validation of the vent model is demonstrated, too. Analytical results show that the developed model is suitable for predicting the landing procedure of the multi-cavity airbag cushion recovery system. The influences of working parameters or environmental factors on the landing buffer performance can be determined by the analytical results.

关 键 词：气囊 回收系统 动力学 缓冲 

分 类 号：V244[航空宇航科学与技术—飞行器设计]