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.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
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
关键词
气囊
回收系统
动力学
缓冲
airbag
recovery system
dynamics
cushion
