临近空间伞张式飞艇气囊结构协同仿真研究  

Co-Simulation Research on Envelope Structure of an Umbrella-Like Inflated Airship in Near Space

作　　者：刘成业[1] 宋笔锋[1] 王海峰[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《宇航学报》2015年第10期1101-1107,共7页Journal of Astronautics

基　　金：航天五院CAST基金(CAST20090106)

摘　　要：首先介绍了临近空间伞张式飞艇气囊结构的组成和工作原理,针对原有伞张式气囊伸缩机构存在的受力集中问题提出了改进设计方案,然后对改进设计的伞张式气囊伸缩机构进行了多柔体动力学仿真,得到连接盘处的位移时间函数,并对20 km飞行高度的飞艇气囊结构进行有限元分析,得到气囊表面应力分布和气囊张力传递到气囊伸缩机构连接盘处的作用力,最后提出了一种多柔体动力学分析和有限元分析协同仿真方法,得到整个变形过程中气囊伸缩机构中受力最大连杆的载荷历程。通过与原有气囊伸缩机构中连杆的载荷历程进行对比,验证了改进设计方案的合理性。The composition and principle of the envelope structure of an umbrella-like inflated airship in near space are firstly introduced in this paper. An improved design scheme of the envelope retractable mechanism is put forward to solve the stress concentration problem in the original envelope retractable mechanism. And then a flexible multi-body dynamics analysis based on the improved envelope retractable mechanism is carried out to obtain the displacement function with time of connection panels. Then a finite element analysis of the envelope structure at altitude of 20 km is used to get the stress distribution on the envelope surface and the tension force transferred to connection panels. Finally,a collaborative simulation method of flexible multi-body dynamics analysis and finite element analysis is put forward. By means of this method,the load history of the maximal force-applied rod in the envelope retractable mechanism during the whole deformation process is obtained,and a comparison of load histories of the rods between the improved envelope retractable mechanism and the original one is demonstrated to verify the rationality of the improved envelope retractable mechanism.

关 键 词：临近空间飞行器 气囊伸缩机构 多柔体动力学 协同仿真 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程]