全向增阻离轨的充气薄膜球设计与性能分析  

Design and performance analysis of an inflatable film balloon for drag deorbiting

作　　者：卫剑征[1,2] 张义[2,3] 侯一心 谭惠丰 WEI Jianzheng;ZHANG Yi;HOU Yixin;TAN Huifeng(Science and Technology on Advanced Composites in Special Environments Laboratory,Harbin Institute of Technology,Harbin 150080,China;Center of Composite Materials and Structures,Harbin Institute of Technology,Harbin 150080,China;Academy of Opto-electronics,China Electronics Technology Group Corporation,Tianjin 300308,China)

机构地区：[1]哈尔滨工业大学、特种环境复合材料技术国家重点实验室,哈尔滨150080 [2]哈尔滨工业大学、复合材料与结构研究所,哈尔滨150080 [3]中国电子科技集团公司、光电研究院,天津300308

出　　处：《清华大学学报（自然科学版）》2023年第3期302-310,共9页Journal of Tsinghua University(Science and Technology)

基　　金：航天进入减速与着陆技术实验室开放基金项目(EDL19092121)。

摘　　要：增阻式离轨是避免小卫星失效后产生空间碎片的高效方式之一。该文针对充气展开增阻薄膜球的离轨问题,首先,给出了充气展开薄膜球的全向增阻设计方案,提出了闭合三维球面变形收缩为紧致星型与星瓣Z型融合折叠方法,经零线宽与变厚度折叠形成密实立方体状;其次,基于小挠度球壳变形假设,分析了增阻薄膜球在极限高度200 km下受到最大气阻力时其球面的失稳临界压力,对比在室温和高温条件下薄膜球的临界压力变化,通过真空环境箱进行试验验证;最后,分析了不同碎片面质比与增阻薄膜球直径对离轨时间的影响关系。结果表明:聚酰亚胺薄膜球可作为空间碎片的全向增阻离轨设计的球状结构,随着球体直径的增大,其临界压力呈指数型下降;在相同的轨道高度,碎片的面质比越大,离轨时间越短;在相同的面质比条件下,碎片的轨道高度越高,离轨时间越长。[Objective] The quantity, total mass, and distribution region of space debris are constantly increasing, and simultaneously, over half of the low earth orbit satellite operators have no sustainable way to remove the failed satellites from space. Consequently, the growth rate of space debris after the end of a satellite’s life considerably increases over time. Thus, the problem of removing space debris is very important. [Methods] Drag deorbiting is an efficient way to avoid space debris after micro-satellites fail. In this study, aiming at the deorbit problem using an inflatable film drag balloon, a design of omnidirectional drag after the inflated film balloon is presented. First, a hybrid folding method involving a closed 3D spherical shrinkage into a star-shaped compaction is proposed, which realizes a dense cube shape with zero-line width and variable thickness folding. Then, the air resistance effect in the low earth orbit is an important factor affecting the orbital height of satellite debris according to the atmospheric perturbation theory in drag balloon design, and NRLMSIE-00 model is used to predict the orbital atmospheric density. Based on the assumption of a small deformation spherical shell, the ultimate load regarding the spherical instability of the film drag balloon is analyzed, when the balloon is subjected the maximum air resistance at the height of 200 km. The ultimate loads of the film balloon at room(20 ℃) and high temperatures(80 ℃) are compared, and a test is validated in a vacuum chamber by a film balloon. Finally, the inflated balloon dragged by the space debris is considered as the perturbed deorbit motion caused by the air resistance effect. The relationship between the surface-to-mass ratio of various space debris and the balloon diameter with the deorbit time is analyzed, as well as the relationship of the deorbit time of the drag balloon with the orbit height. [Results] Results showed that the polyimide film balloon can be used as a design for an omnidirectional drag deorbit fo

关 键 词：离轨 充气展开 薄膜球 折叠 增阻 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]