本文概述了空间碎片的严峻形势以及未来小卫星星座快速发展对空间碎片的影响,薄膜帆式离轨技术因其成本低、技术成熟度高、对不同规格低轨道类航天器具有很好适用性等优点,成为最易于推广应用于空间碎片减缓的技术之一;梳理了国内外在薄膜帆式离轨技术方面的最新研究进展,对薄膜帆技术最新飞行试验进行了介绍;并提出了薄膜帆式空间碎片离轨主要关键技术,包括离轨效能建模与仿真、碰撞风险分析与防护设计、薄膜帆折叠展开技术和帆面长寿命设计技术等,阐述了关键技术攻关途径和后续发展方向;最后对“金牛座”离轨帆的研制和飞行试验情况进行了介绍,比较了“金牛座”卫星理论与实际离轨曲线,得出按约50%平均阻力面积可预测姿态无控飞行器在薄膜帆作用下的离轨效果,介绍了“金牛座”离轨帆技术的后续发展。
The status of space debris and the development of small satellite constellation are introduced at first.The advantages of the space debris removal membrane sail are proposed,such as low cost,high degree of technological maturity and good applicability for all kinds of LEO satellites.The studies on membrane sail for space debris removal are summarized,as well as the latest flight tests.Key technologies associated with the de-orbit sail are presented,such as modeling and simulation technology for de-orbit efficiency,collision risk analysis and protection design,folding and deploying technology and long life membrane technology,and the approaches to solve these key problems are given.The flight test of TAURUS satellite with membrane sail is presented,and the comparison of de-orbit flight efficiency with the simulation results are given,the 50% of membrane sail area is proposed to be used as the average de-orbit sail area for satellite whose attitude is out of control,and the follow-up development of the TAURUS membrane sail is introduced.
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