基于等效迎角的气动融合轨道直接积分计算无控航天器轨道衰降研究  

Research on Orbit Decay Prediction Based on Equivalent-attitude Concept with Coupled Aerodynamics and Orbit Dynamics for Uncontrolled Spacecraft

作　　者：党雷宁 李志辉[1,2] 唐小伟[1] 梁杰[1] 彭傲平[1] DANG Leining;LI Zhihui;TANG Xiaowei;LIANG Jie;PENG Aoping(Hypervelocity Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China;National Laboratory for Computational Fluid Dynamics,Beijing 100191,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [2]国家计算流体力学实验室,北京100191

出　　处：《载人航天》2020年第4期452-458,共7页Manned Spaceflight

基　　金：国家自然科学基金(11325212,91530319);国家973计划项目(2014CB744100)。

摘　　要：针对低地球轨道航天器服役期满离轨陨落、特别是功能失效处于无控飞行的航天器轨道衰降难以模拟的问题,在航天器轨道动力学方程直接积分计算框架中,把稀薄气体动力学与轨道动力学结合起来,发展了基于跨流域空气动力精细数值模拟驱动的低轨航天器气动特性一体化快速算法,提出了无控航天器轨道衰降失稳自旋飞行姿态等效迎角模拟法,初步建立了基于等效迎角的气动融合轨道直接积分高精度计算模型。对大型航天器A受控陨落开展计算分析,验证了本文发展提出的轨道计算、气动力一体化计算方法正确性与高精度。在大型航天器B无控失稳自旋飞行轨道衰降计算分析中,得到了与外测轨道星历数据吻合一致的长弧段和短弧段预报结果,在停止外测轨道数据供给5 h内,地心惯性系位置预报偏差低于1.5 km,验证了基于等效迎角的气动融合轨道直接积分计算模型对无控航天器轨道衰降预报的合理性。The orbit decay of spacecraft in low Earth orbit is very difficult to simulate or predict,especially for the uncontrolled and spin spacecraft.To solve this problem,a rapid computational method for aerodynamic force driven by fine numerical simulation covering various flow regimes was developed.A drag modeling method of equivalent-attitude used as key variable for orbit inversion and prediction was proposed and the rarefied gas dynamics was combined with the orbit dynamics in the direct integration framework of orbit dynamic equations.The models and methods of rarefied gas dynamics and orbit dynamics presented in the paper were verified by the calculation and analysis of orbit decay of controlled spacecraft A.In addition,the orbit decay of uncontrolled and spin spacecraft B was calculated.The results showed that the equivalent-attitude drag modeling method was effective in the prediction of long and short arcs.The results of spacecraft B also showed that if measured orbit data was absent for about 5 hours,the orbit prediction error was below 1.5 km.

关 键 词：低地球轨道 稀薄气体动力学 失控自旋航天器 轨道衰降预报 等效迎角 

分 类 号：O369[理学—流体力学] V447[理学—力学]