大型航天器无控飞行再入时间短期预报的轨道摄动方法研究  

Research on Short-Term Orbit Prediction Method for Large-Scale Spacecraft at End of Its Life During Uncontrolled Flight

作　　者：高兴龙[1,2] 李志辉[1,3,4] 陈钦 丁娣[1,5] 彭傲平[3] GAO Xinglong;LI Zhihui;CHEN Qin;DING Di;PENG Aoping(State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;National Laboratory of Computational Fluid Dynamics,Beijing Pioneering Innovation Center,Beijing 100191,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心设备设计及测试技术研究所,绵阳621000 [3]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 [4]北京前沿创新中心国家计算流体力学实验室,北京100191 [5]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《载人航天》2020年第5期566-573,共8页Manned Spaceflight

基　　金：国家重点基础研究发展计划(2014CB744100);国家自然科学基金(11902331,11325212)。

摘　　要：针对寿命末期大型航天器临近再入前轨道衰降受到跨流域多尺度非平衡环境下气动力/力矩影响显著的问题,基于体坐标系下的气动力和力矩分量,建立了航天器轨道-姿态动力学摄动模型;结合航天器再入跨流域空气动力学统一计算理论与数值模拟手段,提出了大型航天器无控飞行轨道衰降过程气动特性一体化快速算法。基于地心惯性坐标系气动融合轨道动力学方程数值积分方法对航天器的轨道姿态摄动模型进行了外推计算,结合无迹卡尔曼滤波方法对外测轨道星历观测数据初值误差和模型误差进行了滤波。针对250~120 km高度范围的大型航天器短期轨道衰降变化进行仿真预测,对比了外测轨道星历数据,结果表明:本文提出的经卡尔曼滤波误差分析的轨道摄动模型方法对寿命末期大型航天器短期轨道预报具有较强的模拟能力与有效性,有助于推动近地轨道空间目标气动融合轨道数值预报领域发展。The perturbation of aerodynamic forces can significantly affect the orbit decay of large-scale spacecraft at the end of its life before re-entering the atmosphere.The six degree-of-freedom orbit-attitude dynamic model was built on the basis of the aerodynamic forces and moments under the body frame.Then considering the aerodynamic characteristics covering various flow regimes,the unified fast computing technique for aerodynamic components was built.Based on the orbit-attitude perturbation model,the orbit propagation of the target spacecraft was proposed using the numerical integral method.Meanwhile,the initial orbit determination error and the model’s error were filtered by the Unscented Kalman Filter method.Finally,the short-term orbit decay of 250~120 km altitude large-scale spacecraft was simulated and predicted.Comparing with the observed orbit ephemeris data,the results demonstrated that the methodology proposed in this paper was effective.The research can help to improve the short-term orbit prediction ability of large-scale spacecraft at end of its life and promote the development of numerical prediction of aerodynamics combing orbit for space objects at low earth orbit.

关 键 词：无控航天器 轨道预报 无迹卡尔曼滤波方法 跨流域空气动力 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]