空间非合作目标轨道机动特征参数检测方法  

Orbital Maneuvering Characteristic Parameters Detection Method for Space Non-cooperative Targets

作　　者：邓豪 张新 龚柏春 韩飞 宁昕[3] DENG Hao;ZHANG Xin;GONG Baichun;HAN Fei;NING Xin(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Shanghai Aerospace Control Technology Research Institute,Shanghai 201109,China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]南京航空航天大学航天学院,南京211106 [2]上海航天控制技术研究所,上海201109 [3]西北工业大学航天学院,西安710072

出　　处：《宇航学报》2025年第1期168-180,共13页Journal of Astronautics

基　　金：国家自然科学基金(12272168);空间智能控制技术全国重点实验室开放基金(HTKJ2023KL502015)。

摘　　要：针对现有空间非合作目标机动检测方法难以给出目标机动速度和准确机动时刻的难题,提出了一种基于短弧历史数据的机动特征参数检测方法。首先,建立了追踪器轨道坐标系基准的J2项摄动条件下,相对运动动力学模型和视线角测量模型。然后,设计了利用短弧相对轨道历史数据正向和反向演化交汇的机动特征参数检测方案,并建立了基于批处理最小二乘的求解算法模型,用于平滑噪声影响,获取高精度机动特征参数解。最后,对所提算法进行了数值仿真验证,并对相对轨道构型、机动量大小以及量测噪声等关键因素的敏感性进行了仿真分析。仿真结果表明,机动速度求解误差均值在0.008 m/s以内,机动时刻定位误差均值和均方差分别不超过2 s和14 s。A maneuver characteristic parameters detection method,based on short arc historical data,is proposed to address the challenge of accurately determining target maneuver speed and timing in existing non-cooperative target maneuver detection methods.Initially,a relative motion dynamics model and a line-of-sight angle measurement model are constructed under J2 perturbation conditions,with the chaser’s orbit coordinate system serving as the reference frame.Subsequently,a detection scheme for maneuver characteristic parameters is designed,utilizing forward and backward evolution convergence of short-arc relative orbit historical data.A solution algorithm model based on batch least squares is then established to mitigate noise effects and obtain high-precision solutions for the maneuver characteristic parameters.The proposed algorithm undergoes numerical simulation verification,along with a sensitivity analysis to key factors such as relative orbit configuration,maneuver magnitude,and measurement noise.The simulation results reveal that the mean error of maneuver speed estimation is within 0.008 m/s,while the mean error of maneuver timing localization is within 2 seconds,with a standard deviation of no more than 14 seconds.

关 键 词：空间态势感知 机动特征参数检测 短弧历史数据 批最小二乘 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]