基于显式制导的月地返回轨道中途修正研究
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摘要
月地返回轨道存在各种摄动误差,终端约束复杂,有必要对其进行中途修正研究。显式制导法通过二体轨道与精确轨道之间的差别进行多次迭代求解给定时刻所需的修正速度。文章利用显式制导法,采用月球段及地球段分段进行中途修正的策略,给出了基于分段落点预报显式制导的月地返回轨道中途修正方案。该方案无需计算雅克比矩阵,算法简单、计算快速、实用性强,能满足再入点参数要求。算例仿真与蒙特卡洛仿真验证了该方案的适用性。
The research on the midcourse correction of Moon-Earth return trajectory is necessary,as nominal orbit is perturbed by several disturbance sources and boundary constraints is complicated.The solution of characteristic velocity was got through the explicit guidance method by using the iterations algorithm based on the difference between the two-body orbit and precise trajectory.As the midcourse correction strategy was divided into moon-section and earth-section,the explicit guidance correction schemes of Moon-Earth return trajectory based on subsection location points prediction was presented.The scheme can satisfy the reentry point parameters constraints and can be used widely in practice,as the algorithm is simplified to overcome disadvantages of the differential correction algorithm which requires a numerical Jacobian matrix.Finally,the adaptability of the scheme was validated by numerical simulation and Monte-Carlo simulation.
The research on the midcourse correction of Moon-Earth return trajectory is necessary,as nominal orbit is perturbed by several disturbance sources and boundary constraints is complicated.The solution of characteristic velocity was got through the explicit guidance method by using the iterations algorithm based on the difference between the two-body orbit and precise trajectory.As the midcourse correction strategy was divided into moon-section and earth-section,the explicit guidance correction schemes of Moon-Earth return trajectory based on subsection location points prediction was presented.The scheme can satisfy the reentry point parameters constraints and can be used widely in practice,as the algorithm is simplified to overcome disadvantages of the differential correction algorithm which requires a numerical Jacobian matrix.Finally,the adaptability of the scheme was validated by numerical simulation and Monte-Carlo simulation.
引文
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[2]谢剑锋.地月转移轨道中途修正优化分析[C].全国第十二届空间及运动体控制技术学术年会,桂林,2006.
[3]杨维廉,周文艳.嫦娥一号卫星地月转移轨道中途修正分析[J].空间控制技术与应用,2008,34(6):3-7.YANG WEILIAN,ZHOU WENYAN.Analysis on midcourse correction of translunar trajectory for CE-1[J].Aerospace Control and Application,2008,34(6):3-7.
[4]郗晓宁,曾国强,任萱,等.月球探测器轨道设计[M].北京:国防工业出版社,2001.XI XIAONING,ZENG GUOQIANG,REN XUAN,et al.Orbit design of lunar probe[M].Beijing:National Defense Industrial Press,2001.
[5]张磊,于登云,张熇.月地转移轨道中途修正方法及策略[J].航天器工程,2012,21(3):18-22.ZHANG LEI,YU DENGYUN,ZHANG HE.Method and strategy of the Moon-to-Earth trajectory midcourse correction[J].Spacecraft Engineering,2012,21(3):18-22.
[6]BATTIN R H.An introduction to the mathematics and methods of astrodynamics[M].AIAA Education Series,1987.
[7]HINTZ G R,CHADWICK C.Design and analysis techniques for trajectory correction maneuvers[C].AIAA/AAS Astrodynamics Conference,Seattle,Washington,August 20-22,1984.
[8]CHO D H,CHUNG Y S,BANG H C.Trajectory correction maneuver design using an improved B-plane targeting method[J].Acta Astronautica,2012,72:47-61.
[9]何巍,徐世杰.地月低能耗转移轨道中途修正问题研究[J].航天控制,2007,25(5):22-27.HE WEI,XU SHIJIE.Study on midcourse correction of low energy consumption earth-moon transfer orbit[J].Aerospace Control,2007,25(5):22-27.
[10]程国采.弹道导弹制导方法与最优控制[M].长沙:国防科技大学出版社,1987.
[11]周亮,胡军.基于双曲线B平面参数的快速微分修正月地返回轨道精确设计[J].航天控制,2012,30(6):27-31.ZHOU LIANG,HU JUN.Moon-Earth return trajectory precise design of fast differential correction based on B-plane parameters of hyperbola[J].Aerospace Control,2012,30(6):27-31.
[12]BREAKWELL J V.Fuel requirements for crude interplanetary guidance[J].Advances in Astronautical Science,1960,5(8):53-65.
[13]胡少春,孙承启,刘一武.日晕轨道卫星的转移轨道中途修正研究[J].空间控制技术与应用,2012,38(5):21-26.HU SHAOCHUN,SUN CHENGQI,LIU YIWU.On midcourse correction of transfer trajectory for halo orbiters[J].Aerospace Control and Application,2012,38(5):21-26.