基于分段瞄准点预报显式制导的月地返回轨道中途修正研究
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摘要
显式制导法算法简单,计算快速,使用灵活,实用性强,可运用于月地返回轨道的中途修正研究.基于瞄准点的显式制导法在得到瞄准点预报的前提下,利用二体模型计算修正点到瞄准点所需的修正速度作为多体模型下修正点到标称落点的修正速度.根据此方法,采用月球段及地球段分段进行中途修正的策略,给出了基于分段瞄准点预报显式制导的月地返回轨道中途修正方案.最后,算例仿真及蒙特卡洛仿真验证了该方案的适用性,得出了该方案的优势.
The explicit guidance method can be used in the research of the midcourse correction of Moon-Earth return trajectory,as the algorithm is simple,computationally fast and the thought is widely employed in practice.On the premise that the aim point is predicted,the velocity increment needed from the correction point to aim point is computed using the two-body model to replace the one needed from correction point to nominal location point under the multi-body model.According to this method,the explicit guidance correction scheme of Moon-Earth return trajectory based on subsection aim point prediction is presented,while the midcourse correction strategy is divided into moon-section and earth-section.Finally,the adaptability of the scheme is validated by example simulation and Monte-Carlo simulation and the advantages of thd scheme are stuted.
The explicit guidance method can be used in the research of the midcourse correction of Moon-Earth return trajectory,as the algorithm is simple,computationally fast and the thought is widely employed in practice.On the premise that the aim point is predicted,the velocity increment needed from the correction point to aim point is computed using the two-body model to replace the one needed from correction point to nominal location point under the multi-body model.According to this method,the explicit guidance correction scheme of Moon-Earth return trajectory based on subsection aim point prediction is presented,while the midcourse correction strategy is divided into moon-section and earth-section.Finally,the adaptability of the scheme is validated by example simulation and Monte-Carlo simulation and the advantages of thd scheme are stuted.
引文
[1]周文艳,杨维廉.月球探测器转移轨道的中途修正[J].宇航学报,2004,25(1):89-92Zhou W Y,Yang W L.Mid-correction of trans-lunartrajectory of lunar explorer[J].Journal of Astronautics,2004,25(1):89-92
[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):3-7Yang W L,Zhou W Y.Analysis on midcourse correc-tion of translunar trajectory for CE-1[J].AerospaceControl and Application,2008,34(6):3-7
[4]杨维廉,周文艳.嫦娥一号月球探测卫星轨道设计[J].航天器工程,2007,16(6):16-24Yang W L,Zhou W Y.Orbit design for lunar explora-tion satellite CE-1[J].Spacecraft Engineering,2007,16(6):16-24
[5]周文艳,杨维廉.嫦娥二号卫星轨道设计[J].航天器工程,2010,19(5):24-28Zhou W Y,Yang W L.Orbit design for chang’e-2 lu-nar orbiter[J].Spacecraft Engineering,2010,19(5):24-28
[6]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):18-22Zhang L,Yu D Y,Zhang H.Method and strategy of theMoon-to-Earth trajectory midcourse correction[J].Spacecraft Engineering,2012,21(3):18-22
[7]Hintz G R,Chadwick C.Design and analysis tech-niques 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 correctionmaneuver design using an improved B-plane targetingmethod[J].Acta Astronautica,2012,72:47-61
[9]张晓文,王大轶,黄翔宇.深空探测转移轨道自主中途修正方法研究[J].空间控制技术与应用,2009,35(4):27-33Zhang X W,Wang D Y,Huang X Y.Study on the au-tonomous midcourse correction during cruise phase of in-terplanetary exploration[J].Aerospace Control and Ap-plication,2009,35(4):27-33
[10]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
[11]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):22-27He W,Xu S J.Study on midcourse correction of low en-ergy consumption Earth-Moon transfer orbit[J].Aero-space Control,2007,25(5):22-27
[12]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):27-31Zhou L,Hu J.Moon-earth return trajectory precise de-sign of fast differential correction based on B-plane pa-rameters of hyperbola[J].Aerospace Control,2012,30(6):27-31
[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):3-7Yang W L,Zhou W Y.Analysis on midcourse correc-tion of translunar trajectory for CE-1[J].AerospaceControl and Application,2008,34(6):3-7
[4]杨维廉,周文艳.嫦娥一号月球探测卫星轨道设计[J].航天器工程,2007,16(6):16-24Yang W L,Zhou W Y.Orbit design for lunar explora-tion satellite CE-1[J].Spacecraft Engineering,2007,16(6):16-24
[5]周文艳,杨维廉.嫦娥二号卫星轨道设计[J].航天器工程,2010,19(5):24-28Zhou W Y,Yang W L.Orbit design for chang’e-2 lu-nar orbiter[J].Spacecraft Engineering,2010,19(5):24-28
[6]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):18-22Zhang L,Yu D Y,Zhang H.Method and strategy of theMoon-to-Earth trajectory midcourse correction[J].Spacecraft Engineering,2012,21(3):18-22
[7]Hintz G R,Chadwick C.Design and analysis tech-niques 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 correctionmaneuver design using an improved B-plane targetingmethod[J].Acta Astronautica,2012,72:47-61
[9]张晓文,王大轶,黄翔宇.深空探测转移轨道自主中途修正方法研究[J].空间控制技术与应用,2009,35(4):27-33Zhang X W,Wang D Y,Huang X Y.Study on the au-tonomous midcourse correction during cruise phase of in-terplanetary exploration[J].Aerospace Control and Ap-plication,2009,35(4):27-33
[10]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
[11]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):22-27He W,Xu S J.Study on midcourse correction of low en-ergy consumption Earth-Moon transfer orbit[J].Aero-space Control,2007,25(5):22-27
[12]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):27-31Zhou L,Hu J.Moon-earth return trajectory precise de-sign of fast differential correction based on B-plane pa-rameters of hyperbola[J].Aerospace Control,2012,30(6):27-31