针对近地近圆轨道航天器交会任务,设计了基于经典轨道要素的远程快速自主制导算法.对于任意初始纬度幅角偏差的远程导引,通过建立纬度幅角偏差与半长轴偏差的关系,将远程导引段分为初始轨道飞行、调相轨道飞行和调整轨道飞行3个阶段.初始轨道飞行进行轨道共面修正和调相机动;在调相轨道飞行期间,进行自然调相以及调相轨道到调整轨道的机动;调整轨道飞行阶段进行追踪航天器的远地点高度和近地点高度的修正,以及再次共面修正.所有变轨机动都以制导脉冲的形式给出,并都在轨道特殊点执行.精确轨道仿真验证了远程快速自主接近制导算法的可行性.%A fast autonomous guidance algorithm was designed based on classical orbital elements for spacecraft far range rendezvous phasing in near-circular orbit.For arbitrary initial argument of latitude difference,the phasing maneuver was divided into three stages—the initial orbit,the phasing orbit and the adjusting orbit according to the relationship of argument of latitude difference and semi-major axis difference.Coplanar orbital correction and phase maneuvering were done in the initial orbit.In the phasing orbit,the argument of latitude difference was adjusted naturally because of the semi-major axis difference,and then the orbit maneuver from the phasing orbit to the adjusting orbit was implemented.In the adjusting orbit,the apogee altitude and the apogee altitude of chase spacecraft are adjusted to the same as those of target spacecraft at first.Furthermore,a coplanar orbital correction was done again to eliminate the cross-track difference.All orbital maneuvers were given as guidance impulses and implemented in the orbital special points.Precise orbital simulation results show that the fast autonomous guidance algorithm for far range phasing maneuvers is feasible.
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