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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.
In view of the rendezvous mission of near-Earth orbital orbital spacecraft, a fast and autonomous autonomous guidance algorithm based on classical orbital elements is designed. For the remote guidance of any initial latitude and longitude deviation, by establishing the relationship between latitude and longitude axis deviation, The long-range guidance segment is divided into three phases: initial orbit phase modulation and orbit adjustment.Orbit orbit coplanar correction and phase modulation motions are performed on the initial orbit, during natural orbit phase modulation and phase modulation Orbit to adjust the orbit maneuver Adjust the orbit flight phase to track spacecraft apogee and perigee height correction and re-coplanar correction All orbital maneuvers are given in the form of guide pulse, and are executed at the track special point The accurate orbit simulation verifies the feasibility of the remote fast autonomous proximity guidance algorithm.