CAJ | 학술논문

卫星编队与轨道机动是完成在轨监视与捕获等空间任务的关键技术.针对追踪航天器在相对目标航天器的绕飞过程中特殊构型的编队飞行问题,提出了三种特殊的编队构型机动方案;针对近距离轨道逼近问题,分析了同平面轨道变轨策略和轨道转移能耗最优化问题,在此基础上给出了三脉冲升降轨机动方法,并可以根据需要将其扩展为 N 脉冲机动.以目标星运行轨道高度780 km 为例进行仿真分析,结果表明平行四边形编队中追踪星在各交点处完成变轨所需的速度脉冲向量分别为0.1172 m/s、0.1843 m/s,而花形编队和菱形编队中追踪星在各交点处完成变轨所需的速度脉冲向量均为0.1978 m/s,从而验证了所提出方法的有效性.
위성편대여궤도궤동시완성재궤감시여포획등공간임무적관건기술.침대추종항천기재상대목표항천기적요비과정중특수구형적편대비행문제,제출료삼충특수적편대구형궤동방안;침대근거리궤도핍근문제,분석료동평면궤도변궤책략화궤도전이능모최우화문제,재차기출상급출료삼맥충승강궤궤동방법,병가이근거수요장기확전위 N 맥충궤동.이목표성운행궤도고도780 km 위례진행방진분석,결과표명평행사변형편대중추종성재각교점처완성변궤소수적속도맥충향량분별위0.1172 m/s、0.1843 m/s,이화형편대화릉형편대중추종성재각교점처완성변궤소수적속도맥충향량균위0.1978 m/s,종이험증료소제출방법적유효성.
Satellites formation and orbit maneuver are key techniques of the space missions such as orbital monitoring, orbital capture. Aiming at the formation flight problem of special configuration when the tracking spacecraft were flying around the target spacecraft, three special formation configurations were given. To solve the problem of close orbit approximation, the strategy of the plane orbital transfer and the energy consumption optimization problem of the orbital transfer were analyzed. The orbit ascend and descend method of three-pulse on that basis was also given, and it can be extended to N-pulse maneuver. Simulations were made when the orbit altitude of target spacecraft was 780 km, and the results show that the needed speed pulse vectors are 0.1172 m/s and 0.1843 m/s respectively when the tracking spacecraft transfers at the nodes in the parallelogram formation, while the needed speed pulse vector is 0.1978 m/s in the flower shape or diamond formation. The results also verify the effectiveness of the proposed method.