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为满足航天器在轨服务任务对悬停技术的需求,对航天器悬停构型的设计与控制问题进行了研究。通过任务航天器轨道设计得出目标航天器与任务航天器的绝对轨道关系,并用以说明悬停轨道的形成机理。结合任务航天器相对于目标航天器的相对轨迹,采用具有严格定义的相对轨道要素,对悬停轨道在目标航天器轨道平面内和平面外的构型进行描述。对“间隔式”的悬停构型脉冲控制策略进行推导,以实现任务航天器在目标航天器任意位置的长期悬停,并在此基础上分析悬停构型变化对速度脉冲的影响。最后,通过典型仿真算例验证所提方法与结果的正确性和有效性,并获得任务航天器在不同悬停轨道间转移的实现过程。研究结果完善了航天器悬停轨道的设计与控制方法,并说明了设计的悬停轨道具有可行性,能够为工程任务设计人员提供参考。
In order to meet the demand of hovering technology in on-orbit mission of spacecraft, the design and control of spacecraft hovering configuration are studied. Through the mission spacecraft orbit design, the absolute orbital relationship between the target spacecraft and the mission spacecraft is obtained and the formation mechanism of the hovering orbit is illustrated. Based on the relative trajectory of the mission spacecraft relative to the target spacecraft, a well-defined relative orbital element is used to describe the configuration of the orbiting trajectory in and out of plane of the target spacecraft. The impulsive control strategy of the hover configuration of “interval type” is deduced to realize the long-term hovering of the mission spacecraft at any position of the target spacecraft. On the basis of this, the influence of hover configuration change on the speed impulse is analyzed . Finally, the correctness and validity of the proposed method and results are verified by typical simulation examples, and the realization of the mission spacecraft transiting between different hovering orbits is obtained. The results improve the design and control methods of spacecraft hovering orbit and illustrate the feasibility of the proposed hovering orbit, which can provide reference for engineering task designers.