考虑轨控调姿的共面椭圆轨道寻的交会

Coplanar Elliptical Rendezvous Considering Attitude Adjustment in Homing

在交会对接寻的段,为了保证自主测量导航设备的连续跟踪和追踪航天器飞行姿态的稳定,要求寻的段尽量采用水平脉冲进行控制,使对地定向的追踪航天器在寻的轨控期间尽量不调姿或调整的姿态角尽量小。本文考虑轨控前调姿的航天器两脉冲寻的交会问题,提出了轨控调姿定量指标并给出了物理解释和数学定义。根据轨控调姿位置和次数不同,将问题分为首脉冲不调姿、末脉冲不调姿、两次均不调姿和两次均调姿等4类。对于前3类问题,提出迭代求解算法;对于第4类问题,提出非线性规划求解算法。最后,将调姿指标和特征速度的等值曲线叠加,提出了"交会参数设计图",可以快速直观地筛选出满足期望指标的交会参数集,辅助交会策略的制定。仿真结果验证了本文提出方法的有效性。

In the homing phase of spacecraft rendezvous and docking, in order to ensure a continuous tracking of the onboard navigation devices and to ensure a stable flight attitude of the chaser, horizontal impulses are needed as far as possible, so that the earth-orientated chaser does not tune or adjusts the at- titude angle as small as possible during homing orbital control. This paper introduces an orbital maneu- ver attitude adjusting quantification index and gives its physical explanation and mathematic definition. According to the position and the number of times of attitude adjustment, the two-impulse rendezvous homing problem is divided into four types of cases, namely, the first maneuver without attitude adjust- ment, the last maneuver without attitude adjustment, the neither maneuver with attitude adjustment and the both maneuvers with attitude adjustment. Two methods to solve the above problems considering the attitude adjusting quantification index are developed. One is the iterative method applied to the first three cases, and the other is the nonlinear programming method applied to the fourth case. Four exam- ples are calculated, and the results show that the two developed method are correct. Finally, when the contour lines of the attitude adjusting quantification index and the impulsive consumption are over- lapped, the rendezvous parameter selecting map is obtained, which is instructive on rendezvous parame- ter selecting.