小卫星共轨式轨道转移策略

Small satellite co-orbital transfer strategy

针对小卫星与共轨目标星之间的交会问题,设计制导策略使小卫星在预期时间内与目标星相遇。利用均匀中心引力场模型,推导了一个关于两星相对运动状态和转移时间的二次方程,求解该方程能够得到固定燃料转移问题的最优推力时间和推力方向的解析解。在自由滑行段采用Lambert变轨算法代替解析算法,提出了一种改进制导算法。应用该改进制导算法进行大量仿真实验,并利用STK仿真软件对仿真结果进行验证,表明本文算法是有效的。

To deal with the rendezvous problem between the small satellite and the co-orbital target, a guidance strategy was developed to make the satellite meet the target in a desired time. A quadratic equation about the relative motion between the two satellites and the transfer time was derived using the homogeneous central gravity field model. An analytic solution to the equation can provide the optimal thrust time and thrust direction of the fuel-fixed, open-time intercept. An improved guidance algorithm was proposed by replacing the analytic method during the free-flight phase with the Lambert guidance algorithm. Simulations were conducted and their results were tested by STK software to be correct and effective.