摘要
迭代制导方法在运载火箭上升段入轨问题中已有成熟应用。本文针对空间变轨任务,提出一种适用于目标轨道为圆轨道情形的,以轨道要素为终端约束的迭代制导方法。在迭代制导方法的基础上,以推力方向矢量为控制量,推导直接以目标圆轨道的轨道要素为终端约束的边界条件,得到一种简单有效、适应大姿态角变化的迭代制导算法。通过仿真验证了改进方法的有效性和较高的入轨精度。
The iterative guidance method is maturely used in the ascent guidance problem of launch vehi- cle. An iterative guidance algorithm is presented by using the target circular orbit elements as the terminal constraints for orbit transfer problem. Based on the iterative guidance method, a concise and effective itera- tire guidance algorithm is presented by establishing the optimal control model directly in the geocentric iner- tial system, using the orient vector of the thrust as the control variable and using the target orbit elements di- rectly as the terminal constraints. The numerical simulations implemented demonstrate the effectiveness of the approach proposed.
出处
《航天控制》
CSCD
北大核心
2015年第3期34-37,共4页
Aerospace Control
关键词
空间变轨
迭代制导
最优控制
Orbit transfer
Iterative guidance
Optimal control
