摘要
针对航天器空间变轨任务的制导问题,研究了一种适用的迭代制导算法。在传统迭代制导方法的基础上,直接在地心惯性系中建立最优控制模型,以推力方向矢量为控制量来适应大姿态角变化情形;推导直接以目标轨道要素为终端约束的边界条件,给出终端约束方程求解精度和入轨精度的关系;得到一种简单有效的基于轨道要素形式终端约束的航天器空间变轨迭代制导算法。通过仿真验证了所给制导算法的有效性,相比传统迭代制导方法其具有更强的适应性。
An adapted iterative guidance algorithm is researched for the orbit transfer mission of spacecraft. Based on the traditional iterative guidance method, we directly found the optimal control model on the geocentric inertial frame, use the orient vector of the thrust as the control variable to adapt for the significantly change of attitude angel, found the boundary conditions by using the target orbital elements directly as the terminal constraints, obtain the relationship between the accuracy of the solutions of the constraint equations and the injection accuracy, and then present a concise and effective iterative guidance algorithm using orbital elements as terminal constraints for spacecraft orbit transfer. Numerical simulations have demonstrated the effectiveness and better adaptability than the traditional method.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2015年第6期1975-1982,共8页
Acta Aeronautica et Astronautica Sinica
关键词
空间变轨
迭代制导
最优控制
轨道要素
边界条件
orbit transfer
iterative guidance
optimal control
orbital elements
boundary conditions
