摘要
针对小行星探测任务,提出一种基于滑模控制的轨迹跟踪小行星软着陆动力下降段燃料最优制导律,并完成设计与数值仿真验证。首先,建立探测器动力学模型与小行星引力场模型;然后,通过凸优化方法完成探测器燃料最优轨迹规划,设计滑模控制轨迹跟踪制导律完成燃料最优轨迹跟踪,末段轨迹采用零控位移偏差/零控速度偏差(ZEM/ZEV)制导律,使探测器尽量垂直着陆于目标位置,保证软着陆安全性。最后,在考虑重力加速度不确定性与探测器初态偏差的条件下进行仿真,验证制导律的鲁棒性。结果表明:该制导律具有精度高、节省燃料、鲁棒性强的优点。
An optimal guidance law for the asteroid soft-landing fuel based on trajectory tracking is proposed based on the sliding mode control method.The guidance is designed and verified by numerical simulation.First,the dynamic model for a probe and the gravitational field model for an asteroid are established.Then,the optimal trajectory planning of the probe fuel is completed through the convex optimization method,and the trajectory tracking guidance law of the sliding mode control method is designed to complete the optimal fuel trajectory tracking.The zero-effort-miss/zeroeffort-velocity(ZEM/ZEV)guidance law is used in the final trajectory to make the probe land as vertically as possible at the target position to ensure the safety of the soft-landing.Finally,simulation is carried out with the consideration of the uncertainty of gravity acceleration and the initial state deviation of the probe to verify the robustness of the guidance law.The results show that the guidance law has the advantages of high accuracy,fuel saving,and strong robustness.
作者
郭子康
唐超
王鹏宇
郭延宁
GUO Zikang;TANG Chao;WANG Pengyu;GUO Yanning(School of Astronautics,Harbin Institute of Technology,Harbin 150001,Heilongjiang,China;Beijing Institute of Aerospace Systems Engineering,Beijing 100076,China)
出处
《上海航天(中英文)》
2025年第6期36-47,共12页
Aerospace Shanghai(Chinese&English)
基金
国家自然科学基金资助项目(62473110)
空间智能控制技术全国重点实验室基金资助项目(HTKJ2025KL502014)。
