摘要
提出了一种微小探测器软着陆小行星的制导与控制策略 ,将软着陆小行星控制分解为速度方向控制和减速控制。为了控制速度方向 ,给出了一种带有终端控制项的比例导引规律 ,可以按闭环模式将探测器引向着陆点 ,并满足垂直下落的终端条件 ;为了实现无碰撞着陆 ,给出了一种减速控制规律 ,通过对理想速度曲线的跟踪 ,实现软着陆。仿真结果表明 。
A guidance and control strategy for attaching the small solar system body is presented.The small solar system body attachment control is decomposed into the velocity direction and deceleration control. To control the velocity direction, a proportional guidance law with terminal control terms is proposed. It can steer an explorer to landing site, while meeting the terminal condition of vertical descent. To soft land on the surface of the small solar system body, a deceleration control law is made. Simulation results show that a given guidance and control strategy can control the explorer soft landing.
出处
《飞行力学》
CSCD
2002年第2期35-38,共4页
Flight Dynamics
基金
"十五"国防科技民用航天预研课题
航天创新基金资助项目
