摘要
提出了一种新的使用变推力火箭发动机实现月球定点软着陆制导的优化方法。在软着陆加速度抛物线(即二次函数)变化的条件下,通过一组代数方程连接初始条件和终端条件,避免了求解两点边值问题的迭代计算。给出了瞬时位置速度状态参数以及需要推力加速度、推力和秒流量的计算公式,并通过调整总飞行时间和着陆点位置实现了燃料消耗最小的优化处理。算例结果证明了这种方法的可行性和有效性。
A new optimization method for lunar soft landing guidance with variable thrust is presented. The soft-landing acceleration is designed to vary in a 2-degree polynomial. Then the initial and end parameters are connected through a set of algebraic equations. This makes it easier to solve the two-point boundary value problem （ TPBVP）. On the basis of obtaining the instantaneous position and velocity, the formulas to compute needed thrust are provided. The soft-landing trajectories of lunar probes are optimized through the selection of flight time and the landing site. The simulation results show that the method is feasible and effective.
出处
《航天控制》
CSCD
北大核心
2008年第5期22-25,92,共5页
Aerospace Control
关键词
月球探测
软着陆
制导
优化
Lunar exploration
Soft landing
Guidance
Optimization
