摘要
研究Gauss伪谱法(GPM)在液体运载火箭抛罩结束到入轨飞行段制导律设计中的应用性。在每一个制导周期内,采用高效高精度数值轨迹优化方法计算当前制导周期内的制导律。通过合理选择非线性规划问题的基点数量和制导周期,节省制导方法计算时间。将基于伪谱法的制导方法与运载火箭中使用的迭代制导方法进行对比,在保证同等入轨精度的条件下,该方法对于复杂约束问题处理方法更为便捷,满足在线制导的需求。同时仿真表明,该方法能够有效应对各种偏差,是比较接近工程应用的一种方法。
The study conducts an application research on the guidance law design of the ascent trajectory for a launch vehicle based on the Gauss pseudo-spectral method（GPM）.During each period,high efficiency and high precision trajectory optimization numerical methods are used to design the current guidance law.Through making appropriate choices about the number of nodes and the period of guidance,this method is not only to reduce the calculation time,but also to solve the constrained problem rapidly.Compared to the iterative guidance method,the GPM guidance method is much more easily to deal with the constrained problem under the same orbit injection precision.Simulations indicate that this method can also effectively deal with a variety of deviations,so it is very closer to the engineering application.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2017年第3期262-269,共8页
Journal of Astronautics
关键词
伪谱法
实时在线制导
轨迹优化
非线性规划(NLP)
Pseudo-spectral method
Real-time online guidance
Trajectory optimization
Nonlinear programming（NLP）
