摘要
针对月球上升器主动段制导中面临的上升器实际参数与制导计算机中存储参数不一致的问题,研究并提出PEG参数自适应估计的方法.通过分析,将对PEG制导有影响的参数如质量、质量流量、比冲、推力等转化为两个参数vex和τ,并利用加速度计输出对其进行估计.最后通过对使用参数自适应估计的PEG和未使用参数自适应估计的PEG的对比仿真,验证了PEG参数自适应估计的必要性和有效性.
An adaptive parameter estimation method during PEG（ powered explicit guidance） is proposed to solve the difference between true parameters of lunar ascent body and guidance parameters saved in guidance computer. Some parameters that have an influence on PEG are transferred to two parameters vex and 7, including mass, mass flow rate, specific impulse, force and so on. Based on accelerometer out- put, the parameters can be estimated. Finally the necessary and validity of the method are proved via comparing the PEG simulation results respectively with adaptive estimated parameters and the original pa- rameters.
出处
《空间控制技术与应用》
CSCD
北大核心
2015年第5期28-32,共5页
Aerospace Control and Application
