摘要
运载火箭二级飞行段主机推力、游机推力、综合比冲、质量流量、火箭二级飞行初始质量参数间存在交联关系,不能同时进行辨识。采用四步骤辨识方法,以整流罩抛离激励时刻为分界点分别使用输出误差法,利用抛罩产生的火箭质量突变信息求解出推进剂质量流量,进而得到其它参数。仿真结果验证了方法的有效性。
The parameters of second stage of a launch vehicle,including main-engine thrust,vernier engine thrust,integral specific impulse,flow rate and the initial mass,are related in the flight dynamics,which can not be identified simultaneously.According to a four-step approach,maximum likelihood method is applied respectively based on before and after data of payload fairing discarding,the generated mass discontinuity due to fairing discarding is utilized to identify flow rate,other parameters could be got accordingly.Simulation results validate the method.
出处
《导弹与航天运载技术》
北大核心
2010年第4期6-9,共4页
Missiles and Space Vehicles
关键词
运载火箭
参数辨识
极大似然法
Launch vehicle
Parameter identification
Maximum likelihood method
