摘要
主要研究了质心漂移对姿态稳定控制系统的影响。针对姿轨控发动机动力系统,建立了动力学和运动学模型,并利用该模型进行了理论分析和数学仿真。将理论计算结果与数学仿真结果相结合,确定了允许的质心漂移最大值。
The effect of excursion of centroid on attitude stabilizing control system is studied. According to the power system for attitude and trajectory control, dynamic model and kinematic model are set up, then theoretical analysis and numerical simulation are performed based on the models. The maximum of excursion of centroid is obtained by synthesizing the results of theoretical calculation and numerical simulation.
出处
《导弹与航天运载技术》
北大核心
2009年第4期11-13,共3页
Missiles and Space Vehicles
关键词
质心漂移
姿态控制
理论计算
数学仿真
Excursion of centroid
Attitude control
Theoretical calculation
Numerical simulation
