摘要
文中研究了飞行器结构弹性振动和主动式喷气三轴稳定姿态控制系统耦合的数学模型和仿真方法,并以某空间飞行器轨道机动过程中俯仰通道为例,考虑控制系统的非线性特性,分析了弹性振动对姿态控制精度、响应时间以及系统稳定性的影响。
The coupling mathematical model and simulation method of flight vehicle structure elastic vibration and active reaction jet attitude control system ware studied,with taking the pitch channel of a certain spacecraft as an example. With the nonlinear response of the control system considered,influences from the elastic vibration and the attitude con- trol precision,the response time as well as the system stable ware analyzed.
出处
《弹箭与制导学报》
CSCD
北大核心
2006年第S8期712-714,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
喷气控制
弹性振动
非线性系统
相平面法
reaction jet control
elastic vibration
nonlinear system
phase plane method
