摘要
针对提高运载火箭姿态控制系统可靠性问题 ,从姿态角速度信号获取及伺服系统回路设计两方面提出了故障吸收冗余方案模式 ,对其冗余配置、工作原理、可靠性问题进行了讨论 ,并对方案可行性进行了设计分析。
To raise the reliability of attitude control system of launch vehicle, the failure elimination redundance concept mode is given for attitude angular rate measurement and servo system loop design. The redundant layout,operating priniciple and reliability of the concept are discussed. The concept feasibility is analysied.
出处
《导弹与航天运载技术》
北大核心
2001年第6期9-14,共6页
Missiles and Space Vehicles