航天飞机上升与轨道过渡段制导-导航控制  

GUIDANCE-NAVIGATION CONTROL OBOUT ASCENT STAGE AND ORBITAL TRANSITION STAGE OF A SHUTTLE

作　　者：张谦[1] 

机构地区：[1]北京航天自动控制研究所

出　　处：《航天控制》1990年第4期14-21,共8页Aerospace Control

摘　　要：本文分析了航天飞机上升与轨道过渡飞行阶段的制导-导航控制装置及其分系统,并介绍了冗余系统数据选取办法。描述了四框架惯性平台框架配置与运载火箭姿态角的关系、工具误差模型与其修正方框图。最后,介绍了航天飞机制导-导航控制系统的可靠性设计。This paper analyses the guidance-navigation control device with its subsystemwhich is used in the ascent stage and the orbital transition stage of a shuttle, presents a methodused to choose data for a redundant system, describes the relationship between the configura-tion of afour-gimbal inertial platform and the attitude angle of a rocket, the error model ofthe instruments and its correction block diagram. Finally, it introduces reliability design aboutthe guidance-navigation system of the shutlle.

关 键 词：航天飞机 制导 轨道 导航 控制系统 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]