地地导弹快速自对准方法研究——消除航向效应影响的方法  

Research on Rapid Auto-aligning Method——The Method to Relieve the Influence of Heading-effect

作　　者：肖正林[1] 钱培贤[1] 

机构地区：[1]第二炮兵工程学院,西安710025

出　　处：《航天控制》2006年第3期13-16,共4页Aerospace Control

摘　　要：讨论了消除惯导平台航向效应对地地导弹多位置自对准精度影响的方法。惯导平台初始方位相同时航向效应重复性好,根据这个特点设计了消除航向效应影响的两位置自对准方法。首先利用陀螺漂移历史数据粗略估计方位,并据此转动弹体将平台转到航向效应标定时的初始方位。然后介绍了该方法实现自对准的步骤。最后讨论了通过转动弹体实现位置精确转换的方法。The method is discussed to reduce the azimuth error caused by the heading-effect of the inertial guidance platform when multi-position auto-aligning method adopted by ground-to-ground missiles. The repeatability of heading-effect is well when the platform is at the same initial direction. According to this character, the method to relieve the influence of heading-effect is designed. Firstly, the coarse azimuth is estimated according to the past drift of the gyro, and the platform is rotated to the initial direction when the heading-effect is calibrated through the rotating of missile body. Then two-position auto-aligning process is discussed also. Finally, the precise position-transforming method through the rotating of missile body is discussed.

关 键 词：自对准 航向效应 惯性制导系统 地地导弹 

分 类 号：V241.622[航空宇航科学与技术—飞行器设计] V241.614