摘要
为简化中等精度捷联惯导系统的标定步骤,缩短发射准备时间,提高部队反应速度和保障效率,针对实际工程使用的33个参数的惯导系统误差模型的标定问题进行了方案研究。提出了一种适用于整弹不开箱条件下新的7位置标定方法,并对由此带来的转动空间限制问题进行了相应的考虑,有效解决了传统多位置、多速率测试方法难于运用于整弹条件下的惯导误差标定的问题。在考虑存在有转动定位误差为0.1°的情况下,对标定方法进行了相应仿真研究。仿真结果表明采用上述方法可以有效解算出33个误差系数,且得到的误差系数相对误差在7%的范围之内,可以满足部队的一般战斗保障需求,从而验证了方案的实际可行性。
To simplify the calibration process of mid-accurate strapdown inertial system and shorten the preparing time before launch, an error model with parameters using in engineering was studied. A new method of calibrating in 7 positions was introduced based on the whole missile without opening box. Considering the space restriction, the method can solve the problem that the classic multi-position and multi-rate testing method can not be easily implemented in the error calibration based on the whole missile. Assuming there was 0.1° rotating orientation error, a simulation was carried out using the method. The simulation result illustrates that 33 parameters can be solved while the relative error of those parameters is within 7%. Therefore the simulation validates the feasibility of the method.
出处
《中国惯性技术学报》
EI
CSCD
北大核心
2009年第1期33-36,41,共5页
Journal of Chinese Inertial Technology
关键词
误差模型
不开箱
误差标定
小姿态
空间约束
error model
without opening box
error calibration
small gesture
space-limited
