摘要
分析了高动态环境中导弹捷联惯导系统(SINS)圆锥误差形成的原因。研究了由陀螺频带不足、量化误差和安装误差,以及姿态更新率过低造成的圆锥误差。给出了计算公式,并在一定条件下计算了误差的大小。分析结果表明,不能正确感测运载体的角运动和姿态更新率过低是引起圆锥误差的主要因素。
The causing of conic error for missile strapdown inertial navigation system under high dynamic environment was discussed in this paper. The conic errors produced by frequency band narrow, quantization error, and installation error of gyro and low attitude update rate were analyzed. The computation equations were given, and the errors were calculated under different conditions. The analysis results showed that angular motion of carrier could not be sensed and attitude update rate was too low were the two main causes of conic error.
出处
《上海航天》
北大核心
2005年第2期1-5,共5页
Aerospace Shanghai
关键词
导弹
捷联惯导系统
圆锥误差
陀螺
频带
量化误差
安装误差
Missile
Strapdown inertial navigation system
Conic error
Gyro
Frequency band
Quantization error
Installation error
