摘要
针对采用惯性制导的弹道导弹,开展速率捷联惯导系统工具误差计算与补偿研究。给出速率捷联惯导系统的测量模型和工具误差模型,推导了加速度计和陀螺仪的工具误差补偿公式,并进行了仿真计算。根据仿真结果,分析了各工具误差系数偏差对导弹落点精度的影响,证明了补偿算法的有效性,为捷联惯导系统工具误差补偿和提高弹道导弹制导精度提供理论依据。
Focused on the ballistic missile using inertial guidance, the calculation and compensation for instrument error of rate strapdown inertial navigation system was researched. The mathematical model of inertial measuring and instru- ment error was established, the compensation formula of instrument error for accelerometer and gyroscope was de- duced, and simulation calculation was conducted. On basis of simulation results, the effect of instrument error coeffi- cient deviation on the impact point deviation was analyzed, and the effect of the compensation approach was validated. All those can provide theoretic reference for error compensation and guidance precision improvement of strapdown inertial navigation system.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第6期1-5,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家863计划项目(2007AAX02503)资助
关键词
速率捷联惯导系统
工具误差
误差补偿
落点精度
rate strapdown inertial navigation system
instrument error
error compensation
impact point accuracy
