摘要
对激光陀螺速率捷联系统作为制导系统的惯性测量设备进行了研究 ,对其数学平台的解算进行了数值仿真 ,并对制导方程采用显式形式进行了研究和数值仿真 ,对速率捷联显式制导系统的方法误差、工具误差、综合误差进行了分析和计算 。
Using laser gyro rate strapdown system as inertial measurement equipment of guidance system is researched.Arithmetic of its mathematical platform is numerical simulated.Guidance equation is studied and explicit numerical simulated.Methodical error,instrument error and composite error of rate strapdown explicit guidance system is analysied and calculated.The useful result for designing and reference is got.
出处
《导弹与航天运载技术》
北大核心
2001年第5期15-19,共5页
Missiles and Space Vehicles
