摘要
主要研究了角速度零位误差对比例导引制导精度的影响,首先建立了比例导引制导回路的简化模型,并得到了简化模型的解析解。根据解析解定义了导弹无量纲位置误差和无量纲法向加速度,并分析了比例导引系数对以上两个无量纲量的影响。详细研究了更复杂的比例导引制导回路模型,给出了在比例导引制导回路各参数取不同值的情况下,导弹无量纲法向加速度随时间的变化曲线。最后运用仿真手段研究了在比例导引制导回路各参数取不同值的情况下,导弹无量纲脱靶量随无量纲末制导时间的变化情况,仿真结果表明:角速度零位误差引起的无量纲脱靶量随着无量纲末制导时间的增加而收敛。
The effect of the zero position error of angular rate on the precision of proportional navigation was mainly studied. Firstly, the simple model of proportional navigation and homing guidacne loop was built, and then the analytic solution of the simple model was abtained. Non-dimensional missile position error and non-dimensional missile lateral acceleration were deirmed from the analytic solution. The influence of the value of proportion navigation coefficient on this two non-dimensional variables was analysed. The more complicated model of proportional navigation and homing guidance loop was studied, then the curve of non-dimensional missile lateral acceleration changing with time was got when the parameters of proportional navigation and homing guidance loop had different values. At last, the characteristic of missile non-dimensional miss distance varying with non-dimensional terminal guidance time was studied by using simulation method when the parameters of proportional navigation and homing guidance loop had different values. Simulation results show that non-dimensional miss distance introduced by angular rate converges with the non-dimensional terminal guidance time increases.
出处
《红外与激光工程》
EI
CSCD
北大核心
2011年第11期2255-2260,共6页
Infrared and Laser Engineering
基金
国家自然科学基金(60672154)
关键词
零位误差
比例导引
制导回路
脱靶量
zero position error
proportional navigation
guidance loop
miss distance
