论文部分内容阅读
本文是在协方差分析描述函数法研究的基础上,进一步探讨了统计线性化伴随法.导出了导弹非线性制导系统协方差传播方程相对应的伴随方程。然后以姿态控制系统为例,计算了在推力偏心矩、风、起始扰动角速度等随机干扰作用下的散布,研究了各种随机干扰对总的均方根值的影响,并与统计试验法、协方差分析描述函数法进行了比较,效果较好。证明由协方差分析描述函数法和伴随法相结合构成了导弹系统完整的统计性能分析,而统计线性化伴随法在研究单个随机干扰作用下的散怖更为方便、有效。
Based on the study of covariance analysis and descriptive function method, this paper further discusses the statistical linearization adjoint method, and derives the corresponding equation of covariance propagation equation of missile nonlinear guidance system. Then, taking the attitude control system as an example, the distributions under random disturbances such as thrust moment, wind and initial disturbance angular velocity are calculated. The effects of various random disturbances on the total root mean square are investigated. , Covariance analysis described the function method were compared, the effect is better. It is proved that the combination of covariance analysis and descriptive function method and adjoint method constitutes the complete statistical performance analysis of the missile system. Statistical linearization adjoint method is more convenient and effective in studying the spurious of single random disturbance.