某导弹燃油调节器的建模及仿真研究

Research on Modeling and Stimulating of the Fuel Control System of Certain Missile

该文针对某导弹燃油调节器的组成、功能、原理进行了详细分析,以流量连续方程和力平衡方程为基础,采用线性小变量处理的方法建立元部件和系统的数学模型。用MATLAB提供的Simulink进行仿真、优化,选取Runge-Kutta(4,5)算法,变步长积分。并由数学模型和仿真结果对其稳定性和动态特性进行分析、计算。在此基础上,对反映燃油调节器主要型能指标的油门移动速度也进行了单独仿真研究。

This paper is to analyze in detail the composing, functioning and principle of the fuel control system of certain kind of missile. Based on the flux continuum equation and power balance equation, this paper adopts the measure of linear little variable to establish the arithmetic model of its components and system. Simulink of MATLAB is used in the stimulating and optimizing with changeable step integral and Runge-Kutta(4,5) arithmetic. The arithmetic model and stimulating result is referred to analyze and calculate its stability and dynamic feature. Furthermore, the throttle movement speed is stimulated upon the analysis of related parameters.