液体推进剂导弹全动力系统稳态故障仿真(一)

Simulation of Steady-state Fault for Whole Liquid Propellant Missile Power System

为了对液体推进剂导弹动力系统进行稳态故障分析、仿真、检测、诊断以及研制箭载监控系统,必须建立其全系统稳态故障模型。通过对动力系统稳态工作过程,特别是自生增压系统的动力学分析、故障特性分析、故障因素的作用机理的分析、故障因素的引入方法研究等,依据某导弹动力系统的实际结构,完整地建立了该导弹动力系统的全系统稳态故障模型方程。与单纯的发动机系统模型相比,该模型能够模拟飞行状态的稳态故障,能更全面更好地分析动力系统的稳态故障特性。

In order to analyze, simulate, detect, diagnose steady-state fault and develop onboard monitoring system, the steady-state fault model of the whole power system of liquid propellant missile mast be established. Based on the dynamic analysis of steady-state working of power system, especially the analysis of dynamics, failure characteristics, acting mechanism of failure factor, and the study of introduced approach of fault factor for the spontaneous pressurization system, according to the actual structure of the liquid missile power system, the steady-state fault model of the whole power system of liquid missile is integrallty established. Contrasted with single engine system model, this model could simulate steady-state fault of whole power system of flight phase. The steady-state fault characteristics of power system could be better and roundly analyzed by using this model.