液体火箭发动机自动控制系统的过渡过程研究

以能多次启动的某泵压式液体火箭发动机的自动控制系统为研究对象,构造了液体火箭发动机自动控制系统的物理模型,并对其建立了非线性的数学模型.针对可能发生的干扰形式,以阶跃形式输入,进行了单干扰状态下动态特性模拟,计算方法采用小偏差法.通过对数学模拟的结果与从试验获得的数据进行比较,发现:当干扰信号在小范围内变化时,所建数学模型较精确合理,计算方法满足模拟要求.该工作对控制参数的优化选择和合理采用控制系统等具有一定的参考意义.

Study on Transient of Automata System for Liquid Rocket Engine

A physical model of the automatic control system of a pump fed Liquid Rocket Engine (LRE) is constructed, for which a nonlinear mathematical model is built. Considering the interfering modalities probably happening and input with step form, the dynamic characteristic in each interfering status is simulated by using the small deviation calculating method. Comparison between the computed results and the test data shows that: when the interfering signals are varied within small bound, the mathematical model is relatively accurate and the calculating method can meet the simulating requirement. This work has signifcance for optimizing control parameters and reasonably adopting control system.