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本文介绍一种可用于飞行器控制系统中的动力装置——变推力火箭发动机的系统方案。根据控制系统的要求,对发动机可调文氏管——喷注器系统的结构参数选择和设计,推导出数学表达式,并对这种发动机控制系统的动态性能和稳态性能加以分析。变推力液体火箭发动机,通常都是利用改变推进剂的秒流量来实现推力调节,其方案可利用喷注器流通截面的变化,或者在发动机供应系统中设置流量调节器,改变流量达到推力调节的目的。但是比较完善的方案是发动机供应系统和喷注器系统对推进剂的流量都进行调节。供应系统中的调节器用来调节推进剂的流量和组元混合比,喷注器流通截面的变化保证推进剂的喷射速度和雾化质量。供应系统中的流量调节器通常是采用可调节流量文氏管。在一般文氏管中加上一个可沿文氏管中心线移动的同心锥,调节锥的纵向移动改变文氏管的流通截面积,调节推进剂的流量。并且文氏管往往处于汽蚀状态下工作。
This article describes a system that can be used as a power plant in a control system for an aircraft - a variable-thrust rocket engine. According to the requirements of the control system, the structural parameters of the adjustable venturi-injector system are selected and designed. The mathematical expressions are derived and the dynamic performance and steady-state performance of the engine control system are analyzed. Variable thrust liquid propellant rocket engine, usually by changing the second flow of propellant to achieve thrust adjustment, the program can take advantage of injector flow cross-section changes, or in the engine supply system set flow regulator to change the flow to achieve thrust adjustment purpose. However, the more complete solution is that both the engine supply system and the injector system regulate the flow of propellant. Regulators in the supply system are used to adjust the flow rate of the propellant and the mixing ratio of the components. Changes in the flow cross section of the injector ensure the propellant injection speed and atomization quality. The flow regulator in the supply system is usually a venturi with adjustable flow. In a typical Venturi tube with a concentric cone that moves along the venturi centerline, the longitudinal movement of the cone is adjusted to change the venturi cross-sectional area to regulate the flow of the propellant. Venturi tubes often work in cavitation.