论文部分内容阅读
本文主要针对一种带有可调喷注器的双组元变推力液体火箭发动机(BYF-03)在研制过程中曾出现过的低频振荡现象,分析其响应特性和稳定性,在分析过程中,建立了发动机系统的数学模型,并用Gear法进行了大量的数值计算.分析结果表明,这类变推力发动机,电磁阀工作周期T是发动机系统稳定性的决定性因素;弹簧预压量δH,O对系统的稳定性也有很大影响;而控制电路增益K_B则对系统的响应性能影响很大.经过计算找到了一组参数可使该发动机系统不发生低频振荡.这些结果得到了发动机热试车证实.
This paper mainly focuses on the phenomenon of low-frequency oscillation in the development of a two-component variable-thrust liquid propellant rocket engine (BYF-03) with an adjustable injector, and analyzes its response characteristics and stability. During the analysis , The mathematical model of the engine system is established and a large number of numerical calculations are made by Gear method.The analysis results show that the working cycle T of such variable thrust engine and solenoid valve is the decisive factor of the stability of the engine system. The stability of the system also has a great impact; and the control circuit gain K_B has a great impact on the system’s response performance.After calculation to find a set of parameters can make the engine system does not occur low-frequency oscillation.These results obtained the engine hot test confirmed .