双组元轨控发动机声腔技术方案及试验验证

作为解决小推力双组元发动机高频不稳定燃烧的主要技术途径,本文主要对发动机声腔技术方案进行了研究,研究工作包括发动机结构固有频率分析、声腔型式的选择、声腔结构方案设计及全尺寸热试验证。研究结果表明,发动机主要抑制振型为一阶切向振型和一切一纵复合振型。对发动机的工作稳定性进行了评价,验证了发动机固有频率计算结果并对三种声腔结构方案进行了比较。

The acoustic cavity technique options and test validation of the bipropellant orbit control rocket engine

High frequency combustion instability can lead to catastrophic failure of the engine structure, and it is the premise of engine design to make sure the engine works stably. As a main technical approach to solve high frequency combustion instability of the low thrust bipropellant rocket engine, the acoustic cavity technique options of the engine were studied. It included the analysis of engine's natural frequency, the selection of the acoustic cavity forms, the scheme design of the acoustic cavity, and the validation of the hot test. In the test, the engine's stability was evaluated, and the calculated result of the engine's natural frequency was validated, the best one was selected among three acoustic cavity structure schemes.