固体火箭发动机不稳定燃烧时平均压力下降的原因探索

INVESTIGATION ON THE DECREASE OF AVERAGE PRESSURE UNDER UNSTABLE COMBUSTION IN SOLID PROPELLANT ROCKET ENGINE

关键词:  振荡燃烧  固体火箭发动机

Key words:  Oscillating burning  Solid rocket engine

摘要:

本文提出声湍流概念,指出声湍流引起的能量输运会降低经受适当振幅的推进剂的平均燃速,从而解释了不稳定燃烧推进剂平均压力的下降.本文提出的理论与Morita的实验结果在定性上是一致的,而实际发动机计算与实验结果的比较也证实了本文提出理论的正确性.

Abstract:

A new concept known as "acoustic turbulence" is presented in the paper. It is pointed out that energy transportation caused by "aconstic turbulence"may decrease the burning rate of solid propellant while moderate oscillating combustion occurs. This explains the decresing of average pressure under unstable combustion in solid propellant rocket engine. The theory agrees with the Morita’s experiments qualitatively and is further confirmed by the comparing of calculation with test results in a real rocket engine.