关键词: 火箭发动机, 尾焰复燃, 燃烧反应动力学, 飞行时间质谱, 层流预混火焰

Abstract:

Afterburning in rocket engine exhaust plumes significantly impacts flight stability, increase the difficulty of thermal management and reduce the stealth characteristics of rocket engines. The lack of pressure-dependent characteristics in afterburning reaction kinetics models has led to significant discrepancies in the predictions of exhaust temperature, CO concentration and spectral radiation intensity across different reaction kinetics models. Therefore, the development of high-precision combustion kinetics is crucial for predicting the combustion characteristics of afterburning. Laminar premixed flames, characterized by their simple structure, could avoid the influences of turbulence on the combustion process, making them particularly suitable for combustion kinetic studies of afterburning in rocket engines exhaust plumes. Flame-sampling molecular-beam mass spectrometry (MBMS) could perform laminar premixed flame experiments within a pressure range of 2—100kPa, reproducing working conditions of rocket engines from ground level to altitudes of exceeding 10000 meters. Moreover, the concentration of combustion intermediates, including short-lived radicals, can be detected by MBMS. This method could support the development of high-precision combustion kinetics for afterburning in rocket engine exhaust plumes across wide range of pressures, thereby providing theoretical backing for enhancing the stable operation of rocket engines and improving the stealth performance of missile systems.

Key words: rocket engine, afterburning in rocket engine exhaust plumes, combustion kinetics, molecular-beam mas spectrometry, laminar premixed flame