复燃对固体火箭发动机羽流流场及红外辐射特性影响OA

To investigate the impact of the afterburning in solid rocket motor plumes on the flow field and infrared radiation characteristics,a plume model of a certain solid rocket motor was established.A density-based implicit algorithm and finite-rate model were used to calculate the plume flow field parameters.The absorption coefficients of gas components across the spectrum were obtained using a line-by-line integration model,and the infrared spectral radiation characteristics of the plume were calculated using the backward Monte Carlo method.The differences in plume flow field and radiation characteristics before and after the afterburning reaction were analyzed,and the effects of flight altitude and incoming Mach number on the afterburning plume were further investigated.The results show that the afterburning reaction increases the plume temperature and the content of major radi-ating components CO2 and H2O,enhancing the spectral radiation intensity at the 2.5～3.0 μm and 4.0～5.0 μm bands;within 0～20 km,an increase in flight altitude enhances the spectral radiation intensity by promoting the afterburning reaction process,and CO2 has a significant impact on changes in radiation intensity;in the Mach number range of 1 to 4,an increase in incoming Mach number weakens the afterburning reaction intensity,leading to a decrease in plume temperature and a general reduction in spectral radiation intensity,while the spectral radiation intensity in the 2.5～3.0 μm band,dominated by H2O,decreases significantly.