Study On Spectral Radiation Characteristics Of The Tail Flame Flow Field Of Rocket Motor

Solid rocket motor is a kind of engine which is widely used in various tactical and strategic missiles with its own oxidant and fuel.The spectral radiant characteristic of the tail flame flow field is an important characteristic signal for target recognition.Based on FLUENT,the RNG k-ε turbulence model is used to numerically simulate the tail flame flow field.The finite rate chemical reaction model and CO/H2 reaction mechanism are used to simulate the afterburning of the tail flame flow field.The HITRAN spectral database is used to calculate the radiant parameters of the gas components in the tail flame flow field.The spectral radiant characteristics of tail flame flow field were calculated by using the coordinate discrete model.The main contents are as follows:1、The influence of afterburning on the spectral radiation characteristics of the tail flame flow was studied.The results show that the afterburning enhances the temperature and spectral radiation intensity of the tail flame flow field,enlarges the distribution regions of the flow field temperature and spectral radiation,and is an important factor affecting the spectral radiation characteristics of the tail flame flow field.2、The influence of flight velocity on the spectral radiation characteristics of the tail flame flow field was studied.The results show that with the increase of the flight velocity,the afterburning degree of the tail flame field of the solid rocket motor decreases,the temperature and the spectral radiation intensity decrease,the temperature and spectral radiation distribution regions decrease.3、The influence of flight height on the spectral radiatnt characteristics of tail flame flow was studied.The results show that with the increase of the flight height,the afterburning degree of the tail flame flow decreases,the temperature and the spectral radiation intensity decrease,and the distribution region decreases gradually.After reaching a certain height,the afterburning stops.The intensity of spectral radiation at Mach disc is obviously greater than that at other locations in the flow field.4 、 The influence of combustion chamber pressure on the spectral radiation characteristics of the tail flame was studied.The results show that with the increase of the combustion chamber pressure,the afterburning degree of the tail flame flow field of the solid rocket motor increases,the temperature and spectral radiation intensity of the tail flame flow field increases,the peak point gradually moves backward,the temperature and spectral radiation distribution regions increase,the temperature and radiation intensity at Mach disk increased.5、The influence of HMX contents on the spectral radiation characteristics of the tail flame flow in the CMDB was studied.The results show that with the increase of HMX contents in the CMDB,the degree of afterburning of the tail flame flow field decreases and the radiation intensity increases at the Mach disk of the tail flame flow field.The postmedian radiation intensity decreases gradually,and the radiant region changes little.6、The influence of AP contents on the spectral radiation characteristics of tail gas flow field in CMDB was studied.The results show that with the increase of the content of AP in the modified double base propellant,the degree of afterburning of the tail-flame flow decreases,the temperature and radiation intensity increases at Mach disk.The radiation intensity decreases,and the radiation region of the tail flame flow field decreases.