Analsys Of Exhaust Plume Of The Rocket Sled Engine

As a ground simulation experimental platform, the rocket sled has very important test value in the development of aerospace, weapons. In this paper, the numerical simulation and temperature field test of the jet flow generated by solid rocket engine were studied.At first, differential equations of pressure, temperature and other parameters were derived in the combustion process of the rocket sled engine. And the calculation model of the combustion process was established. According to the charge parameters and the size of the engine combustion chamber, the initial conditions for the combustion process were obtained. By calculating the combustion process of the combustion chamber, the change law of the parameters such as pressure and temperature was obtained, as well as the parameters of the nozzle. Secondly, the mesh grids in the computational domain of engine jet flow were divided by ICEM. The calculating results of combustion process were used as the initial boundary conditions of numerical simulation. The jet flow of single nozzle was simulated in 5MPa and 16.5MPa respectively by LES. Then the distributions of pressure, temperature, velocity and Mach number were obtained. The jet flow of four nozzle was simulated in 14MPa and 16.5MPa, and the distributions of pressure, temperature, velocity and Mach number were obtained also. The flow law, shock structure and parameter distribution of flow field were analyzed by numerical simulation. In the jet flow field of single nozzle, the jet was in a loop state of compression and expansion because of the change of internal pressure in the field, and many wave nodes were formed. The higher the inlet pressure was, the longer the wave node was. The shock structures in the node were formed including Mach disk and intersection shock wave. In the jet flow field of four nozzle, the impact shock wave was formed because of the interaction of jet flows. And the parameter distribution and field structure were more complicated. At last, the infrared temperature measurement experiment of jet flow was taken. During engine working, infrared radiation temperature was shot by FLIR SC-7300L thermal imager. The distributions of temperature was got by dealing with the experimental data.By comparing the experimental results with the numerical simulation, the accuracy of the theoretical calculation and numerical simulation was verified. Combined with theoretical calculation, numerical simulation and experimental results, the rope can bear the effect of the high temperature and high speed jet flow ejected by rocket engine.