Solid Rocket Ramjet Combustion Numerical Simulation

The Ducted Rocket (DR) is becoming the important shinning star in the field of aerospace propulsion in the world. To improve the performance of DR, it is absolutely necessary to study deeply how to operate the process of the mixture and combustion of air combining with fuel in the chamber of DR, one of its key technologies.In this dissertation, the simple model of DR' s flow with reaction was founded, the flow model and numerical algorithm were val idated by the data of DR' s test. The mechanism of the mixture and combustion of air and fuel, what was influenced by the head distance of after-burning chamber, the area of fuel nozzle and the angles between dual air— inlets, was studied by the means of CFD, and found: 1, the head distance of after-burning chamber is increasing, the circumfluence in the head of after-burning chamber is stronger and the distribution of fuel backward the after-burning chamber is more well-proportioned, however the distance of the mixture and combustion of air combining with fuel is decreasing. 2, in some extent, increasing the area of fuel nozzle will be improve the combustion efficiency of DR; 3, the angle between dual air-inlets have complex influence with the combustion of DR. When the angle between dual air-inlets is equal to 180 degree, the mixture of fuel and air is best to symmetry fuel nozzle. To the non-symmetry fuel nozzle, the law of the change of flow field of after-burning and combustion efficiency with the variety of the angle between air-inlets is homoplastic.The results supply references and guidance for the design of DR and the organization of afterburning, so these have some scientifie meaning and engineer value.