Hydrants Engine Thrust To Adjust The Characteristics Of Study

Using the movement of pintle to chang the equivalent throat area can achieve thrust control of traditional SRM and inhance the flexiblity performance of modern missiles and weapon systems, and it has the stongly maneuverability requests background. The thrust control process involved many special and complexity physical process compared to the traditional Solid Rocket Motor (SRM), so thrust control property of pintle controlled solid rocket motor has the most significant research meaning. Aim at the specialty of pintle controlled solid rocket motor,the paper estiablished the steady and unsteady numerical simulation model of the motor, carried out an in-depth theoretically analysis and a plenty of numerical simulations, Clarify the mechanism of the motor's flow disciplinarian and thrust control performance, and lay the foundations for the development of pintle controlled solid rocket motor.The main contents and conclusions in the paper including:Estiablished the steady numerical models of pintle controlled solid rocket motor, And verified the model with the theoretical experiment data. By a plenty of numerical simulations, dedicated the mechanism of the motor's flow characteristic, Analysis are performed on various matching combinations of pintle geometry, nozzle geometry and pintle position. The effects of these factors on the flow and thrust control performance are investigated. And obtained an optimized pintle and nozzle shape from the point of thrust control capability and impulse efficiency.Based on on the dynamic mesh methods, the unsteady numerical simulation models are established. And analysed the characteristics of the unsteady flow in thrust control process ,Also indicated the effects of propellant burning properties, pintle movement velocity and the combustor free volume on the inner-flow and the chamber pressure response process.Carried out theoretical research on nozzle expand state disciplinarian varible with pintle's position, Point out that assuming unalterable nozzle geometry , the nozzle exit pressure inhanced with the throat area decrease,and the most possible over-expand and flow seperiation phenomena occurred with the pintle fully extracted and provided suggestions to the direction of nozzle design.Analysed the feasibility of closed-loop pressure control system of pintle rocket...