固体火箭发动机推力可调塞式喷管数值模拟与冷流试验

Numerical Simulation and Cold-Flow Test of Adjustable Thrust Solid Plug Nozzle

为满足高性能导弹推进系统需求,提高固体火箭发动机推力矢量调节性能,综合塞式喷管高度补偿和结构功能一体化的特点,设计了一套环喉型固体塞式喷管。该喷管由小喷管膨胀段和中心塞锥组成,通过移动小喷管膨胀唇部的位置,改变喉部面积大小,实现推力可调,采用数值模拟方法预估了其推力性能。对塞式喷管进行了地面冷流试验,测定了其推力性能。结果表明:环喉型塞式喷管推力性能的数值模拟结果与试验结果相吻合。当塞式喷管喉部面积满足0.7倍变化时,可实现塞式喷管推力4∶1的调节变化,同时具有明显的高度补偿效应。未来可进一步优化内喷管设计,使其广泛适用于全空领域导弹动力系统,提高发动机性能。

In order to meet the requirements of high-performance of the missile propulsion system and improve the regulation of the thrust vector of the solid rocket motor,this paper combines the compensated characteristics of the plug nozzle in different altitudes and the integration of structural and function.A type of plug nozzle,with a small nozzle’s expansion section and a central plug cone,is designed to gain properties of plug nozzle’s performance.Thrust of the nozzle can be changed by moving the lip of the nozzle to adjust the throat area.And then,it is evaluated by numerical simulation.A ground cold-flow test is carried out to measure the thrust of the clustered plug nozzle.The result shows that the data of numerical simulation of the flow phenomenon accords with the experimental results.As for the solid adjustable plug nozzle designed in this paper of which the throat area ranges about 0.7 times,the thrust is 4 times,reflecting the compensated effects of the plug nozzle in different altitudes.Further,the design of the inner nozzle can be optimized to suit for the full-air missile power system and improve solid rocket motor performance.