喉栓式变推力发动机性能研究  

Study on performance of pintle controlled thrust solid rocket motor

作　　者：李娟[1] 李江[1] 王毅林[1] 秦飞[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2007年第6期505-509,共5页Journal of Solid Rocket Technology

摘　　要：利用建立的等效喉部面积计算方法,确定了喉栓式变推力发动机中喉栓构型、喉栓位置、喉部面积之间的重要关系,比较了不同构型发动机推力调节性能的差异。针对喉栓介入后发动机内复杂波系、流动分离等非传统流动现象开展稳态数值模拟,预示了变推力过程中发动机的整体性能;并将计算的稳态平衡压强、推力与原理样机的试验数据进行了对比,结果较为一致,验证了变推力的可行性和数值模型的有效性。所得结论可为变推力固体火箭发动机的设计、试验及应用提供参考依据。The important relationship among configuration,position of pintle and throat area can be determined by means of the equivalent throat area calculation method, and thrust regulating performances of the motors with different pintle configuration were contrasted. Some unconventional flow phenomena such as complex wave system ,flow seperation in the motor due to the intervention of pintle were numerically simulated, and the total performance of the motor during controlled thrust was predicted. The calculated steady-state balance pressure and thrust were compared with experiment data of principle prototype, and the results agreed well;feasibility of thrust control and the validity of the numerical model were verified. The conclusion can provide a useful reference for design, experiment and application of controlled thrust solid rocket motor.

关 键 词：变推力 固体火箭发动机 等效喉部面积 内流场 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]