摘要
喷管是火箭发动机的重要部件之一,它使燃气加速产生推力。可变喉面喷管是一种特殊喷管,可以改变喷管喉部面积,从而改变推力大小,改善发动机的性能。本文提出了一种可变喉面喷管设计方案,进行了性能仿真计算,结果表明,设计的可变喉面喷管能够满足设计要求。
Nozzle is one of the important parts of rocket motor, which accelerates gas and transfers heat energy into kinetic energy, finally produces thrust. Nozzle with variable throat area can change thrust according to requirments, and can improve motor performance. A design scheme of nozzle with variable throat area is given in this paper, which meet the demand of design in the light of simulation results.
出处
《航空兵器》
2007年第5期52-55,共4页
Aero Weaponry
基金
航空科学基金(2006ZC12006)
关键词
可变喉面喷管
推力
设计方案
nozzle with variable throat area
thrust
design scheme
