壁厚对空间小推力发动机喉部壁温的影响  

Effect of wall thickness on throat wall temperature of space small thrust engines

作　　者：张锋[1] 仲伟聪[1] 张魏静[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2011年第6期34-37,共4页Journal of Rocket Propulsion

基　　金：总装备部预研项目(2009AA7020510)

摘　　要：介绍了空间小推力发动机通常采用的冷却方式及降低推力室喉部壁温的常用方法,分析了通过增加壁厚降低喉部壁温的可能性。通过简化模型,对不同壁厚下的喉部壁温进行了计算,计算结果表明,适当增加壁厚可以起到降低喉部壁温的作用。The frequently-used cooling modes for spaceborne small thrust engines and ways usually-used to reduce the throat wall temperature of the thrust chamber are introduced. The possibility of reducing the throat wall temperature by increasing the wall thickness is discussed. The throat wall temperature under the condition of different wall thickness is calculated by simplifying the model. The results show that the throat wall temperature could be reduced by increasing the wall thickness properly.

关 键 词：壁厚 小推力发动机 喉部壁温 

分 类 号：V430-34[航空宇航科学与技术—航空宇航推进理论与工程]