降低NEPE推进剂燃速的途径探讨  

An approach to decreasing the burning rate of NEPE propellant

作　　者：吴芳[1] 王世英[1] 庞爱民[1] 

机构地区：[1]中国航天科技集团公司四院四十二所,湖北襄樊441003

出　　处：《固体火箭技术》2002年第2期48-51,共4页Journal of Solid Rocket Technology

摘　　要：通过对NEPE推进剂燃烧表面的热平衡分析 ,指出了影响推进剂燃速的 3个因素 :“嘶嘶”区 (fizz)的温度梯度、凝聚相反应热和燃面温度 ,提出了降低NEPE推进剂燃速的可能途径 ,研究了某些燃速降速剂的作用及其对推进剂能量的影响。用实验证明了降低燃速几个途径的可行性。Three factors,including temperature profile of fizz zone,heat of reaction of condensed phase and temperature of burning surface have been found to affect the burning rate of NEPE propellant by the light of analysis of the heat balance on the burning surface.The possible methods to decrease burning rate are presented,the action of burning rate depressants and the effect on energy of propellant are researched.The results show that the approach for decreasing the burning rate of propellant is feasible.

关 键 词：NEPE推进剂 降速剂 温度梯度 燃烧速度 影响因素 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]