固液火箭发动机装药设计优化

推进技术 ›› 2000, Vol. 21 ›› Issue (1): 67-70.

固液火箭发动机装药设计优化

曹泰岳,师艳辉,吴海波

国防科技大学航天技术系!湖南长沙410073;国防科技大学航天技术系!湖南长沙410073;国防科技大学航天技术系!湖南长沙410073

发布日期:2021-08-15

Optimization of grain design for hybrid rocket engine

Dept of Aerospace Technology ,National Univ of Defence Technology ,Changsha 410073,China;Dept of Aerospace Technology ,National Univ of Defence Technology ,Changsha 410073,China;Dept of Aerospace Technology ,National Univ of Defence Technology ,Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 按两类不同的气化速率公式,讨论了固液火箭发动机燃料装药优化设计的方法和程序,并针对某HTPBLOX(或GOX)发动机,给出了多孔装药在不同孔数的情形下某些参数随时间的变化以及另一些参数的总体值或平均值,最后就燃料装药设计和配方设计给出了某些结论。

关键词: 混合推进剂火箭发动机;推进剂药柱;推进剂配方;最优设计

Abstract: The method and the procedure of design optimization for fuel grain of hybrid rocket engines were discussed using two different kinds of formula for fuel regression rate With multi port grain of some HTPB/LOX(or GOX) engine the variation of some parameters with time and other parameters were given for different numbers of port Some conclusions were drawn on fuel grain design and fuel ingredient design

Key words: Hybrid propellant rocket engines,propellant grain;Propellant formulation;Optimization design

曹泰岳,师艳辉,吴海波. 固液火箭发动机装药设计优化[J]. 推进技术, 2000, 21(1): 67-70.