自燃推进剂火箭发动机稳态燃烧过程的数值模拟

推进技术 ›› 1998, Vol. 19 ›› Issue (5): 6-9.

自燃推进剂火箭发动机稳态燃烧过程的数值模拟

聂万胜,庄逢辰

长沙国防科技大学航天技术系;长沙国防科技大学航天技术系

发布日期:2021-08-15

NUMERICAL SIMULATION OF STABLE COMBUSTION PROCESS IN EARTH STORABLE BIPROPELLANT ROCKET ENGINE

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

Published:2021-08-15

摘要/Abstract

摘要： 研究了自燃推进剂火箭发动机的稳态燃烧过程。用一甲基肼作燃料，四氧化二氮为氧化剂，考虑了液滴的雾化机理和高压分解燃烧。将ＰＩＳＯ算法应用于任意曲线坐标下，在计算中采用非交错网格技术抑制了压力振荡。成功地获得了发动机燃烧过程的流场参数。

关键词: 自燃火箭推进剂;稳定燃烧;燃烧试验;数值仿真

Abstract: Combustion process in Earth storable bipropellant rocket engine was studied.Monemethyl hydrazine(MMH)was used as the fuel,and nitrogen tetroxide(NTO)was used as the oxidizer.The atomization mechanism of liquid/liquid coaxial injector and decomposition combustion at high presure were considered.The PISO algorithm was introduced to the arbitrary curveline coordinator and nonstaggered grid was employed in the calculation.The flowfield results of the combustion process were numerical simulated successfully.

Key words: Hypergolic rocket propellant;Stable combustion;combustion test;numerical simulation

聂万胜,庄逢辰. 自燃推进剂火箭发动机稳态燃烧过程的数值模拟[J]. 推进技术, 1998, 19(5): 6-9.