液氧/甲烷燃气发生器点火方案研究  

Ignition scheme of LOX/methane gas generator

作　　者：李春红[1] 张小平[1] 马冬英[1] 徐浩海[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》2010年第5期7-12,共6页Journal of Rocket Propulsion

基　　金：国家航天技术支撑项目

摘　　要：在对比化学点火、火药点火及电火花点火优缺点的基础上,选取了技术成熟、点火可靠的火药点火用于液氧/甲烷燃气发生器热试。用黑火药点燃固体推进剂的点火药量计算公式估算了火药点火药量,给出了液氧/甲烷燃气发生器火药点火器的其它参数。根据液氧/甲烷推进剂特点,确定了火药燃气-液氧-甲烷依次进入燃气发生器的点火时序。成功进行了4次液氧/甲烷燃气发生器热试,结果表明:液氧/甲烷燃气发生器点火起动过程平稳,点火品质较好,点火方案合理,适于较宽工作条件下的液氧/甲烷点火。The solid cartridge igniter was chosen for the ignition of LOX/methane gas generator in comparison with chemical and electric igniter. The parameters of the igniter were set by the calculation formula and experience of designing similar igniters. The time sequence of LOX/methane gas generator ignition was determined according to the characteristic of LOX/methane propellant. Four firing tests of LOX/methane gas generator were performed successfully. There was no sharp pressure peak or temperature peak appeared in the tests. The smooth ignition curve indicated that the ignition scheme was reasonable.

关 键 词：液氧/甲烷 燃气发生器 点火方案 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]