RBCC用变工况气氧/煤油引射火箭发动机设计和试验研究  

Design and Experimental Investigation on Gas Oxygen/Kerosene Ejector Rocket for RBCC Application

作　　者：魏祥庚[1] 秦飞[1] 石磊[1] 张保庆[1] 何国强[1] Wei Xianggeng;Qin Fei;Shi Lei;Zhang Baoqing;He Guoqiang(Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi′an 710072,China)

机构地区：[1]西北工业大学燃烧热结构与内流场重点试验室,陕西西安710072

出　　处：《西北工业大学学报》2018年第3期558-564,共7页Journal of Northwestern Polytechnical University

摘　　要：引射火箭是火箭冲压组合发动机的核心部件之一,须具有变工况工作能力。针对RBCC发动机用引射火箭的技术要求,基于挤压式推进剂供应系统,设计了变工况工作气氧/煤油引射火箭系统,完成了4种工作状态下的点火试验验证。试验研究结果表明,设计的变工况工作引射火箭发动机稳定可靠工作,工作参数满足设计要求,可实现快速调节。为开展火箭冲压组合发动机试验及大调节比引射火箭技术研究奠定了基础。The ejector rocket is one of the core components of the rocket based combined cycle propulsion system,and must be capable of variable working conditions.In order to meet technical requirements for RBCC application,the variable duty operating ejector rocket using the gas Oxygen/Kerosene was designed based on the gas pressurized propellant feed systems.Hot firing tests of four different working conditions had been completed.Experimental results show that the designed ejector rocket engine was stable and reliable,and the working parameters met the design requirements,and the working conditions were adjusted quickly.It lays a foundation for the study of the RBCC engine test and the engine technology of large adjustment ratio.

关 键 词：火箭冲压组合发动机 液体火箭发动机 引射火箭 流量调节 试验 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]