固体火箭冲压发动机技术研究进展  

Research Progresses in Solid Rocket-Ramjet Engine

作　　者：夏智勋[1] 陈斌斌[1] 黄利亚[1] 王德全[1] 马立坤[1] XIA Zhixun;CHEN Binbin;HUANG Liya;WANG Dequan;MA Likun(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,Hunan,China)

机构地区：[1]国防科技大学空天科学学院

出　　处：《上海航天》2019年第6期11-18,共8页Aerospace Shanghai

基　　金：国家自然科学基金资助项目(51406231,11572349)

摘　　要：近年来,固体火箭冲压发动机获得飞快发展,本文综述了其技术研究进展,为后续固体火箭冲压发动机技术及相似技术的发展提供借鉴。主要介绍了固体火箭冲压发动机的燃气流量调节技术、贫氧推进剂技术、高效燃烧组织技术、转级技术等关键技术。总结发现国内外关键技术已取得了较全面突破,逐渐进入工程实用阶段,但燃烧基础问题研究不足。因此,有必要进一步深入开展推进剂细观燃烧、多相湍流燃烧、金属颗粒燃烧等基础科学研究,进而促进固体火箭冲压发动机技术发展。In recent years,olid rocket-ramjet engine has developed rapidly.In this paper,the research progresses of the technologies for solid rocket-ramjet engine are summarized,which could provide reference for the development of the subsequent solid rocket-ramjet engine technologies and their similar technologies,mainly including the key technologies such as gas flow regulation technologies,fuel-rich propellant technologies,high-efficiency combustion organization technologies,and transition technologies.It is found that major breakthroughs have been achieved in the key technologies at home and abroad,and the technologies gradually enter the stage of engineering applications.However,the research on basic combustion problems is insufficient.Therefore,it is necessary to further carry out basic scientific research on the process and mechanisms of combustion,e.g.,meso-scale combustion of fuel-rich prop-ellant,flow and combustion in chambers,and particle ignition and combustion,to promote the development of solid rocketramjet engine technologies.

关 键 词：固体火箭冲压发动机 贫氧推进剂 燃气流量调节 燃烧组织 金属颗粒燃烧 细观燃烧 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V435[航空宇航科学与技术—航空宇航推进理论与工程]