冲压发动机突防能力与航程分析  

The penetration capability and voyage analysis of ramjet

作　　者：王玉清 赵文胜[3] 谢海波[3] 裘云[2] 秦飞[1] 蒋妮[2] Wang Yuqing;Zhao Wensheng;Xie Haibo;Qiu Yun;Qin Fei;Jiang Ni(Science and Technology on Combustion,Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi'an 710072,China;Beijing Engine Machinery Research Institute,Beijing 100072,China;China Aerospace Science and Industry Aviation Technology Research Institute,Beijing 100074,China)

机构地区：[1]西北工业大学燃烧,热结构与内流场重点实验室,西安710072 [2]北京动力机械研究所,北京100072 [3]中国航天科工飞航技术研究院,北京100074

出　　处：《空天技术》2023年第5期79-86,共8页Aerospace Technology

摘　　要：随着亚燃冲压发动机应用进一步拓展以及超燃冲压发动机技术逐步取得突破,冲压发动机在高速、远程、宽域工作精确打击武器中发挥了重要作用。从国内外冲压发动机在超声速导弹中应用现状、工作特点和发展趋势出发,研究了冲压发动机对飞行航程、突防能力影响参数。超燃冲压发动机速度快、拦截反应时间短、突防能力强,是高超声速精确打击武器的优势动力;亚燃冲压发动机则兼具有在临近空间和5~50 m低空超声速飞行的特点,可提升导弹高低空突防能力,在相同起飞质量下,基于亚燃冲压发动机的导弹航程优于基于超燃冲压发动机导弹的航程,在作战平台质量受限时,亚燃冲压发动机更适合远距离飞行。With the further expansion of the application of subcombustion ramjet engines and the gradual breakthroughs in scramjet engines technoiogy,ranjet engines piay an important roie in high-speed,iong-range and wide range operation of precision strike weapons.Starting from the application status,working characteristics and development trend of ramjet engines in supersonic missiles at home and abroad,the parameters of ramjet on flight range and penetration capability are studied.The scramjet has fast speed,short interception reaction time,and strong penetration ability,which is the dominant driving force for hypersonic precision strike weapons.However,the subcombustion ramjet has the characteristics of the near space and 5~50 m low-altitude supersonic flight,which can improve the missile's high and low altitude penetration capability.Under the same take-off mass,the range of the missile based on the subcombustion ramjet is better than the range of the scramjet engine-based missile,and when the quality of the combat platform is limited,the ramjet engine is more suitable for long-distance flight.

关 键 词：冲压发动机 飞行航程 起飞质量 超声速飞行 突防能力 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]