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整体式冲压发动机是将固体助推火箭与巡航用液体燃料冲压发动机组合成为一个整体的新型动力装置,它是超声速、小体积、中远程导弹动力系统的最佳选择.整体式冲压发动机的出现将冲压发动机的应用推向一个新阶段,引起世界各国的广泛重视.近几年我国在整体式冲压发动机很多关键技术的研究上有所突破.液体冲压发动机和助推火箭共用一个燃烧室,使燃烧室中无法安装专门的机械式火焰稳定器和空气冷却衬筒,这为解决燃烧室的点火起动问题、振动问题及热防护问题带来了很大的困难.试验表明:冲压发动机的点火起动问题有多种解决方案,其中火焰稳定性准则的满足是点火起动的重要条件;燃烧室的进口流场,燃油浓度分布等对振动有很大的影响;计算表明,冲压发动机在飞行状态时,流经燃烧室壳体外表面的高速气流的冷却作用可大大降低燃烧室壳体的温度,在相同的冷却效果下,可降低对热防护层的要求.
The integrated ramjet engine is a new type of power unit that combines the solid booster rocket with the cruise liquid fuel ramjet engine and is the best choice for the supersonic, small size and long-range missile power system. Stamping engine application to a new stage, aroused widespread attention in all countries in the world.In recent years, many breakthroughs in the research of many key technologies of the integrated ramjet engine.Plumbing ramjet and booster rocket share a combustion chamber, so that the combustion The special mechanical flame stabilizer and the air-cooled liner can not be installed in the chamber, which brings great difficulties to solve the ignition starting problem, vibration problem and heat protection problem of the combustion chamber.The experiment shows that the ignition starting problem of the ramjet engine There are a variety of solutions, of which the flame stability criteria to meet the ignition start important conditions; the inlet flow field of the combustion chamber, the fuel concentration distribution has a great impact on the vibration; calculation shows that the ramjet engine in flight, the flow The cooling effect of the high-speed air flow passing through the outer surface of the combustion chamber shell can greatly reduce the Degree, at the same cooling effect, can reduce the requirement for a heat shield.