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本文介绍一种新的推进概念,即整体式火箭双燃烧冲压发动机(the integralro—cket,dual-combustion ramjet,以下简称IRDCR),它可以用在高超音速、体积有一定限制的导弹上。实际上,就是把一个“突胀式(dump-type)亚音速燃烧冲压发动机放在主超音速燃烧冲压发动机(Scramjet)系统中作富油的、热燃气发生器,因而可以允许使用碳氢燃料而不用极活性硼基燃料。靠超音速冲压发动机燃烧室中装火箭—助推推进剂可改进推进系统的容积效率。研制了一套设计IRDCR发动机热循环和估算其性能所需要的新方法。根据一组特殊进气道,在马赫数4～7,定常飞行动压为5000磅力/英尺~2的飞行条件下的典型计算值讨论了这种新的方法,还根据最大推力和发动机效率原则讨论了发动机性能对进气道工作特性的敏感性。一般说,IRDCR在性能特性上兼有普通冲压发动机和超音速燃烧冲压发动机两者的某些优点。
This article describes a new propulsion concept, the integral rocket dual combustion ramjet (the integral-cket, dual-combustion ramjet, hereinafter referred to as IRDCR), which can be used in hypersonic, size limited missiles. In fact, putting a “dump-type” subsonic combustion ramjet engine in an oil-rich, hot gas generator in a main supersonic combustion Scramjet system allows the use of hydrocarbon fuels Instead of using very reactive boron-based fuels, the volumetric efficiency of a propulsion system can be improved by incorporating a rocket-boosting propellant in a supersonic ramjet engine combustion chamber. A new method is developed to design the thermal cycling of an IRDCR engine and evaluate its performance. Typical calculations for a particular set of inlets at flight conditions with a Mach number of 4 to 7 and a constant aerodynamic pressure of 5000 lbf / ft2 discuss this new approach, based on maximum thrust and engine efficiency The principle discusses the sensitivity of engine performance to the operating characteristics of the intake.In general, the IRDCR has some of the advantages of both a normal ramjet and a supersonic combustion ramjet in terms of performance characteristics.