Upper Bounds on the Flight Speed of Hydrocarbon-Fueled Scramjet-Powered Vehicles
Upper Bounds on the Flight Speed of Hydrocarbon-Fueled Scramjet-Powered Vehicles
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DOI：
10.2514/2.5895
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发表时间：
2001-11
影响因子：
1.9
通讯作者：
P. J. Waltrup-
中科院分区：
文献类型：
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作者：
P. J. Waltrup-
简介 从 20 世纪 50 年代末超音速燃烧冲压发动机（超燃冲压发动机）循环（见图 1）开始至今，人们对使用氢气等气体燃料或煤油等可储存液态烃燃料时的飞行马赫数上限有很多猜测。一些最初的研究声称氢燃料系统的轨道速度（马赫 26）及以上，碳氢燃料系统的轨道速度为 14-16 马赫。1i3 20 世纪 60 年代和 1970 年代初的后续研究将这些估计值分别向下修正为 15-20 马赫和 12-14,4i7 马赫。然而，这些研究中的大多数都不是特定于配置的，并且没有一个包含自超燃冲压发动机动力飞行器印刷以来所了解的操作和性能的知识。在这些早期研究之后，针对氢燃料概念进行了几项现代研究，主要是针对地球到轨道空间运输系统，8i11，其中速度上限稍低，主要在 12-16 马赫范围内。还有许多关于碳氢化合物燃料导弹概念的研究，12i16 但这些研究都没有涉及上限马赫数
Introduction F ROM the inception of the supersonic combustion ramjet (scramjet) engine cycle (see Fig. 1) in the late 1950s through the present time, there has been much speculation about what the upper bound on ight Mach number is when using either a gaseous fuel such as hydrogen or a storable liquid hydrocarbon fuel such as kerosene. Some initial studies claimed orbital speeds (Mach 26) and beyond for hydrogen-fueledsystems andMach 14–16 ight for hydrocarbon-fueled systems.1i3 Subsequent studies in the 1960s and early 1970s revised these estimates downward somewhat to Mach 15–20 and Mach 12–14,4i7 respectively. However, most of these studies are not con guration speci c, and none incorporate what has been learned about the operation and performance of scramjet-poweredvehicles since their printing. Subsequent to these early studies, several modern studies have been done for hydrogen-fueled concepts, primarily for Earth-toorbit space transport systems,8i11 in which the upper speed bound is somewhat lower, primarily in the Mach 12–16 range. There have also been a number of studies on hydrocarbon-fueledmissile concepts,12i16 but none of these addressed the upperMach number