A general strategy is identified to compute the minimum fuel required for the ascent of a generic hypersonic vehicle that is propelled by a dual-mode ramjet–scramjet engine with hydrogen fuel. The study addresses the ascent of an accelerator vehicle rather than a high-speed cruiser. Two general types of ascent trajectories are considered: acceleration within scramjet mode, and acceleration across the ramjet–scramjet transition boundary maximum acceleration and maximum dynamic pressure (lowest allowed altitude) were shown to be near optimum for scramjet-mode trajectories, but optimized trajectories were found to be more complex when both modes are considered. The first-principles model used in this paper computes the combustion efficiency using finite-rate chemistry and a fuel–air mixing model. It also computes the inlet efficiency with a shock wave interaction code, and thus avoids empirical formulas for efficiency that were used in previous models.
Minimum-Fuel Ascent of a Hypersonic Vehicle Using Surrogate Optimization
Journal of Aircraft ; 51 , 6 ; 1973-1986
2014-04-25
14 pages
Article (Journal)
Electronic Resource
English
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