| 摘要 |
An engine for application to the propulsion of aerospace vehicles (terrestrial or orbital) capable of operating in two propulsive modes. The first mode employs liquid hydrogen to pre-cool the intake air of a turbo-compressor in order to deliver it at high pressure to a rocket type combustor/nozzle assembly. In this mode the external atmosphere is the source of oxidizer for the fuel. At a high Mach number in the hypersonic regime the engine changes to the second mode which is a conventional high performance rocket engine using liquid oxygen carried on the vehicle to oxidize the liquid hydrogen fuel. Both modes of propulsion use common hardware, namely the liquid hydrogen pump and the combustor nozzle assembly.
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