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Abstract
ABSTRACTThis paper presents a performance analysis on a novel engine concept, currently under development, in order to achieve hybrid air-breathing rocket technology. A component-level approach has been developed to simulate the performance of the engine at Mach 5, and the thermodynamic interaction of the different working fluids has been analysed. The bypass ramjet duct has also been included in the model. This facilitates the improved evaluation of performance parameters. The impact of ram drag induced by the intake of the engine has also been demonstrated. The whole model is introduced into a multi-platform application for aeroengine simulation to make it accessible to the interested reader. Results show that the bypass duct modelling increases the overall efficiency by approximately 7%. The model calculates the specific impulse at approximately 1800 seconds, which is 4 times higher than any chemical rocket.
Highlights
The technical and commercial feasibility of reusable single-stage-to-orbit (SSTO) vehicles, as well as hypersonic aircrafts, is being considered for many years, worldwide
A scramjet engine can achieve much higher Mach numbers compared to a ramjet engine, but still cannot produce static thrust
The thermodynamic cycles of the different working fluids are analysed
Summary
The technical and commercial feasibility of reusable single-stage-to-orbit (SSTO) vehicles, as well as hypersonic aircrafts, is being considered for many years, worldwide. The air-breathing engines that may be suitable and allow propulsion up to hypersonic speeds are ramjets, scramjets, turbojets or a combination of them[1]. These choices, impose major limitations for both SSTO reusable launch vehicles (RLV) and hypersonic aircrafts. A scramjet engine can achieve much higher Mach numbers compared to a ramjet engine, but still cannot produce static thrust. It is one of the most demanding and complex engine concepts from an engineering perspective[3,4,5].
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