Shcramjet
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A shock-induced combustion ramjet engine (abbreviated as shcramjet; also called oblique detonation wave engine; also called standing oblique detonation ramjet (sodramjet);[1] or simply referred to as shock-ramjet engine) is a concept of air-breathing ramjet engine, proposed to be used for hypersonic and/or single-stage-to-orbit propulsion applications.[2]
Design
The shcramjet engine geometry is simple and similar to
Though shock and detonation waves are related to high pressure loss during combustion, the theoretical total pressure loss associated with shcramjet combustor approaches that of the scramjet engine at increasing mach numbers.[citation needed] This fact, together with the simpler engine geometry with concomitant increase in component efficiencies, results in superior predicted performance at flight Mach numbers beyond 12.[citation needed]
Oblique detonation wave engine
This engine funnels a mixture of air and fuel at
A critical challenge is to confine the detonation in a small area, without allowing it to direct energy upstream towards the fuel source or downstream where it loses force. In 2021 an experimental device maintained a detonation in a fixed location for 3 seconds, far longer than earlier attempts.[4]
Scramjet
A shcramjet engine is similar to a scramjet engine; however, unlike the diffusive mode of combustion in a scramjet engine, shcramjet engine combustion takes place across a thin region of standing oblique shock and/or detonation waves stabilized over a wedge, blunt body, etc. Since combustion is confined to a narrow region across the igniting wave, the combustor length in a shcramjet can be significantly shorter than the scramjet, which requires a lengthy combustor for complete fuel-air mixing and combustion. Also, the shcramjet is believed to have a better overall propulsive performance than the scramjet at higher Mach numbers, especially above Mach 12. Recent researches have stipulated that shcramjet, alongside its other airbreathing variants, can act as an efficient high-speed vehicle propulsion system for SSTO flights.[5] These potential advantages have attracted substantial research on propulsive applications, as well as on the fundamental physical phenomena.[6]
References
- ISSN 1000-9361.
- ^ "High Speed Vehicle Propulsion System Group". J. P. Sislian. Archived from the original on March 21, 2012.
- ISSN 0748-4658. AIAA Paper 87-1785.
- ^ a b Gent, Edd. "Ultra-Fast Air And Space Travel Just Got Closer With a Hypersonic Detonation Test". ScienceAlert. Retrieved 2021-05-13.
- doi:10.2514/1.12630. Archived from the originalon 2011-07-24.
- ^ "Combustion and Energy Systems Research Group".