Sangwook JIN, Haeseung JEONG, Minchan KWON, Juhyun BAE, Seokjin OH, Hojin CHOI, Jaehoon RYU, Suji LEE

DOI Number: 10.82241/ceas-hisst-2024-331

Conference number: HiSST-2024-331

In order to operate an aircraft across a wide range of altitudes and speeds, a combined cycle is required. This combined cycle comprises various engines, each optimized for specific altitude bands. However, in regions where different engines overlap, thrust may become insufficient. To address the issue of inadequate thrust during relatively low-speed, near-hypersonic flight, a dual-mode ramjet combustor with a rocket has been conceptualized. The integrated combustor functions by injecting combustion gases generated by the rocket into the dual-mode ramjet combustor through a strut nozzle. Experimental tests were conducted on the proposed engine to measure the combustor’s thrust, which was then compared to thrust values calculated using theoretical formulas quasi-one-dimensional method and pitot pressure rake at combustor exit.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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