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http://dx.doi.org/10.6108/KSPE.2012.16.1.016

Conceptual Design Study of Two-Stage Hypersonic Scramjet Vehicle  

Lee, Kyung-Jae (한국항공우주연구원 항공추진기관팀)
Kang, Sang-Hun (한국항공우주연구원 미래로켓추진팀)
Yang, Soo-Seok (한국항공우주연구원 항공추진기관팀)
Park, Chul (한국과학기술원 항공우주공학과)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.16, no.1, 2012 , pp. 16-24 More about this Journal
Abstract
In this study, two-stage hypersonic scramjet vehicle was designed for the flight condition of Mach number 6. In order to launch at sea level, two stage concept was applied. The first stage of the vehicle is solid rocket-powered and is mounted under the second stage. The second stage is powered by scramjet propulsion system and gas wings. The suggested mission scenario is to deliver 0.2 ton payload to the range of 2,000 km. For the first step of conceptual design, trajectory of air vehicle was calculated by 3-DOF trajectory code. Based on the result of trajectory code, scramjet engine design and mass estimation were performed by non-equilibrium nozzle flow code and NASA's HASA model, respectively. In order to find best solution, all steps of designing process was iterated until they was reached.
Keywords
Scramjet; Hydrocarbon; Conceptual Design;
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  • Reference
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