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Conceptual Design Study on Rocket Based Combined Cycle Engine  

Kang, Sang Hun (미래로켓연구팀)
Lee, Yang Ji (항공추진기관팀)
Yang, Soo Seok (항공추진기관팀)
Publication Information
Aerospace Engineering and Technology / v.12, no.1, 2013 , pp. 111-119 More about this Journal
Abstract
Conceptual design of RBCC (Rocket Based Combined Cycle) engine is performed through the thermodynamic cycle analysis. The engine is designed to take off at sea level and accelerate to Mach 8 at 30 km altitude. According to the flight speed, the engine operating modes are categorized into 3 modes : Ejectorjet (~ Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). As a design result, the engine has a diameter of 1 m and a length of 6.7 m. In the prediction results, its maximum thrust is 16.5 ton. In Ramjet and Scramjet modes, design condition of the engine intake influence the engine thrust according to the flight speed.
Keywords
Rocket Based Combined Cycle Engine; Ejector-jet; Ramjet; Scramjet; Thermal Choking;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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