Hypersonic technology experimental vehicle for flight experiment of pre-cooled turbojet engine is investigated. The vehicle is assumed to mount two pre-cooled turbojet engines at the bottom. The vehicle will be accelerated up to Mach 5 flight speed by an external booster rocket. The vehicle aims at demonstrating Mach 5 cruise capability for a short-period. Aerodynamic performance, engine thrust and structure mass are analyzed for the baseline system. Lift to drag ratio has improved by adding a strake in front of the main wing. Engine thrust is estimated without considering the additional thrust at the external nozzle. Structure mass is estimated using an optimization program using finite element method. Force balance around the vehicle is summarized and it is confirmed that the vehicle will slightly descend and decelerate at Mach 5 flight condition, without considering the external thrust. Component tests of pre-cooled turbojet engine with simulated' flight condition are conducted toward the flight experiment. Pre-cooler is tested with high temperature condition simulating Mach 4 flight condition. Core engine starting sequence is confirmed with low pressure condition. Fuel supply system for hydrogen fuel with super-critical condition is tested to attain precise fuel flow control for the core engine. High temperature tests and propulsion wind tunnel tests of the engine with simulating Mach 5 condition is planned.
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