Research on hypersonic aircraft using pre-cooled turbojet engines |
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| Institution: | 1. Aviation Program Group, Japan Aerospace Exploration Agency, 7–44-1, Jindaiji-Higashi, Chofu, Tokyo 182-8522, Japan;2. Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency, Japan;3. Space Utilization Mission Office, Japan Aerospace Exploration Agency, Japan;1. Key Laboratory of Aerospace Thermophysics, Ministry of Industry and Information Technology, School of Energy Science and Engineering, Harbin Institute of Technology, China;2. Chongqing Research Institute, Harbin Institute of Technology, Chongqing 401120 China;1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, 210016, China;2. Ryerson University, Toronto, ON, Canada;1. China Academy of Aerospace Aerodynamics, Beijing, China;2. China Aerodynamics Research and Development Center, Mianyang, China;3. School of Aeronautics, Northwestern Polytechnical University, Xi''an, China;1. Energy and Electricity Research Center, Jinan University, Zhuhai 519070, China;2. MOE Key Lab of Disaster and Control in Engineering, Jinan University, Guangzhou 510632, China |
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| Abstract: | Systems analysis of a Mach 5 class hypersonic aircraft is performed. The aircraft can fly across the Pacific Ocean in 2 h. A multidisciplinary optimization program for aerodynamics, structure, propulsion, and trajectory is used in the analysis. The result of each element model is improved using higher accuracy analysis tools. The aerodynamic performance of the hypersonic aircraft is examined through hypersonic wind tunnel tests. A thermal management system based on the data of the wind tunnel tests is proposed. A pre-cooled turbojet engine is adopted as the propulsion system for the hypersonic aircraft. The engine can be operated continuously from take-off to Mach 5. This engine uses a pre-cooling cycle using cryogenic liquid hydrogen. The high temperature inlet air of hypersonic flight would be cooled by the same liquid hydrogen used as fuel. The engine is tested under sea level static conditions. The engine is installed on a flight test vehicle. Both liquid hydrogen fuel and gaseous hydrogen fuel are supplied to the engine from a tank and cylinders installed within the vehicle. The designed operation of major components of the engine is confirmed. A large amount of liquid hydrogen is supplied to the pre-cooler in order to make its performance sufficient for Mach 5 flight. Thus, fuel rich combustion is adopted at the afterburner. The experiments are carried out under the conditions that the engine is mounted upon an experimental airframe with both set up either horizontally or vertically. As a result, the operating procedure of the pre-cooled turbojet engine is demonstrated. |
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