Coupled thermal,structural and vibrational analysis of a hypersonic engine for flight test |
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| Institution: | 1. Defence Science and Technology Organisation, P.O. Box 1500, Edinburgh, SA 5111, Australia;2. Department of Mechanical Engineering, University of Queensland, Australia;1. Harbin Institute of Technology Shenzhen Graduate School, Guangdong 518055, People''s Republic of China;2. Harbin Institute of Technology, Heilongjiang 150001, People''s Republic of China;1. Novosibirsk State Technical University, Department of Applied Mathematics, 20 Prospekt K. Marksa, Novosibirsk 630073, Russia;2. Siberian Aeronautical Research Institute named after S.A. Chaplygin, 21, Polzunov Street, Novosibirsk 630051, Russia;1. School of Marine Science and Technology, Northwestern Polytechnical University, Xi''an, 710072, China;2. School of Mechanical Engineering, Northwestern Polytechnical University, Xi''an, 710072, China;3. Department of Energy Sciences, Lund University, P.O. Box 118, SE-22100 Lund, Sweden;4. Research & Development Institute of Northwestern Polytechnical University in Shenzhen, Shenzhen, 518057, Guangdong, China;1. Structural Sciences Center, Air Force Research Laboratory, AFRL/RQHF, Wright-Patterson AFB, OH, 45433, USA;2. Hypersonic Sciences Branch, Air Force Research Laboratory, AFRL/RQHF, Wright-Patterson AFB, OH, 45433, USA;3. Universal Technology Corporation, 1270 North Fairfield Road, Dayton, OH 45432, USA;1. State Key Laboratory of Advanced Design and Manufacturing for Vehicle Body, Hunan University, Changsha, Hunan 410082, PR China;2. School of Transportation and Vehicle Engineering, Shandong University of Technology, Zibo 255049, PR China |
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| Abstract: | This paper describes a relatively simple and quick method for implementing aerodynamic heating models into a finite element code for non-linear transient thermal-structural and thermal-structural-vibrational analyses of a Mach 10 generic HyShot scramjet engine. The thermal-structural-vibrational response of the engine was studied for the descent trajectory from 60 to 26 km. Aerodynamic heating fluxes, as a function of spatial position and time for varying trajectory points, were implemented in the transient heat analysis. Additionally, the combined effect of varying dynamic pressure and thermal loads with altitude was considered. This aero-thermal-structural analysis capability was used to assess the temperature distribution, engine geometry distortion and yielding of the structural material due to aerodynamic heating during the descent trajectory, and for optimising the wall thickness, nose radius of leading edge, etc. of the engine intake. A structural vibration analysis was also performed following the aero-thermal-structural analysis to determine the changes in natural frequencies of the structural vibration modes that occur at the various temperatures associated with the descent trajectory. This analysis provides a unique and relatively simple design strategy for predicting and mitigating the thermal-structural-vibrational response of hypersonic engines. |
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