Aerodynamic optimization of re-entry capsules |
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| Institution: | 1. China Aerodynarnics Research and Development Center (CARDC), PO Box 211, Mianyang, Sichuan 621000, PR China;2. German Aerospace Center (DLR), Lilienthalplatz 7, 38108 Braunschweig, Germany;1. Energy Engineering Department, German Jordanian University, Amman, Jordan;2. Mechanical Engineering Department, Jordan University of Science and Technology, Irbid, Jordan;3. Mechatronics Engineering Department, German Jordanian University, Amman, Jordan;4. Mechanical and Maintenance Engineering Department, German Jordanian University, Amman, Jordan;1. School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China;2. State Key Laboratory of Technologies in Space Cryogenic Propellants, Beijing 100028, China;1. Department of Mechanical Engineering, IIT Bombay, Mumbai, India;2. Department of Mechanical Engineering, Defence Institute of Advanced Technology, Pune, India;3. Mechanical Engineering Department, Institute of Technology – Nirma University, Ahemedabad, India;1. Department of Mechanical Engineering of Agricultural Machinery, Faculty of Agriculture, Urmia University, Urmia, Iran;2. Department of Mechanical Engineering, Faculty of Engineering, Urmia University, Urmia, Iran;1. National Key Laboratory of Computational Fluid Dynamics, Beihang University, Beijing 100191, China;2. Chengdu Aircraft Design & Research Institute, Chengdu 610041, China |
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| Abstract: | Methods for aerodynamic design and optimization based on linear theory are not well suited for modelling non-linear phenomenons. Their results only represent approximations of real optima. In the present study a new method based on non-linear theory, i.e. the solution of the Euler/Navier–Stokes equations, has been applied to improve these approximations. The structure of the system as well as the incorporated modules are described. Aerodynamic optimizations of a biconic re-entry capsule with respect to the lift-to-drag ratio, the effective volume and the stability are presented and discussed. The method proves to be a robust and relative efficient tool for aerodynamic design of modern aerospace vehicles. An increase in the performance of computer systems will result in an increase in the efficiency as well. It is shown that the method keeps and sometimes expands the established knowledge base of experienced engineers but reduces the design cycle times significantly. |
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