@inproceedings{f84a14076132433b9f54eae17c275f71,
title = "The optimal design and analysis of the IRDT system based on two-dimensional ballistic trajectory in atmosphere reentry",
abstract = "The modeling of two-dimensional reentry trajectory for the IRDT system is presented in this paper. The CFD simulation and theoretical formula is employed to compute the drag coefficient, and the final precise drag coefficient and trajectory of the IRDT system during the reentry is calculated through iteration process. With the result of final drag coefficient and trajectory data, the optimal design and analysis of the IRDT system is carried out. The heat flux on stagnation point, the maximum heat absorption on stagnation point and the maximum drag acceleration are chosen as optimizing restrictions to optimize the half taper angle and initial reentry angle of the IRDT system. The influences of different half taper angle and initial reentry angle under the same reentry height and velocity are investigated in this study. The results show that under the current technological level, the optimal half taper angle of the IRDT system is above 55°and the optimal initial reentry angle is between -2° and -2.7°. The investigation also provide the principle for the design of the IRDT system and long term goals for the IRDT subsystem development.",
author = "Rui Wang and Anping Hou",
note = "Publisher Copyright: {\textcopyright} 2015, American Institute of Aeronautics and Astronautics. All rights Reserved.; 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 ; Conference date: 06-07-2015 Through 09-07-2015",
year = "2015",
doi = "10.2514/6.2015-3672",
language = "英语",
isbn = "9781624103209",
series = "20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015",
publisher = "AIAA American Institute of Aeronautics and Astronautics",
booktitle = "20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015",
}