Aerothermodynamic Shape Optimization for Re-entry Capsule Using Genetic Algorithms

Space hasn’t been for a long time now the final frontier, in the last years more and more spaceships have accessed outer space for different missions, some of them being required to return. The actual and main task of researchers is to find an optimal geometry for new generation of spacecraft which...

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Bibliographic Details
Published in:INCAS bulletin 2019-10, Vol.11 (4), p.71-79
Main Authors: BUNESCU, Ionut, PRICOP, Mihai-Victor, STOICAN, Mihaita Gilbert, DINA, Adrian Gheorghe
Format: Article
Language:English
Subjects:
Acceleration
Accuracy
aerothermodynamic shape optimization
Configurations
Design optimization
Drag coefficients
Genetic algorithms
Geometry
Heat flux
Heat transfer
Inclination
Load
local inclination methods
Optimization
re-entry vehicles
Reentry vehicles
Reusable spacecraft
Shape optimization
Spacecraft
Thermal protection
Vehicles
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Summary:Space hasn’t been for a long time now the final frontier, in the last years more and more spaceships have accessed outer space for different missions, some of them being required to return. The actual and main task of researchers is to find an optimal geometry for new generation of spacecraft which must be reusable and fit the imposed loads (heat flux, pressure, acceleration). The purpose of this paper is to optimize the design of a re-entry capsule configuration, in order to minimize the maximum heat flux on the thermal protection system and to obtain a wanted imposed drag coefficient. For the optimization process we use genetic algorithms and for the solving process, local inclination methods. Even if the latter are low-fidelity methods and do not offer satisfying results on all conditions, we consider them to be good enough for a preliminary study of an optimal design. Thus, this paper purpose is to describe the procedure to obtain an optimal configuration which can be better analyzed with high-fidelity methods.
ISSN:2066-8201
2247-4528
DOI:10.13111/2066-8201.2019.11.4.7