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- W2317651188 abstract "For the development of reusable launchers, new technology has to be developed and tested that requires a hypersonic environment that cannot be reproduced in ground-based facilities. Small and low cost re-entry modules are needed for hypersonic experiments and the shape optimisation for such a re-entry module taking into account the required performance is presented in this paper. For the generic module shape, a blunted bi-cone has been selected that is simple to manufacture, has good stability properties and good potentials for various aerodynamic and material experiments. The cooling of the spherical nose is based on nucleate pool boiling of water. The aerodynamic design is done using a Response Surface Methodology (RSM) that includes the Taguchi method, a parametric multi-disciplinary design method with which the effects of changing several geometric design parameters in an ‘all-at-the-same-time’ approach can be studied, instead of the more traditional ‘one-at-atime’ approach. Each of the design iterations includes an aerodynamic analysis based on the Modified Newtonian method and a three-degrees-of-freedom trajectory analysis. Generating response surfaces for each of the performance indices and optimising them with a multiobjective optimisation method, a set of geometric parameters is found that gives the best alternative for each of the performance indices. Results of the verification of the (sub-) optimal design are included." @default.
- W2317651188 created "2016-06-24" @default.
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- W2317651188 date "2002-06-26" @default.
- W2317651188 modified "2023-09-26" @default.
- W2317651188 title "Shape Optimization for a Small Experimental Re-entry Module" @default.
- W2317651188 cites W2314645512 @default.
- W2317651188 doi "https://doi.org/10.2514/6.2002-5261" @default.
- W2317651188 hasPublicationYear "2002" @default.
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