Abstract
In this study, a conceptual design of a reusable unmanned space vehicle with multi-objective functions is conducted. To do that, the multi-objective genetic algorithm (MOGA) was used. To evaluate the performance of the space vehicles, several discipline were analyzed; weight, propulsion, aerothermodynamic and trajectory analysis. Three objective functions were selected; 1) minimization of weight, 2) minimization of landing speed and 3) maximization of the highest CL in the supersonic range. Moreover, the maximum dynamic pressure and heat flux were considered as constraints. All objective functions are in trade-off relationships with each other. The smallest weight vehicle has a very small wing size. The vehicle which has the highest CL in supersonic range has a closer angle between the flow and the lower surface of wing to angle which shows the highest CL on the flat surface. The vehicle which has the lowest landing speed had the largest wing, which generate sufficient lift.
Original language | English |
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Publication status | Published - 2018 |
Event | 10th International Conference on Computational Fluid Dynamics, ICCFD 2018 - Barcelona, Spain Duration: 9 Jul 2018 → 13 Jul 2018 |
Conference
Conference | 10th International Conference on Computational Fluid Dynamics, ICCFD 2018 |
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Country/Territory | Spain |
City | Barcelona |
Period | 9/07/18 → 13/07/18 |
Bibliographical note
Publisher Copyright:© ICCFD 2018.
Keywords
- Conceptual Design
- MDO
- MOGA
- Reusable Unmanned Space Vehicle