| Autor: |
FUJIMOTO, Keiichiro, ITOH, Takayuki, NEGISHI, Hideyo, NAKAMURA, Ryoh, WATANABE, Yasuhide, TANABE, Kota |
| Rok vydání: |
2019 |
| Předmět: |
|
| DOI: |
10.13009/eucass2019-755 |
| Popis: |
Successful result of HTV small re-entry capsule (HSRC) project was presented. Computational aerothermodynamic analysis methods and its contributions to the HSRC\'s design are overviewed and discussed. Local heat flux peak and the pressure increase are generated due to the hot gas main stream collision onto the wall near the reaction control system (RCS) nozzle exit. Augmentation factor is roughly from 2.0 to 8.0, which is increased by the larger mass flow rate of the free-stream. Effect on the aerodynamic force and moment is significant, which is at least 5 times larger as comparing with the RCS thrust. Severe ablator erosion was not found and the precise GNC was achieved. TPS shell separation failure and collision risks were identified and the shell release air-bag was employed. Its importance on the reliable parachute deployment is confirmed by the post-flight analysis. Conventional MILES-type computational fluid dynamics (CFD) analysis is quantitatively accurate even for the unsteady flows such as the aeroacoustic characteristics prediction. Pressure fluctuation is induced by the unsteady shear layer whose frequency changes with the flow structures such as the local shock on the shear layer. Input sound pressure level is decided based on CFD. 6DoF trajectory analysis was carried out to evaluate the sidewind criterion to prevent the turn-over rotation at the low dynamic pressure phase just after the separation. Drop test was succeeded by meeting the side-wind criterion. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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