Thermal-structural modelling of TDLAS system for SCRAMSPACE hypersonic flight test
Paper
Dasgupta, Arnab, Choudhury, Rishabh, Neely, Andrew, O'Byrne, Sean and Kurtz, Joe. 2012. "Thermal-structural modelling of TDLAS system for SCRAMSPACE hypersonic flight test." 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2012). Tours, France 24 - 28 Sep 2012 United States.
| Paper/Presentation Title | Thermal-structural modelling of TDLAS system for SCRAMSPACE hypersonic flight test |
|---|---|
| Presentation Type | Paper |
| Authors | Dasgupta, Arnab, Choudhury, Rishabh, Neely, Andrew, O'Byrne, Sean and Kurtz, Joe |
| Journal or Proceedings Title | Proceedings of the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2012) |
| Article Number | 2012-5900 |
| Year | 2012 |
| Place of Publication | United States |
| ISBN | 9781600869310 |
| Web Address (URL) of Paper | https://arc.aiaa.org/doi/abs/10.2514/6.2012-5900 |
| Conference/Event | 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2012) |
| Event Details | 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2012) Event Date 24 to end of 28 Sep 2012 Event Location Tours, France |
| Abstract | A thermal-structural analysis of the TDLAS (Tunable Diode Laser Absorption Spectroscopy) system used on the SCRAMSPACE mission was performed to determine the integrity of the in-flight experiment when subjected to descent heat loads. This analysis is essential for the design of optical sensing equipment, which needs to survive the high temperatures generated in hypersonic flight. Firstly, in-flight temperatures reached by critical electro-optical components due to viscous heating were determined. In addition, the structural viability of the sapphire optical window was analysed to ensure it surpassed requirements at flight heating conditions. Lastly, the effect that in-flight heating has on the optical alignment of the system is currently being investigated. It was found that electronic components will operate within recommended temperature bounds. In addition, numerical and experimental analysis verified the flight worthiness and seal integrity of the sapphire window when subjected to the simulated hypersonic flight conditions. © 2012 by Arnab Dasgupta and Andrew Neely. |
| Keywords | Electro-optical components; Electronic component; Heating conditions; Numerical and experimental analysis; Optical alignments; Structural viability; Thermal-structural analysis; Tunable diode laser absorption spectroscopy |
| Public Notes | There are no files associated with this item. |
| Byline Affiliations | University of New South Wales |
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