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 TypePaper
AuthorsDasgupta, Arnab, Choudhury, Rishabh, Neely, Andrew, O'Byrne, Sean and Kurtz, Joe
Journal or Proceedings TitleProceedings of the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2012)
Article Number2012-5900
Year2012
Place of PublicationUnited States
ISBN9781600869310
Web Address (URL) of Paperhttps://arc.aiaa.org/doi/abs/10.2514/6.2012-5900
Conference/Event18th 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.

KeywordsElectro-optical components; Electronic component; Heating conditions; Numerical and experimental analysis; Optical alignments; Structural viability; Thermal-structural analysis; Tunable diode laser absorption spectroscopy
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Byline AffiliationsUniversity of New South Wales
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