Aerothermal-strucutral analysis of a rocket launched Mach 8 scramjet experiment : ascent

Capra, Bianca R., Brown, Laurie, Boyce, Russell R., & Tirtey, Sandy (2015) Aerothermal-strucutral analysis of a rocket launched Mach 8 scramjet experiment : ascent. Journal of Spacecraft and Rockets, 52(3), pp. 684-696.

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This paper reports on the methodology and results of a weak-coupled aerothermalstructural analysis on the ascent phase of the SCRAMSPACE Mach 8 scramjet flight experiment. This vehicle was essentially un-shrouded during the flight trajectory, relying on the thin, 5mm thick aluminium external shell of the payload to maintain structural integrity and protect the flight experiment. As such, understanding the thermal-structural response of the vehicle was imperative to mission success. Using two- and three-dimensional models, an iterative procedure was employed to compute the flowfield, convective heating, wall temperatures and structural coupling at flight times covering both peak heating and peak surface temperature. Accounting for such coupling resulted in a 150K reduction in wall temperature compared to the more conservative cold wall assumption. Despite this, peak temperatures remained of the order of 550 K. Further, thermally induced stresses within these regions were in excess of four times the material failure limits. Irreversible material failure during ascent was therefore concluded likely to occur on the external shell. Two alternate materials, steel 1006 and copper, were therefore assessed with the results indicating that steel sections on the external shell resulted in the best thermal-structural response of the payload.

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ID Code: 81835
Item Type: Journal Article
Refereed: Yes
Additional URLs:
DOI: 10.2514/1.A33112
ISSN: 0022-4650
Divisions: Current > Schools > School of Chemistry, Physics & Mechanical Engineering
Current > QUT Faculties and Divisions > Science & Engineering Faculty
Deposited On: 16 Feb 2015 22:59
Last Modified: 18 Oct 2015 23:43

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