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

Capra, Bianca R., Brown, L. M., Boyce, R. R. and Tirtey, S. C. (2015) Aerothermal-structural analysis of a rocket-launched Mach 8 scramjet experiment: ascent. Journal of Spacecraft and Rockets, 52 3: 684-696. doi:10.2514/1.A33112


Author Capra, Bianca R.
Brown, L. M.
Boyce, R. R.
Tirtey, S. C.
Title Aerothermal-structural analysis of a rocket-launched Mach 8 scramjet experiment: ascent
Journal name Journal of Spacecraft and Rockets   Check publisher's open access policy
ISSN 0022-4650
1533-6794
Publication date 2015-05
Year available 2015
Sub-type Article (original research)
DOI 10.2514/1.A33112
Open Access Status
Volume 52
Issue 3
Start page 684
End page 696
Total pages 13
Place of publication Reston, VA United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2016
Language eng
Abstract This paper reports on the methodology and results of a weak-coupled aerothermal–structural analysis on the ascent phase of the SCRAMSPACE Mach 8 scramjet flight experiment. This vehicle was essentially unshrouded during the flight trajectory, relying on the thin, 5 mm thick aluminum 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 150 K 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.
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2016 Collection
 
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