Static Stability of the SCRAMSPACE I Mach 8 Hypersonic Flight Experiment

Brown, Laurie M.; Tirtey, Sandy; Staden, Paul A. van; Creagh, Michael

doi:10.2514/6.2012-5936

Cited by 3 publications

(2 citation statements)

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“…In this system, the origin is located at the start of the scramjet combustion chamber. The final vehicle measured 1857 mm long with a maximum diameter of 356 mm and included four rear-mounted ceramic matrix composite fins, provided by German Aerospace Center (DLR) Stuttgart, for vehicle stability during descent [13]. In the launch configuration, a nose cone was inserted into the vehicle to protect the internal flowpath during ascent.…”

Section: Flight Vehicle and Trajectorymentioning

confidence: 99%

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Aerothermal–Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Ascent

Capra

Brown

Boyce

et al. 2015

Journal of Spacecraft and Rockets

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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. NomenclatureSubscripts amb = ambient r = radiative m = melting y = yield T = tensile 0 = initial

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Section: Flight Vehicle and Trajectorymentioning

confidence: 99%

“…2a) and flight conditions for the experiment were selected to achieve a meaningful investigation of fundamental scramjet combustion processes [10]. These requirements, along with stability considerations [13,14], subsequently influenced the final design of the external shell of the free-flying vehicle, shown in Fig. 2b.…”

Section: Flight Vehicle and Trajectorymentioning

confidence: 99%