Super-orbital re-entry in Australia: laboratory measurement, simulation and flight observation [Keynote lecture]

Buttsworth, David and Jacobs, Peter and Potter, Daniel and Mudford, Neil and D'Souza, Mary and Eichmann, Troy and Jenniskens, Peter and McIntyre, Tim and Jokic, Michael and Jacobs, Carolyn and Upcroft, Ben and Khan, Razmi and Porat, Hadas and Neely, Andrew and Lohle, Stefan (2012) Super-orbital re-entry in Australia: laboratory measurement, simulation and flight observation [Keynote lecture]. In: ISSW28: 28th International Symposium on Shock Waves, 17-22 Jul 2011, Manchester, United Kingdom.

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Abstract

There are large uncertainties in the aerothermodynamic modelling of super-orbital re-entry which impact the design of spacecraft thermal protection systems (TPS). Aspects of the thermal environment of super-orbital re-entry flows can be simulated in the laboratory using arc- and plasma jet facilities and these devices are regularly used for TPS certification work [5]. Another laboratory device which is capable of simulating certain critical features of both the aero and thermal environment of super-orbital re-entry is the expansion tube, and three such facilities have been operating at the University of Queensland in recent years[10]. Despite some success, wind tunnel tests do not achieve full simulation, however, a virtually complete physical simulation of particular re-entry conditions can be obtained from dedicated flight testing, and the Apollo era FIRE II flight experiment [2] is the premier example which still forms an important benchmark for modern simulations. Dedicated super-orbital flight testing is generally considered too expensive today, and there is a reluctance to incorporate substantial instrumentation for aerothermal diagnostics into existing missions since it may compromise primary mission objectives. An alternative approach to on-board flight measurements, with demonstrated success particularly in the ‘Stardust’ sample return mission, is remote observation of spectral emissions from the capsule and shock layer [8]. JAXA’s ‘Hayabusa’ sample return capsule provides a recent super-orbital reentry example through which we illustrate contributions in three areas: (1) physical simulation of super-orbital re-entry conditions in the laboratory; (2) computational simulation of such flows; and (3) remote acquisition of optical emissions from a super-orbital re entry event


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Item Type: Conference or Workshop Item (Commonwealth Reporting Category E) (Paper)
Refereed: Yes
Item Status: Live Archive
Additional Information: Accepted version deposited in accordance with the copyright policy of the publisher.
Depositing User: Assoc Prof David Buttsworth
Faculty / Department / School: Historic - Faculty of Engineering and Surveying - Department of Mechanical and Mechatronic Engineering
Date Deposited: 09 Sep 2011 04:01
Last Modified: 03 Jul 2013 00:46
Uncontrolled Keywords: spacecraft; thermal protection; simulation; aerospace engineering; expansion tube
Fields of Research (FOR2008): 08 Information and Computing Sciences > 0801 Artificial Intelligence and Image Processing > 080110 Simulation and Modelling
09 Engineering > 0901 Aerospace Engineering > 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
09 Engineering > 0915 Interdisciplinary Engineering > 091502 Computational Heat Transfer
Socio-Economic Objective (SEO2008): E Expanding Knowledge > 97 Expanding Knowledge > 970109 Expanding Knowledge in Engineering
Identification Number or DOI: doi: 10.1007/978-3-642-25688-2_5
URI: http://eprints.usq.edu.au/id/eprint/19608

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