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Research Papers: Forced Convection

Thermostructural Design of a Flying Winglet Experimental Structure for the EXPERT Re-entry Test

[+] Author and Article Information
M. Ferraiuolo

Laboratory of Computational Mechanics, CIRA-Italian Aerospace Research Centre, via Maiorise snc, Capua, 81043, Italym.ferraiuolo@cira.it

A. Riccio

Laboratory of Computational Mechanics, CIRA-Italian Aerospace Research Centre, via Maiorise snc, Capua, 81043, Italya.riccio@cira.it

M. Gigliotti

 University of Poitiers, Laboratoire de Mécanique et Physique des Matériaux (LMPM), Ecole Nationale Supérieure de Mécanique et Aérotechnique (ENSMA), 1 Avenue Ader, 86961 Chasseneuil-Futuroscope, Francemarco.gigliotti@lmpm.ensma.fr

D. Tescione

Laboratory of Computational Mechanics, CIRA-Italian Aerospace Research Centre, via Maiorise snc, Capua, 81043, Italyd.tescione@cira.it

R. Gardi

Space Programs Office, CIRA-Italian Aerospace Research Centre, via Maiorise snc, Capua, 81043, Italyr.gardi@cira.it

G. Marino

Space Programs Office, CIRA-Italian Aerospace Research Centre, via Maiorise snc, Capua, 81043, Italyg.marino@cira.it

J. Heat Transfer 131(7), 071701 (May 05, 2009) (7 pages) doi:10.1115/1.3109242 History: Received May 20, 2008; Revised February 06, 2009; Published May 05, 2009

Within the framework of the European Experimental Re-entry Test Bed (EXPERT) Program, aimed at improving the understanding of physical phenomena occurring during the return of space vehicles from space to earth, the design of a flying winged experimental payload has been performed in order to assess the thermomechanical behavior and resistance of ultrahigh temperature ceramics (UHTC) in real flight aerothermal environment. The EXPERT flying winglet article is intended to reproduce such conditions. Particular interest covers the design of the interfaces between the UHTC winglet and the EXPERT capsule thermal protection systems since thermal stresses arise during the re-entry phase. The fixation of the winglet to the capsule is achieved by means of dedicated bolts that must tolerate mechanical loads occurring at the first stages of the flight, that is, lift-off, ascent, and separation stages. The thermostructural design is performed by employing ANSYS /Workbench finite element commercial code; simulations take into account transient thermostructural loading conditions, the elastic-fragile behavior of the ceramic materials, and the temperature dependent elastic-plastic behavior of the capsule thermal protection systems. In the postprocessing phase, UHTC critical areas have been identified by following two different approaches. The first approach is deterministic and consists in applying a maximum stress criterion, the stress at a node is compared with the temperature dependent strength at that node. The second approach, which is commonly employed for elastic-fragile materials, is probabilistic and consists in applying a Weibull-like failure criterion. Thermal and structural analyses simulating the re-entry phase have demonstrated that the maximum stresses and temperatures evaluated do not exceed their corresponding limits. Then, a configuration respecting all the requirements of the design has been identified, and its thermal and mechanical performances are discussed in detail.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Winglet connection with PM1000 support interface and winglet location on the EXPERT capsule

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Figure 2

Assembling scheme

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Figure 3

Geometry of the model considered for finite element analyses

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Figure 4

Air flow direction around the winglet

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Figure 5

Heat flux variation with time for the stagnation point

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Figure 6

Heat flux distribution at t=115 s

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