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Heat Transfer Analysis for a Winged Reentry Flight Test Bed
Antonio Viviani, Giuseppe Pezzella
Pages - 330 - 345     |    Revised - 05-08-2009     |    Published - 01-09-2009
Volume - 3   Issue - 3    |    Publication Date - June 2009  Table of Contents
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KEYWORDS
Atmospheric Reentry, Aerothermochemistry, Nonequilibirum Hypersonic Flow, Aeroheating, Thermal Protection System
ABSTRACT
In this paper we deal with the aero-heating analysis of a reentry flight demonstrator helpful to the research activities for the design and development of a possible winged Reusable Launch Vehicle. In fact, to reduce risks in the development of next generation reusable launch vehicles, as first step it is suitable to gain deep design knowledge by means of extensive numerical computations, in particular for the aero-thermal environment the vehicle has to withstand during reentry. The demonstrator under study is a reentry space glider, to be used both as Crew Rescue Vehicle and Crew Transfer Vehicle for the International Space Station. It is designed to have large atmospheric manoeuvring capability, to test the whole path from the orbit down to subsonic speeds and then to the landing on a conventional runway. Several analysis tools are integrated in the framework of the vehicle aerothermal design. Between the others, we used computational analyses to simulate aerothermodynamic flowfield around the spacecraft and heat flux distributions over the vehicle surfaces for the assessment of the vehicle Thermal Protection System design. Heat flux distributions, provided for equilibrium conditions of radiation at wall and thermal shield emissivity equal to 0.85, highlight that the vehicle thermal shield has to withstand with about 1500 [kW/m2] and 400 [kW/m2] at nose and wing leading edge, respectively. Therefore, the fast developing new generation of thermal protection materials, such as Ultra High Temperature Ceramics, are available candidate to built the thermal shield in the most solicited vehicle parts. On the other hand, away from spacecraft leading edges, due to the low angle of attack profile followed by the vehicle during descent, the heat flux is close to values attainable with conventional heat shield. Also, the paper shows that the flying test bed is able to validate hypersonic aerothermodynamic design database and passenger experiments, including thermal shield and hot structures, giving confidence that a full-scale development can successfully proceed.
CITED BY (5)  
1 Viviani, A., & Pezzella, G. (2015). Launchers: Present and Future. In Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles (pp. 767-867). Springer International Publishing.
2 Minisci, E., & Vasile, M. (2013). Robust Design of a Reentry Unmanned Space Vehicle by Multifidelity Evolution Control. AIAA journal, 51(6), 1284-1295.
3 Giuseppe Pezzella , “Aerodynamic Design of the Vertical Takeoff Hopper Concept of Future Launchers Preparatory Programme”, Applied Computational Fluid Dynamics, pp. 177-200.
4 L. Hou, H. Li, P. Yu and G. Liang, “A New Multi-disciplinary Robust Optimization Method for Micro Re-entering Lifting-Body Design”, Engineering Recent Advances in Computer Science and Information Engineering Lecture Notes in Electrical Engineering, 126, pp. 515-524, 2012.
5 E. Minisci and M. Vasile, “Robust design of a re-entry unmanned space vehicle by multi-fidelity evolution control”, Proceeding GECCO '11 in 13th annual conference on Genetic and evolutionary computation ACM New York, NY, USA ©2011.
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Professor Antonio Viviani
- Italy
antonio.viviani@unina2.it
Dr. Giuseppe Pezzella
- Italy