Hostname: page-component-cd9895bd7-dk4vv Total loading time: 0 Render date: 2024-12-18T23:08:16.548Z Has data issue: false hasContentIssue false
  • English
  • Français

A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

Part of: 31st Congress of The International Council of the Aeronautical Sciences (ICAS)

Published online by Cambridge University Press:  28 August 2019

R. Fusaro Open the ORCID record for R. Fusaro [Opens in a new window] ,
D. Ferretto ,
N. Viola ,
V. Fernandez Villace  and
J. Steelant
R. Fusaro
Affiliation:
Politecnico di TorinoTurin, Italy
D. Ferretto
Affiliation:
Politecnico di TorinoTurin, Italy
N. Viola
Affiliation:
Politecnico di TorinoTurin, Italy
V. Fernandez Villace
Affiliation:
European Space Agency –ESTECNoordwijk, Netherlands
J. Steelant
Affiliation:
European Space Agency –ESTECNoordwijk, Netherlands
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper addresses a methodology to parametrically size thermal control subsystems for high-speed transportation systems during the conceptual design phase. This methodology should be sufficiently general to be exploited for the derivation of Estimation Relationships (ERs) for geometrically sizing characteristics as well as mass, volume and power budgets both for active (turbopumps, turbines and compressors) and passive components (heat exchangers, tanks and pipes). Following this approach, ad-hoc semi-empirical models relating the geometrical sizing, mass, volume and power features of each component to the operating conditions have been derived. As a specific case, a semi-empirical parametric model for turbopumps sizing is derived. In addition, the Thermal and Energy Management Subsystem (TEMS) for the LAPCAT MR2 vehicle is used as an example of a highly integrated multifunctional subsystem. The TEMS is based on the exploitation of liquid hydrogen boil-off in the cryogenic tanks generated by the heat load penetrating the aeroshell throughout the point-to-point hypersonic mission. Eventually, specific comments about the results will be provided together with suggestions for future improvements.

Keywords

Thermal and Energy Management SystemSizing modelsturbopumpsLAPCAT MR2
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1268 , October 2019 , pp. 1508 - 1544
Copyright
© Royal Aeronautical Society 2019 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

A version of this paper was presented at the 31st ICAS Congress of the International Council of the Aeronautical Sciences in Belo Horizonte, Brazil in September 2018.

References

REFERENCES

Steelant, J. and Langener, T. The LAPCAT-MR2 hypersonic cruiser concept, ICAS-2014-0428, 29th Congress of the International Council of the Aeronautical Sciences, 7–12 September 2014, St. Petersburg.Google Scholar
Steelant, J., Varvill, R., Defoort, S., Hannemann, K. and Marini, M. Achievements obtained for sustained hypersonic flight within LAPCAT-II project, International Space Planes and Hypersonic Systems and Technologies Conference, 6–9 July 2015, Glasgow, Scotland.Google Scholar
Hart, T. J. Design criteria and analyses for thin-walled pressurized vessels and interstage structures. Lockheed Missiles and Space Co Inc, 1959, Sunnyvale California, USA.Google Scholar
Sobin, A. J. Turbopump systems for liquid rocket engines, NASA Space Vehicle Design Criteria SP-8107, 1974, Lewis Research Center, Cleveland, Ohio, USA.Google Scholar
Campbell, W. E. and Farquhar, J. Centrifugal Pumps for Rocket Engines, NERVA Rocket Operations, 1974, Azusa, California, USA.Google Scholar
Huzel, D. K. and Huang, D. H. Design of Liquid Propellant Rocket Engines, Rocketdyne Division North America Aviation Inc., 1967, Washington DC, USA.Google Scholar
Epple, P., Durst, F. and Delgado, A. A theoretical derivation of the Cordier diagram for turbomachines, Proceedings of the IMechE Part C: Journal of Mechanical Engineering Science, 2010, 225, (2), pp 354–368.CrossRefGoogle Scholar
Saunders, D. J. A method of calculating the weight and dimensions of a turbopump for rocket propellants, Technical note of the Royal Aircraft Establishment, 1979.Google Scholar
Fernández-Villacá, V., Paniaguá, G. and Steelant, J. Installed performance evaluation of an air turbo-rocket expander engine, Journal of Aerospace Science and Technology, 2014, 35, pp 63–79. doi: 10.1016/j.ast.2014.03.005.CrossRefGoogle Scholar
Meerts, C. and Steelant, J. Air intake design for the acceleration propulsion unit of the LAPCAT-MR2 hypersonic aircraft, 5th European Conference for Aeronautics and Space Sciences (EUCASS), 1–5 July 2013, Munich, Germany.Google Scholar
Roncioni, P., Natale, P., Marini, M., Langener, T. and Steelant, J. Numerical Simulations and Performance Assessment of a Scramjet Powered Cruise Vehicle at Mach 8, Journal of Aerospace Science and Technology,January 2015, 42, pp 218–228. doi: 10.1016/j.ast.2015.01.006CrossRefGoogle Scholar
Langener, T., Erb, S. and Steelant, J. Trajectory simulation and optimization of the LAPCAT-MR2 hypersonic cruiser concept, 29th Congress of the International Council of the Aeronautical Sciences, 7–12 September 2014, St. Petersburg, Russia.Google Scholar
Fernandez Villace, V. and Steelant, J. The thermal paradox of hypersonic cruisers, International Space Planes and Hypersonic Systems and Technologies Conference, 6–9 July 2015, Glasgow, Scotland.Google Scholar
Steelant, J. and van Duijn, M. Structural analysis of the LAPCAT-MR2 waverider-based vehicle, 17th AIAA International Space Planes and Hypersonic Systems and Technology Conference, 11–14 April 2011, San Francisco, California, AIAA 201–2336.Google Scholar
Balland, S., Villace, Fernandez, V. and Steelant, J. Thermal and energy management for hypersonic cruise vehicles –cycle analysis, International Space Planes and Hypersonic Systems and Technologies Conference, 6–9 July 2015, Glasgow, Scotland.CrossRefGoogle Scholar
Rangwala, A. S. Turbo-Machinery Dynamics: Design and Operations, Mechanical Engineering Series, McGraw-Hill, 2005, New York NY, USA.Google Scholar
Ferretto, D., Vercella, V., Fusaro, R., Viola, N., Fernandez Villace, V. and Steelant, J. Preliminary design and sizing of the thermal and energy management subsystem for LAPCAT MR2, Presented at the HiSST: International Conference on High-Speed Vehicle Science Technology, 26–29 November 2018, Moscow, Russia.Google Scholar