Supersonic Combustion Experimental Investigation at T2 Hypersonic Shock Tunnel

  • D. Romanelli Pinto
  • T. V. C. Marcos
  • R. L. M. Alcaide
  • A. C. Oliveira
  • J. B. ChanesJr.
  • P. G. P. Toro
  • M. A. S. Minucci
Conference paper

Introduction

The aerospace technological products have grown that one cannot conceive of putting payloads (satellites) into Earth orbit or beyond using technologies in operation (rockets carry out solid or liquid fuel). The knowledge required to keep the current launching vehicles is already so high that if the countries do not have a technological support for their own industry, they will depend on of the supplier countries and not have independent capacity sustained. Aerospace vehicle limitations for launching payloads into orbit or beyond require a continuous reduction in size, weight and power consumption of launch vehicles. Some solutions to these challenges require paradigm shifts, new production methods, and new technologies of strategic nature. The requirements of platformslaunched satellites, high performance and reliability, as well as the strict limitations of fuel (reduction of size, weight and power consumption) for launching payloads into orbit or beyond provide the development of hypersonic aircraft using hypersonic airbreathing propulsion based on supersonic combustion.

Keywords

Shock Wave Shock Tube Launch Vehicle High Enthalpy Supersonic Combustion 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

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    Curran, E.T.: Scramjet Engines: The First Forty Years. Journal of Propulsion and Power 17(6) (November-December 2001)Google Scholar
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    Nagamatsu, H.T.: Shock Tube Technology and Design. In: Ferri, A. (ed.) Fundamental Data Obtained from Shock Tube Experiments, ch. III. Pergamon Press (1961)Google Scholar
  3. 3.
    Nascimento, M.A.C.: Gaseous Piston Effect in Shock Tube/Tunnel When Operating in the Equilibrium Interface Condition. Doctoral Thesis. Instituto Tecnológico de Aeronáutica - ITA, São José dos Campos, SP, Brazil (October 1997) (in English) Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • D. Romanelli Pinto
    • 1
  • T. V. C. Marcos
    • 1
  • R. L. M. Alcaide
    • 1
  • A. C. Oliveira
    • 1
  • J. B. ChanesJr.
    • 1
  • P. G. P. Toro
    • 1
  • M. A. S. Minucci
    • 1
  1. 1.Laboratory of Aerothermodynamics and HypersonicsInstitute for Advanced StudiesSão José dos CamposBrazil

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