Development study of precooled-cycle hypersonic turbojet engine for flight demonstration

Tetsuya Sato, Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima, Keiichi Okai, Kazuhisa Fujita, Daisaku Masaki, Motoyuki Hongo, Toyohiko Ohta

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper describes a development study of a precooled-cycle hypersonic turbojet engine for the first stage of TSTO space plane and hypersonic airplane. With reflecting the key technologies accumulated from ATREX (Expander cycle ATR engine) ground tests, the next flyable subscale engine "S-engine" is now developed. S-engine has 23 cm × 23 cm of rectangular cross section, 2.2 m of the overall length and about 100 kg of the weight employing a variable-geometry rectangular inlet and nozzle. It produces 1.2 kN of thrust at SLS, which corresponds to 1/4 of the ATREX engine. Design of the hypersonic components such as the inlet, precooler and nozzle has been finished and their aerodynamic performances were verified by wind tunnel tests and CFD analyses. A prototype model of the diagonal-flow compressor whose pressure ratio is 6 was manufactured. Its rotating tests under the very-low pressure conditions are now in progress. The reverse-flow annular combustion chamber was successfully tested. The first flight test of the S-engine is to be conducted in 2008 by the Balloon-based Operation Vehicle (BOV) which is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high altitude balloon. After 40-second free-fall, the vehicle pulls up and S-engine operates for 30 seconds at about Mach 2. High altitude tests of the engine components corresponding to the BOVs flight condition have been conducted.

Original languageEnglish
Title of host publicationAIAA 57th International Astronautical Congress, IAC 2006
Pages6336-6343
Number of pages8
Publication statusPublished - 2006 Dec 1
EventAIAA 57th International Astronautical Congress, IAC 2006 - Valencia, Spain
Duration: 2006 Oct 22006 Oct 6

Publication series

NameAIAA 57th International Astronautical Congress, IAC 2006
Volume9

Conference

ConferenceAIAA 57th International Astronautical Congress, IAC 2006
CountrySpain
CityValencia
Period06/10/206/10/6

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ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Sato, T., Taguchi, H., Kobayashi, H., Kojima, T., Okai, K., Fujita, K., Masaki, D., Hongo, M., & Ohta, T. (2006). Development study of precooled-cycle hypersonic turbojet engine for flight demonstration. In AIAA 57th International Astronautical Congress, IAC 2006 (pp. 6336-6343). (AIAA 57th International Astronautical Congress, IAC 2006; Vol. 9).