Performance Analysis of Pre-Cooled Turbojet Engines for Space Planes

• TAGUCHI Hideyuki

  Future Space Transportation Research Center, Institute of Space Technology and Aeronautics

• FUTAMURA Hisao

  Aeroengine Testing Technology Center, Institute of Space Technology and Aeronautics

• YANAGI Ryoji

  Aeroengine Testing Technology Center, Institute of Space Technology and Aeronautics

• MAITA Masataka

  Future Space Transportation Research Center, Institute of Space Technology and Aeronautics

Bibliographic Information

Other Title

• 宇宙航空機に適用する予冷ターボエンジンの性能解析

Abstract

The performance of pre-cooled turbojet engines for space planes is analyzed in this study. A program that combines engine performance analysis, flight analysis, and mass estimation is used to determine the payload injection capability of the system. The payload injection capability is then compared to systems with other engines. The pre-cooled turbojet engine has a liquid hydrogen pre-cooler to chill the hot air at high flight Mach number. The engine is considered to be operational up to Mach 6 with existing technologies of supersonic turbojet engines. The engine features high specific impulse and small propellant mass because it uses the air as oxidant. However, both propellant mass and engine mass should be taken into account because the engine mass tends to be much larger than that of rocket engines. A space transportation system with air-breathing engines has a different optimal trajectory than a system with conventional rocket engines, so air-breathing engines and rocket engines cannot be compared in a simple way. It is established that a fuel-rich pre-cooled turbojet engine with an equivalence ratio of nearly 5 is appropriate for single-stage-to-orbit space planes. The combination of a pre-cooled turbojet and a scramjet is proved to provide a larger payload injection capability than the combination of a liquefied air cycle engine and a scramjet.

Journal

• JAXA research and development report

  JAXA research and development report 4 1-37, 2005-03

  Japan Aerospace Exploration Agency

Keywords

• Hypersonic
• Engine
• Engine Cycle
• Flight Analysis
• Mass Estimation

Details

• CRID: 1571417127281006208
• NII Article ID: 110006297380
• NII Book ID: AA1192675X
• ISSN: 13491113
• Text Lang: ja
• Data Source:
  • CiNii Articles