Air Breathing Rocket Engines and Sustainable Launch Systems

Article Preview

Abstract:

An air-breathing rocket engine inhales oxygen from the air for about half the flight, so it doesn't have to store the gas onboard. So at take-off, an air-breathing rocket weighs much less than a conventional rocket, which carries all of its fuel and oxygen onboard. Air breathing rockets, combine the performance characteristics of both rocket and ramjet engines. An air-breathing engine gets its initial take-off power from specially designed rockets, called air-augmented rockets, that boost performance about 15 percent over conventional rockets. When the vehicle's velocity reaches twice the speed of sound, the rockets are turned off and the engine relies totally on oxygen in the atmosphere to burn the hydrogen fuel. Once the vehicle's speed increases to about 10 times the speed of sound, the engine converts to a conventional rocket-powered system to propel the vehicle into orbit. And therefore reducing a vehicle's weight decreases cost significantly. And since an air breathing engine cannot get required initial take off thrust, various launch types like air augmented rockets, horizontal launch mode courtesy hybrid engine, magnetic levitation launch systems are used for initial thrust requirements ,thus reducing fuel emissions and increases net efficiency of rockets. Hence air breathing engines can be implemented to address energy considerations and reduce costs.

You might also be interested in these eBooks

Info:

Periodical:

Pages:

310-315

Citation:

Online since:

November 2012

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2012 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] Dixon, S.C., NASA R&T for Aerospace Plane Vehicles, Langley Research Centre, NASA Technical Memorandum.

Google Scholar

[2] Escher, W.J.D., and Flomnes, B. J., et al, A Study of Composite Propulsion Systems for Advanced Launch Vehicle Applications, Final report on NASA Contract NAS7-377, The Marquardt Corporation, VanNuys, CA.

Google Scholar

[3] Hoge H. J. And Segars R. A (1965) Choked Flow, a generalisation of the concept and experimental data, AIAA J. 3, 2177-2183.

DOI: 10.2514/3.3343

Google Scholar

[4] B.R.A. Burns, HOTOL space transport for the twenty first century, Proceedings of the Institute of Mechanical Engineers, Part G – Journal of Aerospace Engineering, 204, pp.101-110, (1990).

DOI: 10.1243/pime_proc_1990_204_216_02

Google Scholar

[5] Skylon - A Realistic Single Stage Space plane Alan Bond, Richard Varvill, John Scott-Scott and Tony Martin Spaceflight, Volume 45, pp.158-161, April (2003).

Google Scholar

[6] N.V. Taylor and C.M. Hempsell, Optimising Expansion Deflection nozzles for Vacuum Thrust, The Aeronautical Journal, 108, pp.515-522, (2004).

DOI: 10.1017/s0001924000000348

Google Scholar

[7] Maglev tested as launch aid., il Aviation & Space Technology v151 no24 p.78 D13.

Google Scholar

[8] C.R. Carlson and J.S. Simpson, Low-Cost ELV Technology Applicability to Spacelifters, (AIAA 93-4124). September (1993).

DOI: 10.2514/6.1993-4124

Google Scholar