Design of an Airbreathing second stage for a rocket-scramjet-rocket launch vehicle

Jazra, Thomas, Preller, Dawid and Smart, Michael K. (2013) Design of an Airbreathing second stage for a rocket-scramjet-rocket launch vehicle. Journal of Spacecraft and Rockets, 50 2: 411-422. doi:10.2514/1.A32381


Author Jazra, Thomas
Preller, Dawid
Smart, Michael K.
Title Design of an Airbreathing second stage for a rocket-scramjet-rocket launch vehicle
Journal name Journal of Spacecraft and Rockets   Check publisher's open access policy
ISSN 0022-4650
1533-6794
Publication date 2013-03
Sub-type Article (original research)
DOI 10.2514/1.A32381
Volume 50
Issue 2
Start page 411
End page 422
Total pages 12
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2014
Language eng
Abstract The most promising alternative to rockets for improved access to space involves staged systems using airbreathing propulsion. With scramjet technology improving, a number of airbreathing assisted access-to-space vehicle concepts have recently been proposed, including a three-stage rocket-scramjet-rocket launch architecture for payload masses on the order of 100 kg. This article presents a design methodology developed for the airbreathing second stage of such a system. This methodology uses multidisciplinary design optimization with simplified methods for the calculation of vehicle aerodynamics, propulsion, and mass. It has been applied to the design of a reusable scramjet-powered winged cone vehicle with a near-term Mach 6-12 hydrogen-fueled scramjet for propulsion. Through the manipulation of five vehicle design parameters, including the size and position of the engines, and flying the vehicle along constant dynamic pressure trajectories, a configuration was developed to maximize payload mass fraction to low Earth orbit. The mass of the whole system was 11.3 t, and that of the airbreathing vehicle was 4625 kg, delivering a 211 kg payload to low Earth orbit. This corresponds to an overall payload mass fraction of 1.87%. This methodology supplies a useful framework for developing a better understanding of the key drivers for airbreathing hypersonic accelerators.
Keyword Scramjet
Space
Combustion
Propulsion
Hypersonic accelerators
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2014 Collection
 
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Citation counts: TR Web of Science Citation Count  Cited 3 times in Thomson Reuters Web of Science Article | Citations
Scopus Citation Count Cited 14 times in Scopus Article | Citations
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