Title:
StarRunner: A Single-Stage-to-Orbit, Airbreathing, Hypersonic Propulsion System
StarRunner: A Single-Stage-to-Orbit, Airbreathing, Hypersonic Propulsion System
Author(s)
Biltgen, Patrick Thomas
Lafleur, Jarret M.
Loughman, Josh
Martin, Robert
Flaherty, Kevin W.
Cho, Min
Becker, Keith
Ong, Chester
Olds, John R.
Lafleur, Jarret M.
Loughman, Josh
Martin, Robert
Flaherty, Kevin W.
Cho, Min
Becker, Keith
Ong, Chester
Olds, John R.
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Abstract
In response to the request for proposal (RFP) for the 2003 AIAA Undergraduate Team
Engine Design Competition, the FAS Propulsion Design team from the Georgia Institute of
Technology presents StarRunner: A Single-Stage-to-Orbit (SSTO), Airbreathing, Hypersonic
Propulsion System. Low-cost, highly reliable access to low-Earth orbit (LEO) and the
International Space Station (ISS) is an area of continuing research and debate. StarRunner is
proposed to supplement a notional Crew Transfer Vehicle through the ability to deliver a
25,000 lb payload to the ISS. The horizontal takeoff/horizontal landing (HTHL) vehicle
makes use of a turbine-based combined cycle (TBCC) propulsion system consisting of 14
low-bypass-ratio turbofan engines and a dual-mode ramjet/scramjet propulsion system for
high-speed flight. The vehicle also takes advantage of ultra-high-temperature ceramic
thermal protection materials and uses hydrogen fuel for regenerative cooling of engine
components. StarRunner is compatible with standard runways, with a gross takeoff weight of
approximately 1,000,000 lbs, and has a cost per pound to orbit of approximately $825/lb.
This advanced, fully reusable space transport vehicle and integrated propulsion system
design demonstrates student efforts to understand issues facing the space launch community.
Future enabling and enhancing technologies for TBCC SSTO launch vehicles are explored
and analyzed. The final StarRunner design addresses and proposes several innovative
solutions to traditional problems.
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Date Issued
2004-07
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705375 bytes
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Text
Resource Subtype
Paper