The development of scramjet propulsion for alternative launch and payload delivery capabilities has comprised largely of ground experiments for the last 40 years. With the goal of validating the use of short duration ground test facilities, the University of Queensland, supported by a large international contingency, devised a ballistic re-entry vehicle experiment called HyShot to achieve supersonic combustion in flight above Mach 7.5. It consisted of a double wedge intake and two back-to-back constant area combustors; one supplied with hydrogen fuel at an equivalence ratio of 0.33 and the other un-fueled. Following a first launch failure on October 30th 2001, the University of Queensland conducted a successful second launch on July 30th, 2002. Post-flight data analysis of the second launch confirmed the presence of supersonic combustion during the approximately 3 second test window at altitudes between 35 and 29 km. Reasonable correlation between flight and some pre-flight shock tunnel tests was observed.
Flight Data Analysis of HyShot 2
13th AIAA/CIRA International Space Planes and Hypersonic Systems Technologies Conference ; 2005 ; Capua, Italy
2005-01-01
Preprint
No indication
English
Flight Data Analysis of the HYSHOT 2
AIAA | 2005
|Flight data analysis of the HyShot 2 scramjet flight experiment
Tema Archive | 2006
|POST FLIGHT ANALYSIS OF THE HYSHOT SUPERSONIC COMBUSTION FLIGHT EXPERIMENT IN HEG
British Library Conference Proceedings | 2004
|