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https://hdl.handle.net/2440/28796
Type: | Conference paper |
Title: | Launch vehicle mass reduction using a scramjet powered flight segment |
Author: | Tetlow, M. Doolan, C. |
Citation: | Proceedings of the 5th NSSA Australian space science conference, 2005 / Thompson, L. (ed./s), pp.CD ROM 1-CD ROM 9 |
Part of: | Proceedings of the 5th NSSA Australian space science conference |
Publisher: | RMIT University |
Publisher Place: | CD ROM |
Issue Date: | 2005 |
ISBN: | 0864593740 |
Conference Name: | NSSA Australian space science conference (5th : 14 September 2005 : RMIT Storey Hall, Melbourne, Australia) |
Editor: | Thompson, L. |
Statement of Responsibility: | Matthew Tetlow; C.J. Doolan |
Abstract: | With the recent success of scramjet powered atmospheric flights, it may soon become possible to utilise hypersonic airbreathing stages for payload delivery to orbit. A mission is therefore investigated to deliver a 400kg payload to low earth orbit using an airbreathing flight segment. Specifically, this paper investigates the use of an upper atmospheric cruise flight, using scramjet propulsion, to accelerate a second stage vehicle to the upper limits of the scramjet operating range. It is assumed a booster is used to achieve the required scramjet ignition conditions and a third stage is used to accelerate the payload from scramjet shut-down to orbital conditions. An optimisation routine is used, coupled with a trajectory simulator, to optimise a parameterised trajectory. The angle between the lift force on the body and the free-stream velocity is used as an optimisation parameter to control a lifting trajectory, which achieves the required target conditions. The trajectory simulator includes a full spheroidal, rotating Earth model, a fourth order gravitation model and an MSISE93 atmosphere model. A fourth order Runge-Kutta integration routine is used to integrate the trajectory and a gradient projection optimisation routine is used to achieve an optimal solution. From both a gross lift-off mass and a propellant consumption point of view, a part scramjet powered vehicle is seen to have a performance advantage over a totally conventional rocket powered vehicle. |
Description (link): | http://www.nssa.com.au/ocs/viewabstract.php?id=60&cf=5 |
Appears in Collections: | Aurora harvest 2 Environment Institute publications Mechanical Engineering conference papers |
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