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Rocket nozzle flow control using proper orthogonal decomposition

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3 Author(s)
Lucia, D.J. ; Air Force Inst. of Technol., Wright-Patterson AFB, OH, USA ; Pacter, M. ; Beran, P.S.

This paper investigates the use of proper orthogonal decomposition-based reduced order computational fluid dynamics models for model-based controller design. An open-loop optimal control problem is posed and solved concerning the regulation of a rocket engine thrust profile. The control synthesis uses a numerical flow field solver as the plant model. Controllers are synthesized using a reduced order model of the flow field generated via proper orthogonal decomposition. A quasi one-dimensional supersonic convergent-divergent nozzle with varying back pressure is used as a model problem. Treating the nozzle flow as one-dimensional, the reduced order model was used to synthesize a controller that controls thrust along an ascent trajectory by varying nozzle throat area and fuel mass flow rate. The effects of reduced order model accuracy on controller performance are quantified

Published in:

Decision and Control, 2001. Proceedings of the 40th IEEE Conference on  (Volume:5 )

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