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Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

Published online by Cambridge University Press:  03 February 2016

C. Tao ,
Y. Daren  and
B. Wen
C. Tao
Affiliation:
Harbin Institute of Technology, Heilongjiang, China
Y. Daren
Affiliation:
Harbin Institute of Technology, Heilongjiang, China
B. Wen
Affiliation:
Harbin Institute of Technology, Heilongjiang, China
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Abstract

Dual-mode scramjet is one of the candidates for hypersonic flight propulsion system which will be used in wide range of flight Mach numbers from 4 to 12 or higher, wherein dual-mode scramjet should be well designed to be suitable for subsonic/supersonic combustion operation according to the flight conditions. Therefore this system is required to operate in a finite number of operational modes that necessitate robust, stable, and smooth transitions between them by which selective operability of supersonic/subsonic combustion modes and efficient combustor operation in these modes may be realised. A key issue in making mode transition efficient and stable is mode transition control. The major problem in mode transition control is the handling of the various flow and combustion coupling effects of dual-mode scramjet whose physical states are spatially coupled and whose governing equations are partial differential equations. Involving these distributed parameter issues, our basic idea is using the shape control theory to study the control problems of mode transition for dual-mode scramjet with the aim of achieving the desirable design properties and increasing control reliabilities. This specific approach is motivated by the promise of novel techniques in control theory developed in recent years. Concrete control arithmetic of this approach, such as shape control model, sensitivity analysis and gradient-based optimisation procedure, are given in this paper. Simulation results for an axisymmetric, wall-injection dual-mode scramjet show the feasibility and validity of the method.

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1135 , September 2008 , pp. 557 - 565
Copyright
Copyright © Royal Aeronautical Society 2008 

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