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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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References

1. Denis, S.R. and Kau, H.P., Experimental study on transition between ramjet and scramjet modes in a dual-mode combustor, AIAA 2003-7048, December 2003.Google Scholar
2. Eijiro, K. and Tohru, M., Evaluating the aerodynamic performance of scramjet engines by pressure measurement, AIAA 2003-7053, December 2003.Google Scholar
3. Edward, T.C., Scramjet engines: The first forty years, J Propulsion and Power, 2001, 17, (6), pp 1138–1148.Google Scholar
4. Ali, M., Sadrul, I. and Ahmed, S., Mixing and flame holding with air inlet configuration in scramjet combustor, International Communications in Heat and Mass Transfer, 2004, 31, (8), pp 1187–1198.Google Scholar
5. Gruber, M.R., Donbar, J.M. and Carter, C.D., Mixing and combustion studies using cavity-based flameholders in a supersonic flow, J Propulsion and Power, 2004, 20, (5), pp 769–778.Google Scholar
6. Daren, Y., Tao, C. and Wen, B., An idea of distributed parameter control for scramjet engines, Aeronaut J, in press.Google Scholar
7. Harefors, M., Application of control structure design methods to a jet engine, J Guidance, Control and Dynamics, 2001, 24, (3), pp 510–518.Google Scholar
8. Hashem, A.A. and Nada, T.R., Design of turbofan engine controller based on non-linear analysis, J Engineering and Applied Science, 2002, 48, (1), pp 137–153.Google Scholar
9. Wang, F., Fan, S.Q. and Wu, D., Study of MAPS methods for turbofan engine performance seeking control, J Aerospace Power, 2005, 20, (3), pp 503–507.Google Scholar
10. Hoo, K.A. and Zheng, D., Low-order control-relevant models for a class of distributed parameter systems, Chemical Engineering Science, 2001, 56, (23), pp 6683–6710.Google Scholar
11. Tomioka, S., Kobayashi, K. and Murakami, A., Distributed fuel injection for performance improvement of staged supersonic combustor, J Propulsion and Power, 2005, 21, (4), pp 760–763.Google Scholar
12. Gallimore, S.D., Jacobsen, L.S. and O’Brien, W.F., Operational sensitivities of an integrated scramjet ignition/fuel-injection system, J Propulsion and Power, 2003, 19, (6), pp 183–189.Google Scholar
13. Godasi, S., Karakas, A. and Palazoglu, A., Control of nonlinear distributed parameter processes using symmetry groups and invariance conditions, Computers and Chemical Engineering, 2002, 26, (7), pp 1023–1036.Google Scholar
14. Hironoyi, A.F., Disrtibuted parameter approach to control large space structures, Proceeding of the 35th Conference on Decision and Control, Kobe, Japan, 1995.Google Scholar
15. Karlsson, N., Optimal nonlinear distributed control of spatially-invariant systems, Proceeding of the 40th IEEE conference on decision and control, Orlando, Florida, USA, 2001.Google Scholar
16. Yu, D.R., Cui, T. and Bao, W., Distributed parameter control method for hypersonic jets, J Aerospace Power, 2004, 19, (2), pp 259–264.Google Scholar
17. Haftka, R.T. and Adelman, H.M., An analytical investigation of shape control of large space structures by applied temperatures, AIAA J, 1985, 23, (45), pp 1–7.Google Scholar
18. Balakrishnan, A.V., Shape control of plates with piezo actuators and collocated position/rate sensors, Applied Mathematics and Computation, 1994, 6, (3), pp 213–234.Google Scholar
19. Tan, Z., Optimal linear quadratic gaussian digital control of an orbiting tethered antenna/reflector System, J Guidance, Control and Dynamics, 1994, 17, (2), pp 234–241.Google Scholar
20. Agrawal, B.N. and Treanor, K.E., Shape control of a beam using piezoelectric actuators, Smart Materials and Structures, 1999, 8, (6), pp 729–739.Google Scholar
21. Chee, C., Tong, L.Y. and Steven, G.P., Static shape control of composite plates using a slope-displacement-based algorithm, AIAA J, 2002, 40, (8), pp 1611–1618.Google Scholar
22. Irschik, H. and Pichler, U., Dynamic shape control of solids and structures by thermal expansion strains, J Thermal Stresses, 2001, 24, (3), pp 565–78.Google Scholar
23. Murozono, M. and Sumi, S., Active vibration control of a flexible cantilever beam by applying thermal bending moment, J Intelligent Material and System Structure, 1994, 5, (4), pp 21–9.Google Scholar
24. Hsu, C.Y., Lin, C.C. and Gaul, L., Shape control of composite plates by bonded actuators with high performance configuration, J Reinforced Plastics Composition, 1997, 16, (18), pp 1692–710.Google Scholar
25. Josyula, E., Pinney, M. and Blake, W.B., Applications of a counter flow drag reduction technique in high-speed systems, J Spacecraft and Rockets, 2002, 39, (4), pp 605–614.Google Scholar
26. Kim, S.J. and Song, K.Y., Active control of sound fields from plates in flow by piezoelectric sensor/actuator, AIAA J, 1999, 37, (10), pp 1180–1186.Google Scholar
27. Eleshaky, M.E. and Baysal, O., Airfoil shape optimization using sensitivity analysis on viscous flow equations, J Fluids Engineering, 1993, 115, (1), pp 75–84.Google Scholar
28. Ashrafizadeh, A., Raithby, G.D. and Stubley, G.D., Direct design of airfoil shape with a prescribed surface pressure, Numerical Heat Transfer, 2004, 46, (6), pp 505–527.Google Scholar
29. Cochran, L.S. and Howell, J.F., Wind tunnel studies for the aerodynamic shape for Sydney Australia, J Wind Engineering and Industrial Aerodynamics, 1990, 36, (2), pp 801–810.Google Scholar
30. Heiser, W. and Pratt, D., Hypersonic airbreathing propulsion, AIAA J, Washington, DC, USA, 1994, pp 342–362.Google Scholar
31. Timothy, F.O., Ryan, P.S. and Mark, J.L., Quasi-one-dimensional high-speed engine model with finite-rate chemistry, J Propulsion and Power, 2001, 17, (6), pp 1366–1374.Google Scholar