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Flight control using pin-protuberances for blunted cones

Published online by Cambridge University Press:  03 February 2016

R. Samar ,
S. Zahir  and
M. A. Khan
R. Samar
Affiliation:
raza@mail.comsats.net.pk, National Engineering and Scientific Commission, Islamabad, Pakistan
S. Zahir
Affiliation:
cfdpak@apollo.net.pk
M. A. Khan
Affiliation:
cfdpak@apollo.net.pk
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Abstract

This paper presents the concept of using cylindrical pins as short protuberances for trajectory control of a blunted cone in the supersonic and hypersonic regimes. Supersonic and hypersonic flow interactions for cylindrical protuberances, installed on a blunt cone are studied for their aerodynamic effects. The utility of these protuberances for aerodynamic control and trajectory shaping of a re-entry cone are explored. Static aerodynamic coefficients in the Mach range of 2–9·7 at various incidences are computed. The pressure distribution along the vehicle longitudinal axis in the presence of the pin-protuberance is studied using CFD analysis. With the altered pressure distribution, a net increase in the aerodynamic force is obtained which can be actively utilised for flight control and maneuvering of the vehicle during re-entry. After quantifying the aerodynamic effects of the protuberance, it is modelled and used as an effective actuation mechanism for flight feedback control. It is shown that this can work as an effective control device for Mach numbers less than five. An actuator design for insertion/retraction of the protuberance is presented and modelled, and a robust controller is synthesised which can in real time govern the position of the protuberance to control the flight attitude angle to achieve a desired trajectory. The controller takes in measurements of the vehicle’s pitch angle and actuates the pin height continuously to control the pitch angle to a desired value. The control performance is demonstrated on a high fidelity six degrees-of-freedom (6-DOF) nonlinear flight simulation.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1154 , April 2010 , pp. 245 - 257
Copyright
Copyright © Royal Aeronautical Society 2010 

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References

1. Blakelock, J.H., Automatic Control of Aircraft and Missile, John Wiley & Sons, 2nd ed, 1991.Google Scholar
2. Cassel, L.A., Durando, N.A., Bullard, C.W. and Kelso, J.M., Jet interaction control effectiveness for subsonic and supersonic flight. Technical Report RD-TR-69-21, McDonnell Douglas Astronautics Company, 1969.Google Scholar
3. Chamberlain, R., McClure, D. and Dang, A., CFD analysis of lateral jet interaction phenomena for the THAAD interceptor. In Proceedings of the 38th AIAA Aerospace Sciences Meeting & Exhibit, Reno, NV, USA, January 2000.Google Scholar
4. Aerodynamics Division. A User’s Guide to LOOK. Aerodynamics and Structural Analysis Centre, Islamabad, Pakistan, 1997.Google Scholar
5. Aerodynamics Division. A User’s Guide to PAK-3D. Aerodynamics and Structural Analysis Centre, Islamabad, Pakistan, 1998.Google Scholar
6. Kandebo, S.W., New powerplant key to missile demonstrator, Aviation Week and Space Technology, September 2002, 157, (10), pp 56–59.Google Scholar
7. Marx, W.J., Wessling III, F.C., Peters, B.R., Thies, A., Strickland, B.R. and Lianos, D., Miniature smart munitions/guided projectiles for the objective force. In 23rd Army Science Conference, December 2002.Google Scholar
8. Massey, K.C., McMichael, J., Warnock, T. and Hay, F., Development of mechanical guidance actuators for a supersonic projectile. Aeronaut J, April 2008, 112, (1130), pp 181–195.Google Scholar
9. McFarlane, D. and Glover, K., A loop shaping design procedure using H∞ synthesis, IEEE Transactions on Automatic Control, 1992, 37, (6), pp 759–769.Google Scholar
10. McRuer, D., Ashkenas, I. and Graham, D., Aircraft Dynamics and Automatic Control, Princeton Univeristy Press, Princeton, New Jersey, USA, 1973.Google Scholar
11. Postlethwaite, I., Prempain, E., Turkoglu, E., Turner, M.C., Ellis, K. and Gubbells, A.W., Design and flight testing of various H∞ controllers for the Bell 205 helicopter, Control Engineering Practice, 2005, 13, pp 383–398.Google Scholar
12. Regan, F.J. and Anandakrishnan, S.M., Dynamics of Atmospheric ReEntry. AIAA Education Series. American Institute of Aeronautics and Astronautics, 1993, Washington DC, USA.Google Scholar
13. Samar, R., Murad, G., Postlethwaite, I. and Gu, D.-W., A discrete time H∞ observer-based controller and its application to a glass tube production process, European J Control, 1996, 2, pp 112–125.Google Scholar
14. Skogestad, S. and Postlethwaite, I., Multivariable Feedback Control Analysis and Design, John Wiley & Sons, West Sussex, England, UK, 2nd ed, 2005.Google Scholar
15. Smerlas, A., Walker, D.J., Postlethwaite, I., Strange, M.E., Howitt, J. and Gubbells, A.W., Evaluating H ∞ controllers on the NRC Bell 205 fly-by-wire helicopter. Control Engineering Practice, 2001, 9, (1), pp 1–10.Google Scholar
16. Stevens, B.L. and Lewis, F.L., Aircraft Control and Simulation, John Wiley & Sons, 1992.Google Scholar
17. Tsai, M.C., Geddes, E.J.M. and Postlethwaite, I., Pole-zero cancellations and closed-loop properties of an H ∞ mixed sensitivity design problem, Automatica, 1992, 28, (3), pp 519–530.Google Scholar
18. Warnash, A. and Killen, A., Low cost, high G, micro electromechanical (MEMS) inertial measurement unit (IMU) program. In 23rd Army Science Conference, December 2002.Google Scholar
19. Zahir, S. and Asif, M., Computational aerodynamic interaction of a side plate and forward facing spike on blunted configurations in hypersonic flow. In Proceedings of the East West High Speed Flow Field Conference, Beijing, China, October 2005.Google Scholar
20. Zahir, S. and Ye, Z., Aerodynamic analysis of pitched plate/jet – interactions with hypersonic flow. Czech Aerospace Proceedings, 2, 2007.Google Scholar
21. Zahir, S. and Ye, Z., Hypersonic flow interaction of pitched plates on blunted cone at incidence. Int J Mathematical Models and Methods in Applied Sci, 2007, 1, (3), pp 133–136.Google Scholar
22. Zahir, S. and Ye, Z., Hypersonic flow interaction of pitched short lateral plates on blunted cone configuration. In Proceedings of the 2nd European Conference for Aerospace Sciences, Brussels, Belgium, July 2007.Google Scholar
23. Zubkov, A.I., Kuznetsov, O.M. and Panov, Y.A., Vortices downstream of a wedge in a supersonic flow on a surface with a turbulent boundary layer, J Fluid Dynamics, 1996, 31, (1).Google Scholar