An H Design Approach for a PID Automatic Flight Control System of a Launch Vehicle

Abstract:

Article Preview

The paper presents a design methodology for the automatic flight control of a launch vehicle. In the proposed approach the controller has a PID (Proportional-Integral-Derivative) structure but its gains are determined solving an H norm minimization problem of the mapping from the atmospheric disturbances to the control amplitude and to the angle of attack of the launcher. The design methodology is illustrated by numerical examples in which both time responses and stability robustness properties of the optimal PID controller are analyzed.

Info:

Periodical:

Edited by:

Adrian Olaru

Pages:

116-123

DOI:

10.4028/www.scientific.net/AMM.859.116

Citation:

A. M. Stoica and M. R. Stefanescu, "An H Design Approach for a PID Automatic Flight Control System of a Launch Vehicle", Applied Mechanics and Materials, Vol. 859, pp. 116-123, 2017

Online since:

December 2016

Export:

Price:

$38.00

* - Corresponding Author

[1] W. De Castro Leite Filho: Control System of Brazilian Launcher, Proceedings on the 4th ESA International Conference on Spacecraft Guidance, Navigation and Control Systems, Noordwijk, The Netherlands, (1999).

[2] A.L. Greensite: Control Theory Volume II: Analysis and Design of Space Vehicle Flight Control Systems, Spartan Books, (1971).

[3] B. Wei and W. Du: Analysis and Design of Launch Vehicle Flight Control Systems, AIAA 2008-6291, AIAA Guidance, Navigation and Control Conferences, August (2008).

DOI: 10.2514/6.2008-6291

[4] M. Abbas-Turki, G. Duc and B. Clement: Robust control of a space launcher by introducing LQG/LTR ideas in the NCF robust stabilisation problem, 16th IFAC Symposium on Automatic Control in Aerospace, St-Petersburg, Russia (2004).

DOI: 10.1016/s1474-6670(17)32310-8

[5] O. Voinot, D. Alazard and A. Piquereau: A Robust Multiobjective Synthesis applied to Launcher Attitude Control, Proceedings of 15th IFAC Symposium on Automatic Control in Aerospace, Bologne, Italy (2001).

DOI: 10.1016/s1474-6670(17)40728-2

[6] O. Voinot, P. Apkarian and D. Alazard: Gain-scheduluing control of the launcher in atmospheric flight via linear parameter varying technique, AIAA Guidance, Navigation and Control Conference, Monterey, USA (2002).

DOI: 10.2514/6.2002-4853

[7] Y. Morita: An Idea of Applying -Synthesis to Launcher Attitude and Vibration Control Design, Journal of Vibration and Control, Vol. 10, No. 9 (2004).

[8] S. Mauffrey, P. Meunier, G. Pigni, A. Biard and I. Rougier: control for the ARIANE 5 plus Launcher, 52nd International Astronautics Congress, Toulouse, France (2001).

[9] M.A. Creagh and R. Lind: Control for Attitude Maneuvers of a Spinning Asymmetric Vehicle, Proceedings of Guidance, Navigation and Control Conference, Chicago, USA (2009).

DOI: 10.2514/6.2009-5641

[10] E. de Weerdt, E. van Kampen and D. van Gemert: Adaptive Nonlinear Dynamic Inversion for Spacecraft Attitude Control with Fuel Sloshing, Proceedings of Guidance, Navigation and Control Conference and Exhibit, Honolulu, Hawaii, USA (2008).

DOI: 10.2514/6.2008-7162

[11] C. Tournes, Y.B. Shtessel and E. Wells: Upper Stage Rocket Guidance and Control Using Discontinuous Reaction Control Thrusters via Sliding Mode, Proceedings of AAC Albuquerque, New Mexico (1997).

DOI: 10.1109/acc.1997.609254

[12] B. Tian, W. Fan, Q. Zong, J. Wang and F. Wang: Nonlinear Robust Control for Reusable Launch Vehicles in Reentry Phase Based on Time-Varying High Order Sliding-Mode, Journal of Franklin Institute, Vol. 350, Issue 7 (2013).

DOI: 10.1016/j.jfranklin.2013.04.022

[13] F. Amato, G. Ambrosino, E. Fillipone and R. Iervolino: Attitude Control of a Small Conventional Launcher, Proceedings of the 2002 IEEE International Conference on Control Applications, September 18-20, Glasgow, UK (2002).

DOI: 10.1109/cca.2002.1040199

[14] J. Corban, E. Johnson and A. Calise: Reusable Launch Vehicle Adaptive Guidance and Control Using Neural Networks, AIAA Guidance, Navigation and Control and Exhibit, 6-9 August, Montreal, Canada (2001).

DOI: 10.2514/6.2001-4381

[15] A. -M. Stoica and C.E. Constantinescu: An State Feedback Control Law for Launch Vehicles, Proceedings of ICMERA Conference, Bucharest, Romania, (2014).

[16] D.C. McFarlane and K. Glover: Robust Controller Design Using Normalized Coprime Factor Plant Descriptions. Springer Verlag (1990).

DOI: 10.1007/bfb0043199

[17] E. Gadea Diaz: Design of a robust controller for the VEGA TVC uing the -synthesis technique, Master thesis, Noordwijk (2011).

In order to see related information, you need to Login.