In this paper, a fuzzy logic guidance algorithm is presented for the ascending phase of satellite launch vehicles in the presence of wind effects. In this algorithm, the midcourse constraints including maximum allowable angle of attack at the maximum dynamic pressure and the product of the dynamic pressure and angle of attack, as well as constraints on the final altitude and flight-path angle are considered. The algorithm uses a Mamdani-type fuzzy controller with centroid defuzzification.Maximizing and minimizing set methods to reduce wind effect, while satisfying the midcourse and final constraints. Simulation results show that the presented algorithm improves the performance of the satellite launch vehicle, satisfying the constraints within the maximum allowable estimation error on wind speed.


[1] Malyshev V. V. (Editor), Aerospace Vehicle Control: Modern Theory and Applications, Brazil, 1996.
[2]The Advisory Group for Aerospace Research and Development of NATO, Wind Effects on Launch Vehicles, Technivision Services Slough, England, 1970.
[3] Mohanlal, P. P. and Kaimal, M. R. and Dasgupta, S., "Exact Fuzzy Modeling and Optimal Control of a Launch Vehicle in the Atmospheric Phase," 7th International Conference on Control, Automation, Robotics and Vision, Singapore, 2002.
[4] Pamadi, B. N., "Simple Guidance Method for Single Stage to Low Earth Orbit,"Journal of Guidance, Control and Dynamics, Vol. 18, No. 6, 1995, pp. 1420-1426.
[5] Queen, E. M. and Warner, M. S., and Moerder, D. D., "Monte Carlo Simulation of Launchsite Winds at Kennedy Space Center,"Journal of Spacecraft and Rocket, Vol. 31, No. 2, 1994, pp. 249-258.
[6] Rohollahi, S.M.S., Novinzade, A., Amintorabi, A., "Optimal Design of Preset Guidance System Using Neuro-Fuzzy,"1st Symposium on Space Launch System, K.N.Toosi University, 2011 (In Persian).
[7] Sohrab, M., Zardashti, R., Jalali Naini, S.H., "Fuzzy Guidance Algorithm Design for Launch Vehicles in the Presence of Wind Disturbance,"11th Conference of Iranian Aerospace Society, Sattari University, 2011 (In Persian).
[8] Min, C. and Lee, D. and Cho, K. and Jo, S. and Yang, J. and Lee, W., "Control of Approach and Landing Phase for Reentry Vehicle Using Fuzzy Logic,"Aerospace science and Technology, Vol. 15, 2011, pp. 269-282.
[9] Wei-jun, H. and Jun, Z., "A New Method of Terminal Energy Management for Suborbital Launch Vehicle,"IEEE International Conference onIntelligent Computing and Intelligent Systems,Vol. 2, 2009,pp. 710-714.
[10]Shafieenejad, I. and Novinzadeh, A.B., "Close-Loop Guidance Laws for Law-Thrust Spacecraft,"Journal of Modelling, Identification and Control, Vol. 21, No.1, 2014,pp. 17-28.
[11]Burchett, B.T., "Fuzzy Logic Trajectory Design and Guidance for Terminal Area Energy Management,"Journal of Spacecraft and Rockets, Vol. 41, No. 3, 2004, pp. 444-450.
[12]Tewari, A., Atmosphere & Spacecraft Dynamic Modeling and Simulation with Matlab and Simulink, Birkhauser Press, India, 2007.
[13] Blakelock, J. H., Automatic Control of Aircraft and Missiles, 2nd Edition, John Wiley & Sons, Inc., 1991.
[14]Zipfel, P. H., Modeling and Simulation of Aerospace Vehicle Dynamics, 2nd Edition, AIAA, 2007.
[15] Wang, L. X., A Course in Fuzzy Systems and Control, Prentice-Hall International, 1997.
[16]Kisabo, A. B. and Osheku, C. A., Moshood Adesoye Lanre, A. and Funmilayo Adebimpe, A., "Fuzzy Logic Control for an Expendable Launch Vehicle Autopilot," European Journal of Scientific Research, Vol. 59, No. 2, 2011, pp. 226-240.
[17]Savage, M., Launch Vehicle Handbook, National Aeronautics and Space Administration, USA, 1982.
[18]Yaroshevski, V.A., Space Vehicle Atmospheric Entry, Nauka-Moskow, 1998.
[19]Karimi Mazraeshahi, H., Hashemi Doolabi, M., Ballistic Missile and Launch Vehicle Design, Jahad. Press, Iran, 2005 (In Persian).
[20]Sohrab, M., Zardashti, R., Jalali Naini, S.H., "Launch Vehicle Pitch Programming Design for Improving Performane in the Effect of Wind,"1st Symposium on Space Launch System, K.N.Toosi University, 2011 (In Persian)