7b269834-2609-4324-a5d0-0ce656fbfdbc20220702041529562wseas:wseasmdt@crossref.orgMDT DepositInternational Journal of Applied Mathematics, Computational Science and Systems Engineering2766-982310.37394/232026https://wseas.com/journals/amcse/61820226182022410.37394/232026.2022.4https://wseas.com/journals/amcse/2022.phpTain-SouTsayDepartment of Aeronautical Engineering, National Formosa University, No.64, Wen-Hua Road, Huwei, Yunlin, TAIWANIn this literature, a linear quadratic regulation (LQR) method with controller reconfiguration and state observer is proposed for analyses and designs of a supersonic roll-yaw coupled flight control system. The flight control system of some specially shaped airframe can be decomposed into a Pitch Control System and a Roll-Yaw Coupled Control System. It can be designed separately, no need for three loops to be designed together. The design process is relatively simple, which is conducive to the design of flight control systems in large airspace. The proposed method for the considered system will give the good tracking characteristic at low frequencies and robustness at middle frequencies; simultaneously. All state variables are measurable and found controllers are all realizable either in analog or digital hardware.72202272202239435https://wseas.com/journals/amcse/2022/a10amcse-004(2022).pdf10.37394/232026.2022.4.5https://wseas.com/journals/amcse/2022/a10amcse-004(2022).pdfB. D. Anderson and J. B. Moore, Optimal Control: Linear Quadratic Methods, Courier Corporation, Chelmsford, MA, USA, 2007. M. Athans and P. L. Falb, Optimal Control: An Introduction to the Theory and its Applications, Dover Publications, New York, NY, USA, 2013. 10.2514/6.1980-1749F. W. Nesline and P. Zarchan, “Robust Instrumentation Configurations for Homing Missile Flight Control, “AIAA Guidance Control Conference, AIAA-Paper-80-1749, 1980, pp. 209-219. 10.23919/acc.1984.4788471F. W. Nesline and M. L. Nesline, “How Autopilot Requirements Constraint the Aerodynamic Design of Homing Missile, “American Control Conference, 1984, pp. 716-730. T. S. Tsay, “Linear Quadratic Regulation Method for Supersonic Missile Flight Control System Design, “Journal of Aeronautics, Astronautics and Aviation, Series A, Vol.38, No.3, pp.207-216, 2006. 10.1016/j.ast.2007.05.005T. S. Tsay, “Decoupling the flight control system of a supersonic vehicle, “Aerospace Science and Technology,Vol.11, pp.553-562, 2007. T. S. Tsay, “Coupling Effects and Decoupling for Supersonic Flight Vehicle,” WSEAS Transactions on System and Control, Vol.7, No.3, pp.108-117, 2012. Gerald Corning, “The Pitch-Yaw-Roll Coupling Problem of Guidance Missile at High Angle of Pitch (U),” NAVWEPS-77383, 1961. L. L. Crodvich and B. E. Amsler,” Pitch-Yaw-Roll Coupling, “AGARD-353, 1961. W. J. Monta,” Supersonic Aerodynamic Characteristics of An Airto-air Missile Configuration With Cruciform Wings and In-Line Tail Control, “NASA-TM-X-2666, Longley Research Center, Hompton, Virginia, 1972. W. J. Monta, “Supersonic Aerodynamic Characteristics of A Sparrow III Type Missile Model With Wing Control and Comparison With Existing Tail-control Results,” NASA-TR-1078, Langley Research Center, Hompton, Virginia, 1977.