In this paper, a research investigation is presented in the flight guidance and control design for a loss-of-thrust aircraft. A zero effort miss based guidance law is applied to deal with the impaired aircraft dynamics. The zero effort miss vector is derived to express the expected miss distance between the aircraft and the target on the trajectory at a future time. As a result, the traditional trajectory tracking problem is treated as an aircraft-target intercept problem. In addition, both nominal and impaired nonlinear aircraft dynamics can be formulated as a generic affinity-in-control framework in which we propose a statedependent Riccati equation (SDRE) control method. The SDRE based controller with integral servomechanism is designed to track guidance law commands. A modified SDRE flight control design is formulated by variable substitutions and state augmentation to enforce SDRE design conditions. The application of guidance law and design under SDRE for impaired aircraft is verified through simulations on a UAV aircraft case study. The proposed system is also compared with a well known nonlinear control method in the example. Promising results are obtained for the proposed guidance and control system. Nomenclature F Aerodynamic forces (N) M Aerodynamic moments (N m) m Mass (kg) H Angular momentum vector V, ω Translational and rotational velocities (m/s, deg/s) S Wing planform area (m 2 ) bWing span (m) cChord length (m) cMean aerodynamic chord (m) qDynamic pressure g Acceleration due to gravity (m/s 2 ) δ th Throttle setting (in percentage) δ e Elevator deflection (deg) U, W Axial and normal velocity (m/s) θPitch angle (deg)Angle of attack (deg) γFlight path angle (deg) d TOffset of the thrust line from the aircraft CG in z-direction of the body frame(m) T max Max. thrust force (N) C X Axial force coefficients
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