NomenclatureD δ e = aerodynamic drag derivative with respect to elevator deflection angle L p , N p = roll and yaw moment derivatives with respect to roll rate L r , N r = roll and yaw moment derivatives with respect to yaw rate L r , L β = aerodynamic roll moment derivative with respect to yaw rate and sideslip angle L α , D α , T α = aerodynamic lift, drag, and thrust derivatives with respect to angle of attack L _ α = aerodynamic lift derivative with respect to rate of change angle of attack L β , N β = roll and yaw moment derivatives with respect to sideslip angle L δ e , M δ e = aerodynamic roll and pitch moment derivatives with respect to elevator deflection angle L 0 , D 0 = benchmark aerodynamic lift and drag derivatives with respect to angle of attack M V , M q = aerodynamic pitch moment derivative with respect to aircraft flight speed V and pitch rate M α , M _ α = aerodynamic pitch moment derivative with respect to α and _ α m, g = mass of the aircraft, gravity acceleration N δa , L δa = yaw and roll moment derivatives with respect to aileron deflection angle N δr , L δr = yaw and roll moment derivatives with respect to rudder deflection angle p, q, r = body axis components of the angular velocity p W , q W , r W = local air mass angular velocities resulting from the wind gradients T, δ T , T δ T = engine thrust, throttle, and aerodynamic thrust derivative with respect to the throttle T V , D V , L V = thrust, aerodynamic drag, and aerodynamic lift derivatives with respect to airspeed V u; v; wu A ; v A ; w A = body axis components of, aircraft flight velocity, and aircraft track velocity V W ; u W , v W , w W = local turbulence velocity and body axis components of V W V 0 , α 0 , γ 0 = benchmark flight velocity, angle of attack, and flight-path angle Y β , Y p , Y r = side force derivatives with respect to sideslip angle, roll rate, yaw rate Y δa , Y δr = side force derivatives with respect to aileron deflection angle and rudder deflection angle α, β = angle of attack and sideslip angle α K , β K = angle of attack and sideslip angle due to V K α W , β W = angle of attack and sideslip angle due to V W θ, ϕ, ψ = Euler pitch, roll, and yaw angle σ = angle between thrust and body x b axis

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An adaptive disturbance rejection algorithm is proposed for carrier landing system in the final-approach. The carrier-based aircraft dynamics and the linearized longitudinal model under turbulence conditions in the final-approach are analyzed. A stable adaptive control scheme is developed based on LDU decomposition of the high-frequency gain matrix, which ensures closed-loop stability and asymptotic output tracking. Finally, simulation studies of a linearized longitudinal-directional dynamics model are conducted to demonstrate the performance of the adaptive scheme.

A robust fault detection scheme is developed for networked control systems (NCSs) with limited quality of services (QoS), such as network-induced time delay, data dropout, and error sequence. An augmented Markov jump systems (MJSs) model is constructed, based on which a robust fault detection filter is designed. Such a design solved by using Ricatti inequality can guarantee that the error dynamic system is stochastic stable and the residual is sensitive to the fault. A numerical example and an aircraft application simulation study are provided to verify the effectiveness of the proposed method.