No abstract

Abstract-Adaptive control algorithms are of interest in flight control systems design not only for their capability to improve performance and reliability but also for handling aerodynamic parameter uncertainties, external disturbances and modeling inaccuracies. In this paper, a direct adaptive sliding mode control is developed for the quadrotor attitude stabilization and altitude trajectory tracking. First, developed controller is applied without considering disturbances and parameter uncertainties. After, a centered white gaussian noise with some parameter uncertainties are added to the considered output vector, mass and inertia matrix, respectively. The synthesis of the adaptation laws is based on the positivity and Lyapunov design principle. Numerical simulations are performed showing the robustness of the proposed control technique.

With the growth of civil aviation traffic, enhanced accuracy performances are required from guidance systems to maintain efficiency and safety in flight operations. This communication proposes a new representation of aircraft flight dynamics at approach for landing and a space-based nonlinear dynamic inversion control technique for the guidance of transportation aircraft. The main novelty is that the adopted independent variable is distance to land which allows the development of a new guidance approach with a perspective for improved performance. Nomenclaturex Longitudinal displacement, m z Altitude, m V air Airspeed, m/s V G Ground speed, m/s γ air Flight path angle w.r.t airspeed, rad θ Pitch angle, rad α Angle of attack, rad L Lift force, N D Drag force, N T Thrust force, N C Z Lift force coefficient C X Drag force coefficient m Mass, Kg q Pitch rate, rad/s M Pitch moment, N.m I y Pitch inertia moment, Kg.m 2 ρ Air density, Kg/m 3 S Wing surface area, m 2 g Gravity acceleration, m/s 2 τ Engine time constant , s T C Throttle setting , rad δ e Elevator deflection , rad w x Longitudinal wind component , m/s w z Vertical wind component , m/s Subscript k Variable number

No abstract

No abstract