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The paper presents a new autonomous adaptive system for the control of airplanes during landing in longitudinal plane. For the first stage of landing in longitudinal plane, the main variables to be controlled are the glide slope angle and longitudinal velocity; during the second main stage of landing in longitudinal plane, the vertical velocity error and the airplane's longitudinal velocity are controlled. The new robust control architecture has linear subsystems, for which the relative degrees are calculated; the new architecture will also consists of a dynamic compensator, a linear observer, and two reference models, their design being accomplished with respect to the calculated relative degrees. The signal estimated by the observer is useful for training a neural network – an adaptive subsystem of the architecture that provides the adaptive component of the control law. In the case of actuators having nonlinear dynamics, pseudo control hedging blocks are used to cancel the adapting difficulties of the neural networks. The new adaptive architecture is software implemented and validated by complex numerical simulations. [ABSTRACT FROM AUTHOR]

The paper focuses on two automatic systems for the attitude and position's control of the microaerial vehicles--insect type by using a nonlinear dynamic model, which describes the motion of microaerial vehicles with respect to the Earth tied frame. The attitude control is adaptive type, with the estimation of the inertia moments' matrix and of the dynamic damping coefficients' matrix in two variants: by means of the attitude vector or by using the quaternion vector. The new resulting control architectures use a vector for the control of the microaerial vehicles' attitude, a proportional-derivative linear dynamic compensator, an error vector (whose elements are the estimated deviations of the inertia moments and dynamic damping coefficients with respect to the real ones), and the Lyapunov theory. In the two variants of the adaptive control, the control law is represented by the command aerodynamic moments and the wing rotation's command vector, respectively; the control law for the microaerial vehicle position's control is deduced in the same way. The two obtained control systems are validated by complex numerical simulations. [ABSTRACT FROM AUTHOR]

This paper presents two new automatic landing systems (ALSs) for aircraft motion in longitudinal plane; the model of the landing geometry determines the flight trajectory and the aircraft calculated altitude; the flight trajectory during landing consists of two parts: the glide slope and the flare. Both designed ALSs have an adaptive system (ACS) for the aircraft output's control; for the first ALS, the output vector consists of the flying altitude and the longitudinal velocity, while, for the second ALS, the output variables are the pitch angle and the longitudinal velocity of aircraft. The second variant of ALS also contains an altitude controller providing the calculated pitch angle. The calculated altitude (for the first ALS), the calculated pitch angle (for the second ALS), and the desired flight velocity are provided to the ACS by means of a block consisting of two reference models. ACS is based on the dynamic inversion concept and contains an adaptive controller which includes a linear dynamic compensator, a state observer, a neural network, and a Pseudo Control Hedging block. The paper is focused both on the design of the two ALSs and on their complex software implementation and validation. [ABSTRACT FROM AUTHOR]