This paper presents a new approach to perform 4D trajectory tracking for transportation aircraft. As current systems are extensions of 3D guidance with overfly time constraints at some given points and no general control framework has been developed for 4D guidance of a transport aircraft; the main goal of the proposed approach is to introduce a new method based on the inversion of the flight dynamics while avoiding numerical issues. A six degree of freedom model for a wide body transportation aircraft was developed in Matlab to provide a numerical simulation of the proposed approach, showing satisfying results.

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Sustained increase in air transportation as well as urban encroachment have generated noise critical situations around airports. Then the prediction of the noise impact resulting from new departure/arrival procedures and new traffic patterns at airports gains more importance. Until recently, this estimation has been performed on statistical grounds through the segmentation of nominal aircraft trajectories. This approach is in general not representative of the temporal dimension of the noise impacts over the airport surrounding population. To go beyond this limitation, a dynamical approach to noise impact estimation taking explicitly into consideration the operated 3D+T aircraft trajectory, is proposed in this communication. This is achieved by taking profit of the differential flatness property of the flight guidance dynamics of transportation aircraft, which allows through inversion to compute the corresponding thrust and aerodynamic conditions, which are also responsible for aircraft noise generation. In numerical grounds, this is achieved by building a neural network device which produces ground noise levels histories along the trajectories flown by aircraft. The proposed approach is partially validated using for comparison noise levels estimated from the Integrated Noise Model (INM). The proposed tool appears to be useful to analyze the noise impact of complex traffic scenarios including traffic dispersion phenomena.

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This study is dedicated to the problem of non linear attitude control for a rigid large angle maneuver satellite. The non linear control method is based upon the linearization of the input-output of the system, also called feedback linearization, via state feedback.The output function is chosen amongst the attitude quaternion parameters.