1,721,000 research outputs found
Survey of Certifiable Air Data Systems for Urban Air Mobility
Full text linkIn the near future, vertical take off and landing aircraft of the urban air mobility sector will be integrated into the civil airspace and they will be characterised by several levels of autonomous flying capabilities. Many countries worldwide are funding several researches to identify and develop enabling technologies to make urban air mobility as safe as modern aviation. One of the most critical aspect of those aeroplanes rely on the reduced fuselage dimensions and available space on board to welcome all those safety critical systems commonly used on commercial aviation. The air data system is one of the safety critical system that is equipped with several probes and vanes, protruding externally from the aircraft fuselage, and some of its functionalities are adequately redundant for general aviation and large aeroplanes. Even though an airworthiness standard applicable to urban air mobility is not ready yet, worldwide there are several efforts that will lead to type certification standards in next years. This work presents a brief survey of certified technologies available for sensing solutions feeding air data systems and solutions based on synthetic sensors certifiable in a couple of years. The survey relies on certified and certifiable innovative data sensing units for realistic urban air mobility applications. To this aim, a safety assessment analysis is presented in order to support the validity of the certifiable air data sensing solutions presented in this paper
MODULO DI DECOLLO E ATTERRAGGIO VERTICALE DI UN AEROMOBILE AD ALA FISSA, E RELATIVI METODO E SISTEMA
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ThrustPod: a novel solution for vertical take-off and landing systems
Full text linkThe work introduces a patented solution, named ThrustPod, to adapt the state-of-the-art fixed-wing aircraft for vertical take-off and landing operations. The proposed system is conceived to overcome the need of tilting surfaces or rotors and to overcome the aerodynamic low performance of multicopters. The ThrustPod is applicable to very light and general aviation aircraft and next generation air vehicles that aim to operate on urban and regional routes. The proposed solution is based on retractable thrusters to provide the required vertical thrust for the take-off and landing phases. The more suitable thrusters can be adopted, e.g. ducted fans or propellers. Another characteristic is the modularity as the ThrustPod can be scaled on different vehicle categories. In fact, the proposed solution can be used on different fixed-wing aircraft to provide vertical and take-off capabilities or to design novel airframes. The work proposes an integrated preliminary design process to optimise both the aircraft and the ThrustPod configuration to define fuselage length, thruster’s arrangement, power budget, energy management and performance evaluation of a potential aircraft for urban air mobility applications. The aim of the present work is to present a preliminary design application to evaluate advantages and drawback with respect to the most promising urban air mobility vehicles
Metodo e sistema per stimare angoli aerodinamici di un corpo volante
No full textLa presente invenzione si riferisce a un metodo per stimare gli angoli aerodinamici di incidenza e di derapata di un corpo volante, basato sulla soluzione numerica o analitica di un’equazione. Tale metodo è applicabile a bordo del corpo, e.g. un aeromobile, tramite sensori e dispositivi elettronici di bordo per eseguire calcoli in tempo reale, oppure a terra. In quest’ultimo caso è possibile impiegare il metodo in una fase di diagnostica di volo sulla base di dati memorizzati durante un volo, oppure il metodo è integrato in un simulatore di volo per l’addestramento a terra, sulla base di dati e.g. del vento generati artificialmente e non misurati
SISTEMA E PROCEDIMENTO DI MISURA E VALUTAZIONE DI DATI ARIA E INERZIALI
No full textSono descritti un sistema ed un procedimento di misura e valutazione di dati aria e inerziali di un velivolo (1) per stimare in modo indiretto almeno un angolo di incidenza ed un angolo di derapata rispetto ad una direzione di vento relativo di tale velivolo (1)
Range Estimation Of A Novel Concept Electric Aircraft Based On Modified Breguet Equation
Full text linkThe electric vertical-take off and landing aircraft are able to perform vertical flights, equipped with an electric propulsion and energy storage system. This kind of aircraft has gained more importance during the last decades, in particular for urban aerial mobility. Its design is function of several project specifications, among them the range to cover a cruise flight mission profile. The present work is intended to show a modified Breguet equation for the range estimation applied to a novel electric aircraft concept.
The advantage of this equation is to avoid the knowledge of parameters which are difficult to be found a-priori in a preliminary design phase. It is worth noticing that the modified Breguet estimated range needs further corrections to obtain a correct effective cruise range. For this reason, the estimated range is compared with the effective cruise range obtained with an energy balance equation. Results show that the estimated and theoretical range values are very close and comparable, hence the modified Breguet
equation for electric aircraft is correct. In order to validate the present results, a comparison with several urban air mobility aircraft is performed
Neural Network Techniques to Solve a Model-Free Scheme for Flow Angle Estimation
No full textIn the area of synthetic and smart sensors for flow angle estimation for UAS applications, model-based, data-driven and model-free approaches represent the state-of-the-art techniques to estimate the angle-of-attack and angle-of-sideslip. Thanks to sensor fusion techniques, a synthetic sensor is able to provide estimation of flow angles without any dedicated physical sensors. A model-free approach, based on a set of nonlinear equations, demonstrates good performances when used with flight simulated data. As shown in this work, an iterative solver could not be adequate dealing with real flight data affected by common instrument uncertainties. In order to cope with real flight data, two deterministic solvers can be adopted that are based on neural techniques: pre-trained multilayer perceptron and generalised radial basis function neural networks. The neural networks considered in this work are trained with batch and sequential algorithms. All solvers are tested with noise-free and noisy signals simulating real flight instrument noise. The aim of the present work, in fact, is to provide a preliminary benchmark between the aforementioned solvers when used to solve the proposed nonlinear scheme for flow angle estimation dealing with instrument noise
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