bluuebunny/crossref_metadata_2025 huggingface dataset:
A CFD study on the strut interference on a regional aircraft wind-tunnel model
Authors: Russo S , Müller J , Alderman J , Paletta N , Adden S , Ruiz-Calavera L P
Published: January 2021

The aim of this paper is to investigate the aerodynamic interference effects of typical devices supporting aircraft models during wind tunnel tests by means of CFD tools. This work proposes the use of steady RANS simulations of the flow field in order to predict the interference produced by two different models of struts: (1) one that is made up of two parts and is solidal with the wind-tunnel model for variation of the angles of incidence (α) and of the angles of sideslip (β) and (b) the second that is made up of one part and is fixed for α variations and is solidal with the model for β variations. Low and high Reynolds flow conditions are considered and a typical cruise configuration of a scaled model of regional aircraft is addressed in both power-off and power-on conditions. The strut effect is investigated for several angles of incidence and sideslip. From the numerical point of view, the flow field and forces disturbance caused by the struts are derived by comparing simulations with and without the support. The interference is analysed in terms of global forces and moments coefficients and local quantities, such as pressure coefficients distributions. The main result regarding the comparison between the two models of strut is that the corrections to be applied to experimental data and the effect of both ventral struts on the global aerodynamic forces and moments are small.
Non-intrusive determination of the unsteady surface pressure and aerodynamic loads on a pitching airfoil
Authors: Mertens C , Sciacchitano A , van Oudheusden B W , Sodja J
Published: January 2021

The unsteady surface pressure distribution and aerodynamic loads on a pitching airfoil are determined non-intrusively using PIV measurements. An experimental test case is considered where the flow around the airfoil is mostly attached while the unsteady effects on the aerodynamic loads are significant. The surface pressure is calculated from the flow velocity measurements in the vicinity of the airfoil surface, that are obtained with a robotic PIV system, by using relations from unsteady potential flow and thin airfoil theory. The proposed approach is a robust and computationally efficient approach to obtain non-intrusive measurements of the unsteady surface pressure distribution and the aerodynamic loads, that are in good agreement with reference data from installed pressure transducer sensors.
Measurements of deformation, schlieren and forces on an OAT15A airfoil at pre-buffet and buffet conditions
Authors: Accorinti Alessandro , Baur Tim , Scharnowski Sven , Knebusch Johannes , Dillinger Johannes , Govers Yves , Nitzsche Jens , Kahler Christian J.
Published: January 2021

Self-sustained shock wave oscillations on airfoils, commonly defined as shock buffet, can occur under certain combinations of transonic Mach number and angle of attack due to the interaction between the shock and the separated boundary layer. To help understanding buffet physics, a rigid supercritical wing model (OAT15A) was investigated in pre-buffet and buffet conditions using a combined application of BOS (Background Oriented Schlieren), deformation and force measurements. From the observation via BOS of the change of the shock location and the extent of the boundary layer separation with the AoA (angle of attack), the transition from stable shock to buffet was detected. A comparison with other research groups at supposedly similar aerodynamic conditions highlighted a great disparity among them in terms of buffet onset, amplitudes of buffet oscillations, and flow development (motion of the mean shock location with the AoA) after the onset. The average and rms (root mean square) of the surface displacement were computed together with the effective geometric AoA, taking into account the static torsional deformation of the model and its support. Moreover, the spectra of the balance and deformation data showed the same buffet peak as in the BOS spectrum, indicating a coupling between structure and flow, which increased with the AoA.
Design of a tilting mechanism for a VTOL flying wing UAV
Authors: Mitridis D , Bliamis C , Kaparos P , Yakinthos K
Published: January 2021

In this paper, the detailed design of a mechanism for the transition from vertical to horizontal flight of a Vertical Take-off and Landing (VTOL) fixed wing Unmanned Aerial Vehicle (UAV) is presented. The UAV, which is being developed in the framework of the MPU research project, under the designation MPU RX-4, is a lightweight, all electric driven UAV with a flying wing layout. The MPU RX-4 is capable of performing both conventional flight, like a regular fixed wing aerial vehicle, as well as vertical hovering, like a multicopter, adapting on different operational demands. To achieve that, the development of a robust transition procedure from one flight phase to the other is required. This procedure is based on mechanisms capable of altering the flying characteristics of the UAV. More specifically, these mechanisms should be designed in order to change the orientation of the thrust vectors from horizontal to vertical and vice versa. MPU RX-4 uses a configuration of three electric motors (two mounted on the canards, and one in the main body) in order to perform both flight phases. For the transition from the hovering phase to the level flight, the two frontal motors have to be tilted from the vertical position to the horizontal, and the rear motor to be nested in its proprietary position, using four external hatches. Two separate mechanisms are designed, one for the canards’ tilting movement and another one for the extension and retraction of the rear motor hatches. Finite Element Analysis is carried out for the structural sizing of the mechanism (i.e. internal loads, linkages cross-section, joints sizing). The aerodynamic loads, acting on the mechanisms, are derived from Computational Fluid Dynamics analysis performed for the various flight phases (hovering, level flight and transition) of the UAV. Finally, the designed mechanisms are presented as integrated parts of the prototype UAV.
Enhancing preliminary aircraft design through operational considerations: a data-driven approach
Authors: Longueville Sébastien de , Jézégou Joel , Bénard Emmanuel , Gourinat Yves
Published: January 2021

Nowadays, digitalisation of aircraft, of their operations and their support became a crucial component for all the market players of the aeronautical industry. This technical field occupies an increasingly significant place, due to the generation of a substantial volume and an extensive variety of operational data. This new trend suggests taking those data into account during preliminary design and certification steps, in order to include additional considerations during those phases, such as operational criteria, maintenance, added value, development times or certification delays. In that way, this paper aims at suggesting a methodology to consolidate the aircraft design and certification processes though the use of those novel “digital” resources.
Multi-disciplinary framework for propeller blade design
Authors: Kümmel A. , Breitsamter C.
Published: January 2021

Improved propeller designs are necessary to ensure an eco-friendly and resource-saving operation. The shape optimization of propellers involves different disciplines, which include the aerodynamics and the structural characteristics of the propeller. The requirements of the individual disciplines for the propeller design are contradictory and compromises must be made. To deal with this complex optimization task, a modular multi-disciplinary optimization framework is developed. The framework is based on a Python control script, which invokes the individual analysis modules. Within the framework, a blade element momentum theory approach for the aerodynamic analysis and a finite element method for the structural analysis are used. This allows for an efficient calculation of various designs. In a first step, a pure aerodynamic optimization is conducted. In a second step, structural constraints in form of the permissible material stress and the propeller blade tip deflection are considered. The results are compared to a design method, which calculates the blade shape for minimal induced losses.
From FAST to FAST-OAD: An open source framework for rapid Overall Aircraft Design
Authors: David Christophe , Delbecq Scott , Defoort Sebastien , Schmollgruber Peter , Benard Emmanuel , Pommier-Budinger Valerie
Published: January 2021

To face the increasing environmental footprint of commercial aviation, industrial and research efforts have been focusing on exploring unconventional configurations and new propulsion paradigms, mostly based on electric technology. Such explorations require Overall Aircraft Design that has to be performed in an integrated multidisciplinary design environment. Such design environments are often limited to multidisciplinary analysis, adapted for a single aircraft configuration or require an important effort to be mastered. FAST-OAD is a software program developed by ONERA and ISAE-SUPAERO for aircraft sizing analysis and optimization that aims at user friendliness and modularity. It is an aircraft sizing code based on multidisciplinary design optimization techniques and the point mass approach to estimate the required fuel and energy consumption for a given set of TLARs. This paper presents the motivations for moving from the original software program, called FAST, to the open source code FAST-OAD based on OpenMDAO.
Performance and emissions of a microturbine and turbofan powered by alternative fuels
Authors: Przysowa Radoslaw , Gawron Bartosz , Bialecki Tomasz , Lçgowik Anna , Merkisz Jerzy , Jasiński Remigiusz
Published: January 2021

BACKGROUND: Alternative fuels containing biocomponents produced in various technologies are introduced in aviation to reduce its carbon footprint but there is little data describing their impact on the performance and emissions of engines. OBJECTIVES: The purpose of the work is to compare the performance and gas emissions produced from two different jet engines: the GTM-140 microturbine and the full-size DGEN380 turbofan, powered by blends of Jet A-1 and one of two biocomponents: 1) ATJ and 2) HEFA produced from used cooking oil (UCO) in various concentrations. The acquired data will be used to develop an engine emissivity model to predict gas emissions. METHODS: Blends of the mineral fuel with synthetic components were prepared in various concentrations, and their physicochemical parameters were examined in the laboratory. Measurements of emissions from both engines were carried out in selected operating points using the Semtech DS gaseous analyzer and the EEPS spectrometer. RESULTS: The impact of tested blends on engine operating parameters is limited, and their use does not carry the risk of a significant decrease in aircraft performance or increase in fuel consumption. Increasing the content of biocomponents causes a noticeable increase in the emission of CO and some other gasses (HC and NOx), which should not, however, worsen the working conditions of the ground personnel. This implies that there are no contraindications against using tested blends for fuelling gas-turbine engines.
Development of a Flight Mechanics Simulation Computer based on a Flexible Aircraft Model for a Regional Aircraft
Authors: Malisani Simone , Capello Elisa , Guglieri Giorgio
Published: January 2021

The changes on aircraft structures and the increased use of advanced and light materials have led to the design of more efficient and flexible aircraft. This implies that rigid body dynamics is no longer sufficient to describe the aircraft behaviour in atmospheric flight. Coupling between structural and rigid body dynamics should be included, due to frequencies of structural modes. In this work, an analytical method, based on a mixed Newtonian-Lagrangian approach, is used to derive a simplified model of a flexible aircraft. Moreover, flexible displacements and torsional variables, starting from the Lagrange’s equations, are discretized by means of a finite number of generalized coordinates. This approach allows to derive directly a finite-order system of ordinary differential equations, making it less complex and suitable for real time simulation and control law synthesis. The main objective of the proposed methodology is the real-time implementation on a “flyable” hardware, for experimental tests, including sensor models. In detail, accelerometers on selected wing sections are design to measure the effect of flexibility in terms of bending and torsional deformations. A simplified low-order model is designed for a regional aircraft, including different masses and flight conditions. Moreover, only two symmetrical bending modes and one torsional mode are considered in the flexibility definition. Finally, the hinge moments acting on the control surfaces are evaluated. The hinge moment is calculated as the aerodynamic torque generated on the hinge axis by the variation of the pressure distribution acting on the control surfaces. A gust response of this aircraft is mainly analysed, considering both a discrete gust model and a continuous model. This research is performed within the ASTIB project, which has received funding from the Clean Sky 2 Joint Undertaking under the European Union’s Horizon 2020 research and innovation program under grant agreement CSJU – GAM REG 2014-2015.
Foundations towards the future: FutPrInt50 TLARs an open approach
Authors: Eisenhut D , Windels E , Reis R , Bergmann D , Ilário C , Palazzo F , Strohmayer A
Published: January 2021

A hybrid-electric regional aircraft for 50 passengers has challenges in technology, operation and future regulations similar to larger class aircraft. It is thus at the right spot to drive technology, regulations and operational developments in order to accelerate cleaner flight technologies based on propulsion electrification. The FutPrInt50 team set up Top-Level Aircraft Requirements that aim to be a reference foundation for the development of specific topics handled in this H2020 project but also drive the open collaboration model adopted by FutPrInt50. In this paper the development of the mission statement will be explained for a hybrid-electric 50 passenger regional aircraft, which builds the framework for the Top-Level Aircraft Requirements. To further support development from these requirements, a mission scenario will be presented for this class of aircraft.
Determination of the 1st Buckling and Collapse Loads for Integrally Stiffened Panels by Artificial Neural Network and Design of Experiment Methodology
Authors: Guzel S , Gurses E
Published: January 2021

Buckling is a structural instability that load carrying capacity of a structural element may suddenly decrease. This sudden change in the load carrying capacity may cause catastrophic failures. Therefore, determination of the first buckling and collapse loads of structural elements is essential. FE analyses and structural testing are used to determine buckling characteristics of a structural element. However, in early design stages, FE analyses are time consuming and structural testing is costly. In this paper, artificial neural network tool is used to reduce computational effort to determine buckling loads of integrally stiffened structural panels in early design stages. Moreover, Latin Hypercube Sampling (LHS) methodology is used to reduce the number of required FE analyses to generate database that artificial neural network is based on. Mean errors and fit performance model results are compared to determine accuracy of the neural network results.
Development of a prototype test system for certification of curved fuselage panels
Authors: Jiménez M. , Cabrera R. , Armario J.L. , Graciani E. , Estefani A. , Muñoz K. , García E. , París F.
Published: January 2021

A prototype test system with capacity to reproduce combined loads representative of real loading cases of a curved fuselage panel has been developed. This prototype test system allows the structural validation of curved fuselage panels to be accomplished. The developed system is able to apply combined mechanical and pressurization loading states under quasi-static and dynamic loading conditions. It has been designed using CAD models and calculated with the aid of Finite Element models to ensure its integrity. A data acquisition system synchronized with a control system enables real time monitoring of test parameters.
Advanced Weather Awareness System for Small Air Transport vehicles: design advancements in the COAST project
Authors: Montesarchio M , Zollo A L , Ferrucci M , Bucchignani E
Published: January 2021

It is well known that, in the aviation sector, flights are strongly influenced by weather conditions, especially considering small aircrafts. This kind of vehicles, ideal for transportation on regional base, are having an increasing importance in the last decades. In the framework of the COAST (Cost Optimized Avionics SysTem) project, funded by Clean Sky 2, several key technologies are under development for the affordable cockpit and avionics in the area of small aircrafts. One of these technologies is AWAS (Advanced Weather Awareness System), devoted to increase the weather awareness of the pilots, providing on board information concerning monitoring and forecasting of weather hazards having not negligible potential impact on the aircrafts. AWAS technology is composed by two applications, namely AWAS on-ground and AWAS on-board, connected each other via a satellite link. The AWAS on-ground is the core of the entire system, devoted to provide on-board synthetic information concerning the weather hazards detected or forecast over an area defined according to the aircraft position. The weather information is extracted from the geodatabase of MATISSE (Meteorological AviaTIon Supporting SystEm), a prototype software developed by the Meteorology Laboratory of CIRA, in which weather data coming from different sources are stored. The AWAS on-board application, instead, is devoted to provide on-ground the required input information (such as the aircraft position). Moreover, it decodes the data received by the on-ground application and allows the visualization of weather information in the cockpit by means of a Human Machine Interface specifically designed for the project. In this work, the main features of the AWAS system are presented, along with the future activities to be carried out in the COAST project.
Compact Computing Platform for Future General Aviation in the COAST Project
Authors: Zaykov Pavel , Beran Jan , Axman Petr
Published: January 2021

The CS-23 category in the General Aviation domain requires affordable, greener technologies and support single-pilot operation. The CS2 COAST project addresses these needs by proposing i) a leap-change in computation performance, ii) reduction of development and operational costs, and iii) reduction of Size, Weight, Power, and Cost (SWaPC). In the COAST project, the findings in these technological areas are packaged in a common platform referred as a Compact Computing Platform (CCP). The CCP effort is split in two areas of development-Platform Engineering and Innovative Elements. The first area covers the development of the necessary Hardware (HW) and Software (SW) building blocks. The second area corresponds to the advanced features that provide product differentiation and competitive advantage on the market. In this paper, we briefly describe the most significant SW and HW components from both technological areas and their potential integration in a demonstrator.
Flight management enabling technologies for single pilot operations in Small Air Transport vehicles in the COAST project
Authors: Di Vito V , Beran J , Kabrt T , Grzybowski P , Rogalski T , Maslowski P , Montesarchio M
Published: January 2021

Small Air Transport (SAT) is emerging as suitable transportation means in order to allow efficient travel over a regional range, in particular for commuters, based on the use of small airports and fixed wing aircraft with 5 to 19 seats, belonging to the EASA CS-23 category. The affordability of the SAT industry needs to be supported by the availability of new technological solutions allowing reducing the related operational costs while at the same time maintaining the required flight safety levels. In this framework, Clean Sky 2 Joint Undertaking funded the project COAST (Cost Optimized Avionics SysTem), which started in 2016 with the aim of tackling this challenge and delivering key technology enablers for the affordable cockpit and avionics, while also enabling the single pilot operations for small aircraft. The project activities cover several technologies and, among them, some selected ones, specifically addressing flight management, are considered in this paper, whose aim is the one of providing an outline of the design and implementation process status reached up to date, emphasizing the obtained results and the work to be done in the future activities expected to be performed in the project. The selected technologies here considered are the ones of tactical traffic separation and enhanced situational awareness, meteorological enhanced awareness, and pilot’s incapacitation emergency management. The paper, therefore, focuses on a selected cluster, from the overall framework of the COAST project, of SAT single pilot operations enabling technologies: Tactical Separation System (TSS), Flight Reconfiguration System (FRS), and Advanced Weather Awareness System (AWAS). In the paper, a description is first reported of the overall COAST project objectives, motivations and approach to the SAT vehicles cockpit design. Then, the implemented design process is outlined and the description of each of the above-indicated selected technologies is presented (the additional technologies considered in the COAST project are out of the scope of this paper). Based on that, for each of the considered systems (TSS, FRS, AWAS) the status of the design and implementation process is described and the next steps expected to be implemented in the project are outlined.
Optical fibers applied to aerospace systems prognostics: design and development of new FBG-based vibration sensors
Authors: Quattrocchi G , Berri P C , Vedova Dalla M D L , Maggiore P
Published: January 2021

Future generation actuation systems will be characterized by ever-increasing complexity. In this context, it will be necessary to adopt advanced health monitoring strategies to guarantee a high level of operational safety and system reliability. Prognostics and Health Management (PHM) is thus emerging as an enabling discipline for the design and operation of future advanced, complex systems. Smart systems with embedded self-monitoring capabilities are nowadays required in order to provide early faults identification and to perform innovative diagnostic and prognostic functions. In aerospace applications, the use of smart sensors could replace various types of traditional sensing elements, commonly used in structural monitoring with the additional capability of performing some prognostics or diagnostics tasks. This work proposes the first results of an experimental campaign aimed at evaluating and validating various packaging solutions for vibration amplification and detection using optical sensors (Fiber Bragg Gratings, FBGs), since characteristics frequencies can be good prognostics indicators of particular failure modes of a system. Several test samples were created by using 3D printed PLA and compared using a variety of bench tests. Results were compared in order to identify the strengths and weaknesses of the various proposed configurations, and were validated by comparing them with numerical simulations and experimental measurements performed with traditional sensors such as strain gages and accelerometers.
High gear ratio mechanical transmissions for actuators: Simplified models for efficiency under opposing and aiding loads
Authors: Berri P C , Vedova M D L Dalla , Maggiore P , Manuello Bertetto A
Published: January 2021

Planetary gear drives are widely employed in electrical and hydraulic actuation systems, to adapt a high speed, low torque motor to a low speed, high torque user, within strict weight and volume constraints. During the early design phases of these devices, accurate yet simple simulation models are required to evaluate the performance of a given configuration of the device. Similar models are also useful within diagnostic and health monitoring analyses of existing machines, as a discrepancy between the actual behaviour of the physical system and that predicted by its digital twin may be the effect of a damage. This work compares different models available in literature for the efficiency of high gear ratio mechanical transmissions; the models are applied to multiple arrangements common for planetary drives, and the results in form of an efficiency map for the transmissions are compared and discussed. The simulations provide different levels of detail, and require different levels of knowledge about the specific architecture of the system. All of them are able to deal with dry friction; additionally, the different behaviour of the transmission under the effect loads aligned in the same direction of speed or in the opposite one is accounted for.
Model-based strategy and surrogate function for health condition assessment of actuation devices
Authors: Berri P C , Vedova M D L Dalla , Quattrocchi G , Maggiore P
Published: January 2021

Prognostics and Health Monitoring (PHM) is a discipline aiming to determine in advance the Remaining Useful Life (RUL) of a system. To do so, the operation of the system is monitored in search of the early signs of degradation and incipient faults; then, a model for the propagation of faults is employed to estimate the propagation of damages and evaluate the RUL. Usually, a fault threshold is employed as a stopping criterion for the evaluation of damage propagation, but this is not a reliable method when dealing with multiple faults affecting the system at the same time. Specifically, the combined effect of two fault modes can cause the system not to meet its requirements well before the single faults reach their individual thresholds. In this work, we address a model-based strategy to estimate whether the system with incipient faults is still able to meet its performance requirements. The method is applied to aerospace actuators, and performance is evaluated in terms of dynamical response. This model-based algorithm is too slow to be evaluated in real-time, so a Support Vector Machine (SVM) is trained as a surrogate function to speed up the computation. The results and computational times of the full, physics based model and those of its surrogate are compared and discussed.
Capabilities of the Regional Cabin Demonstrator as digital twin for a future test mock-up
Authors: Lindner A J M , Norrefeldt V
Published: January 2021

Digital twins are essential for Industry 4.0 and the digitalization of research, development and manufacturing. By now, the models contain more and more information and are already often highly complex systems. However, an important step is to keep the model as simple as possible in order to reduce computing resources and the associated simulation time. The Indoor Environment Simulation Suite (IESS) is a tool to generate a zonal model from a CAD geometry. It is designed to simulate the transient indoor climate in a short time, while still considering all important physical processes (heat conduction, radiation, convection). After the zonal model has been generated, the user can parameterize it specifically to the application and couple it with other models when needed. Here, a new approach is to integrate a thermo-physiological model of the human body in order to make statements about the human perception of thermal comfort. This is of particular interest in early development phases in order to assess air conditioning strategies as well as structural or technical adaptions due to thermal bridges or other influences on the cabin climate. In this paper a concept will be presented where the zonal model is coupled with the thermo-physiological model to investigate selected case studies on how thermal comfort in a regional aircraft can be assessed and considered in early design phases. The cabin model is based on a new type of regional aircraft for which a mock-up is currently being built in order to perform subject test at the Fraunhofer Institute in Holzkirchen. The thermal model can thus make statements in advance about how test scenarios should be carried out in order to gain the greatest possible benefit from the subject study tests, where the number of different tests is limited.
A human factors’ approach for multimodal collaboration with Cognitive Computing to create a Human Intelligent Machine Team: a Review
Authors: Dormoy Charles , André Jean-Marc , Pagani Alain
Published: January 2021

In the Horizon 2020 funded Clean Sky 2 programme, the Cognitive Collaboration for Teaming project aims at positioning a roadmap towards Single Pilot Operations (SPO) and human intelligent machine teaming. Built on top of the states-of-the art of human factors, a careful examination of the factors and parameters to be taken into account to form a Human intelligent Machine Team (HiMT) was carried out. Each parameter can influence positively or negatively teaming. A good HiMT is a HiMT that communicates, shares knowledge, information, collaborates and trusts each other to ensure flight safety at the highest level. This review shows the added value of multimodality for bidirectional communication in the HiMT. Multimodality will allow both verbal and non-verbal communication to be maintained in both directions. A review was conducted on the benefits of each of the modalities and means of interaction under different conditions and how each modality can complement each other for better bidirectional communication that is natural, efficient, and reliable. The objective is to transmit information in a clear, accurate and concise manner, but also to ensure that it is well received by the receiver (i.e. the CCTeammate and the pilot) and well understood. Each modality will allow the CCTeammate to present and/or represent the information in the best possible way to the pilot depending on the context and the task at hand.
Applying Machine Learning Modeling to Enhance Runway Throughput at A Big European Airport
Authors: Stempfel G , Visscher I De , Ellejmi M , Brossard V , Bonnefoy A , Treve V
Published: January 2021

One of the factors limiting busiest airport’s runway throughput capacity is the spacing to be applied between landing aircraft to ensure that the runway is vacated when the follower aircraft reaches the runway threshold. Today, because the Controller is not able to always anticipate the runway occupancy time (ROT) of the leader aircraft, significant spacing buffers are added to the minimum required spacing in order to cover all possible cases, which negatively affects the resulting arrival throughput. The present paper shows how a Machine Learning (ML) analysis can support the development of accurate, yet operational, models for ROT prediction depending on all impact parameters. Based on Gradient Boosting Regressors, those ML models make use of flight information (such as aircraft type, airline, flight data) and weather information to model the ROT. This paper shows how it can be used operationally to increase runway capacity while maintaining or reducing the risk of delivery of separations below runway occupancy time. The methodology and related benefits are assessed using three years of field measurements gathered at Zurich airport.
Impact of Weather Conditions on Airport Arrival Delay and Throughput
Authors: Rodríguez-Sanz Álvaro , Cano Javier , Rubio Fernández Beatriz
Published: January 2021

Weather events have a significant impact on airport arrival performance and may cause delays in operations and/or constraints in airport capacity. In Europe, almost half of all regulated airport traffic delay is due to adverse weather conditions. Moreover, the closer airports operate to their maximum capacity, the more severe is the impact of a capacity loss due to external events such as weather. Various weather uncertainties occurring during airport operations can significantly delay some arrival processes and cause network-wide effects on the overall Air Traffic Management (ATM) system. Quantifying the impact of weather is, therefore, a key feature to improve the decision-making process that enhances airport performance. It would allow airport operators to identify the relevant weather information needed, and help them decide on the appropriate actions to mitigate the consequences of adverse weather events. We present a methodology to evaluate the impact of adverse weather events on airport arrival performance (delay and throughput) and to define operational thresholds for significant weather conditions. Our results are computed from a dataset of over 750,000 flights on a major European hub and from local weather data during the period 2015-2018. We combine delay and capacity metrics at different airport operational stages for the arrival process (final approach, taxi-in and in-block). We introduce a new approach for modelling causal relationships between airport arrival performance indicators and meteorological events, which can be used to quantify the impact of weather in airport arrival conditions, predict the evolution of airport operational scenarios and support airport decision-making processes.
HERA Mission LIDAR Altimeter Implementation
Authors: Dias Nicole G. , Arribas Beltran N. , Gordo Paulo , Sousa Tiago , Marinho Joâo , Melicio Rui , Amorim António , Michel Patrick , Team NEO-MAPP
Published: January 2021

The Asteroid Impact & Deflection Assessment (AIDA) is a collaboration between the NASA DART mission and ESA Hera mission. The aim scope is to study the asteroid deflection through a kinetic collision. DART spacecraft will collide with Didymos-B, while ground stations monitor the orbit change. HERA spacecraft will study the post-impact scenario. The HERA spacecraft is composed by a main spacecraft and two small CubeSats. HERA will monitor the asteroid through cameras, Radar, Satellite-to-Satellite doppler tracking, LIDAR, seismometry and gravimetry. In this paper is reported the first iteration on the LIDAR ENGINEERING MODEL ALTIMETER named HELENA. HELENA is a TOF altimeter that provides time-tagged distances and velocity measurements. The LIDAR can be used for support near asteroid navigation and provides scientific information. The HELENA design comprises a microchip laser and low noise sensor. The synergies between these two technologies enable developing a compact instrument for range measurements of up to 14 km. Thermal-mechanical and radiometric simulations of the HELENA telescope are reported in this paper. The design is subjected to vibrational, static and thermal conditions, and it was possible to conclude by the results that the telescope is compliant with the random vibration levels, the static load and the operating temperatures.
Alternative fuels for aviation: possible alternatives and practical prospects of biofuels
Authors: Adami Renata , Lamberti Patrizia , Tucci Vincenzo , Guadagno Liberata , Valdés Arnaldo Rosa , Zaporozhets Oleksandr , Wacnik Pawel , Burmaoglu Serhat
Published: January 2021

The successful implementation of the new European Green Deal in aviation depends on the European aeronautics industry’s ability to develop new technologies able to face the climate changes. The decarbonization in the aviation is very difficult, compared to other transport sector, and one possibility to reduce emissions is by increasing the usage of low-carbon alternative fuels. Among the analyses carried out within the Horizon 2020 project PARE – Perspectives for Aeronautical Research in Europe, one relevant aspect concerns the possible strategies already applied or under study to reach the zero-emission target using alternative fuels.
Application of machine learning methods for optimizing the technical and economic performance of generating systems
Authors: Arakelyan E K , Boldyrev I A , Evseev K V , Gorban Y A
Published: January 2021

The paper is on the technical and economic performance optimization technique for thermal and power generating system using machine learning methods. The possibility of using regression analysis for parameter influence evaluation when calculating technical and economic performance in order to reach better generating unit efficiency is described. The approach to evaluate the parameter influence of a large distributed control system is presented.
Study of work efficiency of the energy system at the introduction of small hydropower plants
Authors: Zhelyaskova O I , Smirnov A A , Sultanov M M
Published: January 2021

The paper describes a comprehensive approach to assessing the effectiveness of introducing renewable energy sources by the example of switching on small hydropower plants in a certain section of the energy system. The study combines an algorithm for selecting the composition of the included generating equipment in the case of connecting new consumers, and a developed program for calculating and constructing generation and load schedules. The results of the research are presented on the example of the introduction of mini hydroelectric power plants through joint work, the developed approach and the program.
The structure and the electrical properties of a multilayer system based on a composite (Co40Fe40B20)34(SiO2) and zinc oxide
Authors: Zhilova O V , Sitnikov A V , Pankov S Yu , Makagonov V A , Kashirin M A , Babkina I V
Published: January 2021

A heterogeneous multilayer system (Co40Fe40B20)34(SiO2)66/ZnO was obtained by ion-beam sputtering. X-ray diffraction analysis showed that the obtained films have an amorphous multilayer structure. Transmission electron microscopy analysis (TEM) confirmed the formation of separated (Co40Fe40B20)34(SiO2)66 and ZnO layers. The (Co40Fe40B20)34(SiO2)66 composite layers are monogranular with a metal particle size of 1 nm. The thin films remain stable after heat treatment at temperatures up to 350 °C. Measurement of the electrical resistance confirms the formation of a multilayer structure and crystallization of films after heating above 350 °C.
Influence of the separation elements’ shape on the process of water-oil emulsion demulsification in the pipe
Authors: Zinurov V E , Dmitriev A V , Madyshev I N
Published: January 2021

In order to intensify the demulsification of water-oil emulsions, various types of separation elements for the settling tanks are proposed, namely, the corrugated plates with different orientation of corrugations, located at an angle of 45°, 135° and the cross-corrugated plates. The experimental studies of water-oil emulsion demulsification by means of a laboratory unit, using the developed separation elements were conducted. The conducted studies showed that the use of various separation elements inside the settling tanks allows intensifying the process of water-oil emulsion demulsification. The separation elements, considered in this paper, allow the performance of demulsification process with minimum 62% efficiency at the average rate of emulsion movement of more than 0.04 m/s. In the course of studies, it was found that the most effective of the considered separation elements are the corrugated plates with an orientation of corrugations, located at an angle of 45°, allowing the process of water-oil emulsion demulsification with an average efficiency of 80.1% at the movement rate within the range of 0.04–0.053 m/s. It is also shown that for the various separation elements, there are the most effective ranges of emulsion rates, at which the maximum values of demulsification efficiency are achieved.
Analysis of modern environmental management mechanisms for energy providers
Authors: Ivanitckii M S , Sultanov M M , Kuryanova E V , Konstantinov A A
Published: January 2021

In the paper the essential changes in Federal Law № 219-FZ “About changes in Federal Law “On protection of the environment” and the separate acts of the law of Russian Federation” under 21.07.2014 are concerned, the mechanisms and new energy provider environment management principles are analyzed. The main field of environment protection realization from heat power facilities’ negative effects according to the new Russian environmental regulation requirements is presented. The new environmental norming and control principles for industrial facilities based on the best available technologies are determined. Their implementation issues taking into account development financing are analyzed.
Electrochemical properties of AB5type La0.8Ce0.2Ni4Co0.5Mn0.3Al0.2alloy for unified metal hydride fuel cell
Authors: Kazakov A N , Bodikov V Yu , Blinov D V
Published: January 2021

Metal hydride materials are widely applied for electrochemical energy storage. AB5type alloys are the main anode material for Ni-MH batteries. Reversible hydrogen uptake and release provides good opportunities to use metal hydrides for alkaline fuel cell applications. Metal hydrides have good activation performance, high hydrogen sorption/desorption rates, catalytic activity in alkaline solution. Current work presents the first experimental results of AB5type metal hydride electrodes, measured in a battery mode. The electrochemical properties of the prepared electrodes, such as activation performance, maximum discharge capacity, and high rate dischargeability are investigated in detail.
Combined use of the nearest vector selecting technique and low-frequency quarter-wave symmetric space vector PWM in control of three-phase multilevel voltage source inverter
Authors: Lopatkin N N
Published: January 2021

The paper offers the problem’s solution of the three-phase multilevel voltage source inverter (MLVSI) control with low dynamic losses in power semiconductor switches. The proposed technique is based on a single approach that operates with values of the integer and fractional parts of the relative values of the reference delta voltages, and it allows combining the use of the space-vector control, choosing the nearest vector (SVC), with the low-frequency space-vector pulse-width modulation with the quarter-wave symmetry of the output voltages (QWS-SVPWM). Depending on the impedance kind of a generalized load, the integrated voltage harmonics factor (weighted THD) of the appropriate order is being minimized by applying one of the two mentioned modulation methods (SVC or QWS-SVPWM) for a current range of voltage amplitude modulation index. Like its components, the combined algorithm is suitable for MLVSI of any circuit configuration and any number of equal output voltage levels.
Simulation of the static synchronous compensator for the electrical system with non-linear load
Authors: Makarov A V , Makarova T V , Morozov D S
Published: January 2021

This paper presents the STATCOM model in PSIM, which compensate reactive power and current harmonics from the non-linear load. Reactive power consumption and harmonics current of non-linear load given from measurement. The model of STATCOM is a multi-level voltage inverter. Constant system voltage, power factor and harmonics currents are controlled. All modes are realized and plots are plotted.
Experimental obtaining characteristics of current transformers for developing their models and determining the time of saturation of the magnetic circuit
Authors: Batmanov M R , Evdakov A E , Filatova G A , Petrov A E , Yablokov A A
Published: January 2021

Electromagnetic current transformers (CT) are subject to saturation and residual magnetization of a magnetic circuit. This phenomenon has an impact on the operation of devices of commercial accounting of electric energy and relay protection and automatics (RPA). Saturation of the current transformer’s magnetic core can lead to emergency situations due to incorrect operation of the protections and excessive disconnection of the protected connections. At the moment, Russian norms do not regulate the work in transient modes, including short circuits with an aperiodic current component. The Ivanovo State Power Engineering University (ISPEU) conducts research on the topic of determining the time to saturation of CT at short circuit. The purpose of the work was to develop an algorithm for monitoring saturation and determining the time to saturation of the CT magnetic core, in order to ensure the correct operation of the RPA in all modes. The article is devoted to the method of construction and research of mathematical models of CT for calculating the time to saturation. The general structure of the algorithm for determining the time to saturation is presented.
Study of the effect of the thickness of the photosensitive layer of perovskite on its efficiency using SCAPS-1D software
Authors: Rozhko A A , Petrov V V , Sayenko A V
Published: January 2021

Photovoltaic cells are the best way to convert solar energy into electrical energy by absorbing photons emitted by the sun. This paper presents the results of studies of the effect of the thickness of the absorbing layer of perovskite on the quantum efficiency of the solar cell, as well as on its efficiency. These results were obtained by modelling in the software product SCAPS-1D. Perovskite photovoltaic is getting to be a distinctly predominant option for the conventional solar cells achieving maximum efficiency of 22.1% and more. This work is concerned about the design and analyses of lead-based perovskite solar cell model with the architecture of TiO2/CH3NH3PbI3/spiro-OMeTAD. The analysis of solar cell architecture is done using the Solar Cell Capacitance Simulator (SCAPS). It is a computer-based software tool and is well adapted for the analyses of homo and heterojunctions, multi-junctions and Schottky barrier photovoltaic devices. This software tool runs and simulates based on the Poisson’s and continuity equation of electrons and holes. For this model, it is used to optimize the various parameters such as thickness, the defect density of absorber layer, doping concentrations (ND and NA) of Electron Transport Material (ETM) and Hole Transport Material (HTM)
Remote leakage method in heat supply systems out flow
Authors: Sazonova S A , Korablin S N , Asminin V F , Zvyagintseva A V
Published: January 2021

This paper describes the method of remote sensing of the existence or absence of leaks in functioning heat supply systems developed on the basis of the application of a two-alternative hypothesis. To achieve this goal, we proposed to apply a method for determining the location and volume of leaks, based on the use of energy equivalents. We proposed to check for leakage between static assessments of the state of heat supply systems according to data from a remote manometric survey, with the help of which a simultaneous poll of pressure sensors in the end nodes of the system in question is performed. In the event of sudden changes in the estimated system parameters, it is concluded that there is a leak. If the results of two neighboring evaluations are relatively stable, then a conclusion is made about the absence of leakage. The considered problems are based on mathematical models of flow distribution for a heat supply system. The results of a computational experiment are compared with the results of calculating the parameters in the system based on the results of gauge surveying.