bluuebunny/crossref_metadata_2025 huggingface dataset:
Characterization of Fungal Community Composition in the Rhizosphere Soil of Actinidia chinensis Planch Accompanied by Root Rot
Authors: Chen Haisheng , Fang Fang , Zhang Jiancheng , Ding Qihang , Zhao Yi , Chen Yanli , He Yuhao
Published: March 2024

Nowadays, with the development of Actinidia chinensis Planch cultivation, occurrence of Actinidia chinensis Planch root rot disease have increasingly affected the yield and quality of Actinidia chinensis Planch which caused by many kinds of fungal communities. The aim of this paper is to study fungal community structure in rhizosphere soil of Actinidia chinensis Planch infected and non- infected by root rot disease, and to look for monitoring of Actinidia chinensis Planch root rot disease and green ecological control. The rhizosphere soil samples of Actinidia chinensis Planch infected and non-infected by root rot disease were collected respectively in western mountain areas of Huangyan, Taizhou city, Zhejiang province,China, which is the one of the largest Actinidia chinensis Planch planting regional of Zhejiang province. The fungal community structure of rhizosphere soil of Actinidia chinensis Planch were determined by high throughput sequencing techniques. Compared with non-infected soil, the Chao1 indexes of fungal in rhizosphere soil of Actinidia chinensis Planch infected by root rot disease were decreased with significant level. At phylum level, the relative abundance of some dominant fungal in rhizosphere soil of Actinidia chinensis Planch infected by root rot disease were lower than those of non-infected with significant level(P<0.01), such as Basidiomycota, Fungi-unclassified and Zygomycota, while the relative abundance of Ascomycota in rhizosphere soil of Actinidia chinensis Planch infected by root rot disease were higher than those of non-infected with significant level(P<0.01). At genus level, the relative abundance of some dominant fungal in rhizosphere soil of Actinidia chinensis Planch infected by root rot disease were higher than those of non-infected with significant level, such as Gibberella, Nectria, Fusarium, Pseudogymnoascus and Hypocrea, while the relative abundance of some fungal in rhizosphere soil of Actinidia chinensis Planch infected by root rot disease were lower than those of non-infected with significant level(P<0.01), including Agaricomycetes-unclassified, Cladorrhinum, Trechispora, Ophiocordyceps, Acremonium, Ascobolus and Mortierella. It is conclude that in rhizosphere soils of Actinidia chinensis Planch infected with root rot disease, At the phylum and genus levels, great variations in the abundance of the dominant fungal have been confirmed. Actinidia chinensis Planch root rot disease is closely related to the structure of rhizosphere fungi community, and the changes of the balance and diversity of soil fungi is the major cause of Actinidia chinensis Planch root rot disease. The finding could provide some theoretical reference for controlling Actinidia chinensis Planch root rot disease in Zhejiang Province.
Extreme Wind Speed Estimation for Wind-Resistance Design of a Transmission Line Situated in a Typhoon-Prone and Hilly Area
Authors: Bian Rong , Zhang Linlin , Zhu Zidi , Huang Mingfeng , Chen Keji , Bao Xuming
Published: March 2024

The southeastern coast of China is annually threatened by typhoons originating from the northwestern Pacific Ocean, posing a risk of severe damage to coastal transmission lines. This study employs the random forest-based typhoon full-track simulation method and YM wind field to assess the wind-resistance reliability of transmission lines. The obtained extreme wind speeds of a transmission line site in Wenzhou are 33.7m/s and 35.8m/s under the 50-year and 100-year return periods, respectively. The effects of micro-topography on the extreme typhoon wind speed are further analyzed, and the extreme wind speed distribution maps of Wenzhou City and Yueqing City are plotted, respectively. The results indicate a decreasing trend in typhoon wind speed within inland regions, while micro-topography displays a substantial effect on enhancing the typhoon wind speed.
System Performance of Wing and Propellers in a Periodic Distributed Propulsion Experiment
Authors: Lindner T.K. , Oldeweme J. , Scholz P. , Friedrichs J.
Published: March 2024

The design task for distributed propulsion (DP) aircraft is more complex than conventional twin-engine designs due to the pronounced propeller wing interaction. DP concepts rely on a beneficial and robust interaction of propulsion and lifting surface. Additionally, a good DP design is optimised as a system such that each element is not optimised by itself (i.e. ηprop
and CL/CD), but with consideration of the close coupled interaction. The evaluation of such an interaction driven setup is scope of this work. Thrust and torque of a periodic co-rotating DP wing are measured simultaneously with airfoil coefficients. Thereby the influence of propeller on the wing and vice versa are identified.

Two different sets of propeller geometries with a diameter of D = 0.6 m are studied. One propeller set is designed for minimum induced propeller loss (MIL). The second propeller set is designed to have a constant induced axial velocity over the radius (CIV). We shall compare how the different strategies perform in the DP system.

The two element wing has a span of B = 2.4 m and a reference chord of c = 0.8 m, operating at Re = 2.1 × 106. For this study, the propellers are pitched to meet a constant cT, J and Matip
. The results focus on the system performance for the combined setup in take-off configuration. While the isolated propeller efficiency benefits from the integration in front of the wing by > Δηprop = 12%, the system efficiency suffers from increased drag on the trailing wing that is roughly tripled over the clean wing. Depending on the propeller position relative to the wing, interaction losses can be minimised so that a system efficiency gain over the isolated wing and propeller of > Δηsys = 4% is achieved.
Experimental Propeller Performance Analysis of Distributed, Single and Isolated configurations
Authors: Oldeweme Jonas , Lindner Till K. , Scholz Peter , Friedrichs Jens
Published: March 2024

Distributed propulsion (DP) configurations are a promising concept for future aircraft systems. The main objective of the presented experiment is to investigate aerodynamic interactions of such configurations in detail and compare DP results to a single propeller configuration. The experimental setup at the Propulsion Test Facility, TU Braunschweig, features three co-rotating propellers. These are not attached directly to the wing, but are mounted on a separate carrier. This decoupling allows the forces and moments acting on wing and propeller to be considered separately. Additionally, different relative propeller positions are set up easily. In order to eliminate side wall effects, only the centre propeller and the centre wing element are subject of investigation for the distributed configuration. The periodically repeating outboard propellers reduce the wind tunnel interference while providing a true DP setup for the instrumented centre. Additionally to the DP setup, tests for conventional propeller wing configurations (only centre propeller installed) as well as isolated propeller and clean wing tests were performed. Thus, the DP effects on wing and propeller and the effect of the downstream wing on the propeller are clearly identified. The comparison between single propeller and distributed propulsion configurations shows that with distributed propulsion the drag increase is reduced from 326% to 216% compared to a clean wing. This effect is intensified by a greater thrust level and higher angles of attack. In order to identify the distributed propulsion effects, the forces acting on the propeller as well as the resulting efficiency of the propeller are compared between the distributed and single propeller configuration for two different relative propeller positions. The efficiency of the centre propeller is increased due to the outer propellers by approx. 2% to 3%.
Propeller-Wing Interaction: A Simplified Method for Coupling BEM and CFD
Authors: Merola Umberto , Russo Serena , Natale Nunzio
Published: March 2024

This paper presents a numerical procedure for studying the interaction between the wake generated by a propeller and the wing, considering a tiltrotor model framed within the T-TECH Italian project, which has the scope to develop innovative technologies for a flight demonstrator. A tiltrotor is an aircraft that generates lift and propulsion by way of powered rotors mounted on rotating shafts or nacelles at the ends of a fixed wing; in which, in contrast with conventional aircraft, the dimension of the propeller is comparable with the vehicle one. The procedure proposes to couple a 3D low-order unsteady Boundary Element Method (BEM) approach, to evaluate the performance of the isolated propeller, and a Reynolds-Averaged Navier-Stokes (RANS) solution for the analysis of the flow field interaction between the propeller (simulated as actuator disk) and the wing.
A Sensitivity Analysis on the Range Equation of Hybrid-electric aircraft
Authors: Batra A , Raute R , Camilleri R
Published: March 2024

This paper carries out a sensitivity analysis on the recently proposed hybrid-electric range equation [1]. The proposed hybrid-electric range equation is based on an efficiency-based definition of the degree of hybridization and the efficiencies of respective drivetrains on the range estimation of the hybrid-electric aircraft. The ATR 72 turbo-prop aircraft is chosen as the case study for the sensitivity analysis. The sensitivity analysis done in this paper shows the effects of parameters such as lift to drag ratio, efficiencies, energy densities, payload weight, etc. on the aircraft range. It was observed that variation in aircraft range due to each parameter was distinct and unique. The analysis also depicted the implications of the changes in the above-mentioned parameters from an aircraft designer’s viewpoint. The changes were carried out using the predictions for the year 2050. The sensitivity analysis performed in this work successfully narrowed down the parameters that had the maximum impact on the aircraft range.
Conceptual Design and Evaluation of Air Inlets of Fuel Cell-Powered Electric Aero Engines for Regional Aircraft
Authors: Kazula Stefan , Hintermayr David
Published: March 2024

Hydrogen fuel cell-powered electrified propulsion systems hold great promise for the development of sustainable aircraft. However, the integration of fuel cells into aircraft presents unique challenges, particularly in the context of air inlet systems. Key development priorities are to ensure a constant supply of air to the fuel cells and to efficiently manage the transfer of waste heat from the fuel cells. This paper investigates different air inlet systems using analytical methods. Firstly, concepts are identified by analysing the state of the art in air inlet design. Secondly, promising concepts are selected through a qualitative evaluation. Finally, the most promising concept is sized for the given topology. The results of this research highlight the importance of careful air inlet design in order to achieve operability and acceptable performance with fuel cell powered aero engines. The performance and sizing data obtained from the performed analytical calculations can serve as a general basis for the preliminary design of scoop inlets and annular inlets for fuel cell-powered aircraft.
Development of a Series Hybrid Multirotor
Authors: Castellani Nicholas , Pedrosa Francisco , Matlock Jay , Mazur Anna , Łowczycki Krzysztof , Widera Patryk , Zawadzki Kamil , Lipka Karol , Suleman Afzal
Published: March 2024

Hybrid-electric power is an appealing technology for multirotor platforms due to its ability to enhance the range of the vehicle while providing low emissions and the precise thrust control required for vehicle stability. The development of a multirotor utilizing hybrid propulsion is an essential step for CfAR as it will be the basis of research on this technology in flight. The designed multirotor, MIMIQ (Modular Inertia Matching Quadcopter), is a 32kg quadcopter with a motor-to-motor diameter of 2.7m which will require a total of 3,700W of power to hover. This demand is primarily met by the series hybrid generator onboard which requires the battery to only supplement a portion of that power. At peak thrust however, the motors will demand 12,000W from the system. During these rapid bursts of energy the battery plays a critical roll in providing an immediate response to the power demand which the generator would not be able to provide otherwise.

This multirotor is designed to accommodate a wide range of propulsion configurations to optimize performance. In addition, the mechanical characteristics are also intended to be easily adjustable. Parameters such as center of mass, inertia, and motor distance can be adjusted to mimic characteristics of future flight vehicles that implement hybrid systems. Before integration, ground tests were performed on various off-the-shelf hybrid generators in order to evaluate their performance and reliability to ensure that they are well suited for the MIMIQ. To characterize the different modes of operation an extensive performance map was pursued. A number of parameters were measured over time with the most important being load, power, and fuel consumption. It has been proven that at low loads the generator can provide power to the propulsion system while charging the onboard batteries. However, at higher loads both the generator and the battery pack are required to provide power. The tests demonstrated that the integration of a hybrid system into MIMIQ is possible. It was also verified that when the engine is integrated into MIMIQ, both the generator and batteries have to provide power simultaneously in all flight phases.
Validation of a turboprop cabin demonstrator
Authors: Reichherzer Anna , Norrefeldt Victor , Herbig Britta , Müller Benjamin , Vink Peter , Song Yu , Euhus Aenne , May Adrian , Bellmann Michael , Mansfield Neil
Published: March 2024

Turboprop aircraft should be improved as they are more environmentally friendly aircraft compared to turbojet aircraft but noise and vibration are often too high for passengers. A simple and uncomplicated way to carry out experiments is using a demonstrator. To determine whether the demonstrator represents the reality, it must be validated. In this project, real flights were first conducted in a turboprop aircraft. During two 70-minute flights, 94 subjects answered questions about symptoms, mood or comfort levels related to noise and vibration, among other things. In the next step, investigations will be carried out in the demonstrator under the same conditions as the real flights. Both results will be compared with each other. If the data from the demonstrator corresponds to that of the real flights, the demonstrator is considered to have been successfully validated. The requirement for this is that the demonstrator data lies within the confidence intervals of the results from the real flights. The aim is to validate a full-scale on-ground demonstrator of a regional turboprop aircraft cabin that will be used for multiple tests like subject tests and comfort evaluation, composite materials and structures, systems and energy consumption.
Helicopter main rotor FSI analysis using parametric blade model as an application for multidisciplinary optimization
Authors: Kocjan J , Kachel S , Rogólski R
Published: March 2024

This work is part of a research program aimed at finding new approaches and design solutions for helicopter main rotor modelling using multidisciplinary optimization. It is the fourth stage of an individual research program that includes preliminary tasks such as parametric modelling of a single blade, CFD modelling of a full main rotor for different flight conditions, and preliminary structural modelling of a blade. The main goal of this work is to present the parametric modelling of the rotor blade body and structure as an application for complex simulation. The paper demonstrates the method of advanced analysis of the entire rotor and provides exemplary results obtained from complicated analyses. The analytical foundation for combined fluid-structure analysis is presented. The parametric design method is shown to be applicable for different blade planform shapes and various section airfoils. The blade CFD fluid domain is also prepared using the parametric method, as well as the blade’s inner structure. The simulation parameters from the previous stages of research, which serve as inputs to the FSI analysis, are outlined. These previously obtained parameters are combined and introduced into an FSI simulation to assess their compatibility and applicability. The configuration procedure of the analysis and the boundary conditions are presented. The obtained numerical results are then compared with analytical assumptions. The simulation products, which serve as inputs for further analysis, are presented with graphical representations. The time and memory consumption of the simulation are outlined. The application of the described work in an optimization loop is proposed. As a result of this research, new options for main rotor optimization are developed. The paper demonstrates some crucial possibilities of FSI analysis in the described simulation cases. The use of combined parametric modeling with fluid-structure interaction analysis for different flight conditions is presented as a new perspective for multidisciplinary design optimization of a helicopter rotor system.
Performance enhancement of a Box-Wing airliner with the application of riblets
Authors: Bliamis C , Kaparos P , Yakinthos K
Published: March 2024

The rapid growth of the commercial aviation sector in recent years, as well as the ambitious emission reduction targets, necessitate the investigation of novel methods to improve the aerodynamic efficiency of future airliners. With increasing passenger demand and evolving industry requirements, innovative designs, like the Box-Wing aircraft configuration, and flow control techniques, such as riblets, are essential to enhance efficiency, reduce fuel consumption and emissions, and meet future aviation needs. In this work, the performance enhancement of a novel Box-Wing airliner with the application of riblets is investigated through CFD modeling. The riblets are small, streamwise grooves aligned with the airflow, which when applied correctly, can reduce the turbulent skin friction drag. The riblets installed on the aircraft are modeled through a dedicated surrogate model, based on the cross-section area of their groove. In this study, both optimal size riblets, as well as constant size riblets, have been examined, assessing the performance degradation associated with the practical application limitations. The results show that the riblets can improve the aircraft’s aerodynamic characteristics, with a maximum drag reduction of 60 drag counts, as well as the overall flight performance, providing a maximum increase of 6.4% in payload and 13.3% in range.
Stratified materials for aircraft structure: thermal effect of lightning impact by numerical simulations
Authors: Lamberti Patrizia , Mignemi Giulia , Sieni Elisabetta , Durante Tiziana , Mura Monica La , Tucci Vincenzo
Published: March 2024

This paper studies the effect of lightning impact on aircraft fuselage made of innovative Carbon Fibers Reinforced Composites (CFRC) panels, as an alternative to traditional metal structures. Metal layers are able to dissipate the current generated by lightning impacting the structure, whereas the multilayer CFRC panels are less conductive and therefore have limited capacity for current dissipation. This study presents a time-varying thermal simulation coupled with an electromagnetic simulation, considering different lightning currents that represent both short strokes (i.e., impulses), and long strokes (i.e., square pulses). In order to compare different stoke shapes, the temperature increment resulting from the lightning impact will be assessed through Finite Element Analysis. This approach allows for an assessment of the impact of different strokes on CFRC panels. The model serves as a starting point for future analyses aimed at comparing different technological solutions, beginning with experimental laboratory tests.
Characterizing the shape-morphing behaviour of 4D printed PLA structures
Authors: Georgantzinos Stelios K. , Kostopoulos Grigorios , Stamoulis Konstantinos P.
Published: March 2024

This study aims to provide an in-depth characterization of the intelligent behaviour exhibited by structures fabricated using fused deposition modelling (FDM) printing technology. The primary objective is to understand the variability in the shape-morphing behaviour of additively manufactured PLA structures. A comprehensive analysis is conducted to shed light on the impact of various factors on shape transformation, encompassing both working and printing parameters. To establish the relationship between the printing and working parameters with the shape morphing characteristics, the experimental procedure employs Taguchi’s method design of experiments. Notably, the study quantitatively reveals the extent of these parameters’ impact on the characteristics.
Experimental Structural Validation of a Landing Gear System for High-Speed Helicopter Applications
Authors: Arena Maurizio , Miano Mario , Spinaci Francesco , Russo Luca , Kuzmins Nikita , Nasibullins Aleksejs , Castaldo Martina
Published: March 2024

The design and technological demonstration of a Landing Gear architecture were addressed for Airbus fast rotorcraft end application within the Clean Sky 2 Racer project. Numerical activities including advanced modelling approaches were carried out to substantiate the feasibility of structural concepts in compliance with industrial standards and CS-29 applicable airworthiness requirements. In order to demonstrate the goodness of design strategies, a true-scale prototype was manufactured and tested for demonstrating its capability to withstand static loads representative of the limit and ultimate cases expected in service. The paper will focus on the qualification of the Nose and Main Landing Gear systems. Sizing process was validated and verified by test whose results allowed for validating/calibrating the FE model. In such a way, the design database could count on a reliable tool available for analysing the effect of any further load condition change.
Proposed life cycle assessment approach to estimate the environmental impact due to high altitude platform systems
Authors: Solazzo M A , Travascio L , Vozella A
Published: March 2024

The anthropic activities, starting from the early industrial development phases, are pointed-out as concurrent causes affecting the environmental conditions of planet Earth as well as people life quality. Evidences of these influences have been observed even in the remote territories like North and South poles. Every day news report about extreme meteorological events affecting vast geographical areas with heavy loss in terms of victims and damages to infrastructures. In these potential risk scenarios, it is extremely important to support emergency management with timely and accurate geo-spatial information and also to restore minimal communication services. In these severe conditions a relevant role may be played by High-Altitude Platform Systems (HAPS) operating at high altitudes, ranging from 17 to 22 kilometres, typically in the stratosphere, extending coverage for large areas and improving connectivity in remote or underserved areas, bridging the digital divide and providing connectivity to rural or isolated regions, carrying remote sensing instruments, such as imaging sensors or atmospheric sensors, to gather data about the Earth’s surface, weather patterns, or atmospheric conditions. To analyse their sustainability, the proposed work presents the definition of a Life Cycle Assessment (LCA) for two distinct “lighter than air” configurations: an “innovative blimp airship” (IBA) and a classical blimp airship (CBA) as baseline. While IBA configuration is considered as an unmanned, the CBA airship is a manned configuration. The goal of this activity is to support the characterization and validation of the environmental contribution in terms of CO2 emissions due to innovative technologies, concepts and industrial processes adopted for the development of such HAPS configurations. For this assessment SimaPro tool has been used. The applied methodology has adopted the ISO standards: ISO-14040:2006 and ISO-14044:2018 as guidelines to estimate the collectable benefits due to the adoption of innovative eco-design solutions. Specifically, this paper is focused on the identification of materials and on inventory development in order to support the LCA process.
Eco-friendly composites with specific functional properties
Authors: Passaro J , Bifulco A , Guadagno L , Aronne A , Cimino F , Russo P
Published: March 2024

The development of sustainable hydrophobic composite coatings is of high interest for aircraft applications. Currently, the use of natural derived functionalized microparticles as filler to obtain hydrophobic epoxy-based coatings was not deeply investigated. In this scenario, a novel hydrophobic epoxy-based composite including waste hemp microparticles functionalized with silica layer, 3-aminopropyltriethoxysilane, polypropylene-graft-maleic anhydride and silanes (hexadecyltrimethoxysilane and 1H,1H,2H,2H- Perfluorocotyltriethoxysilane) is presented. The resulting coating was casted on typical aeronautical panel, based on carbon-fiber-reinforced polymers, to achieve an improved hydrophobicity and anti-icing property induced by functionalized hemp microparticles.

The wettability and anti-icing property were investigated. Compared to unfilled epoxy resin, the obtained composite coating achieved a greater water contact angle of 30° and doubled increase in icing time. Despite the low content (2 wt.%) of hemp particles, DSC analysis displayed a relevant increase in Tg value, confirming an efficient interaction between the epoxy matrix and the functionalized hemp filler. AFM analysis proved how the presence of hemp filler leads to an increase in roughness due to the hierarchical structure formed by the long chains of silane molecules. The combination of silane activity and rough morphology allows the development of hemp composite coatings with enhanced hydrophobicity, anti-icing behavior and thermal stability for aircraft applications.
Current approaches in UAV Operational Risk Assessment and Practical Considerations
Authors: Gigante G. , Bernard M. , Palumbo R. , Travascio L. , Vozella A.
Published: March 2024

The expansion of Unmanned Aircraft Systems (UAS) is creating new markets, particularly in Urban Air Mobility (UAM), which presents unique challenges. Beyond the risk of mid-air collisions, UAM services in urban areas introduce ground risks to buildings, traffic routes, and pedestrians. This research explores trends in Ground Risk models for different operation planning stages: strategic, pre-tactical, and tactical. It offers a logical pipeline for UAS operators, emphasizing detailed analysis and data source considerations, along with the importance of model interoperability. Using a Naples case study, the research provides practical steps for national authorities to streamline the UAS authorization process.
Analysis of the new market trends of UAVS for safe BVLOS operations
Authors: Politi Elena , Rodosthenous Panagiotis , Dos Reis Ricardo J. , Larsen Morten , Varlamis Iraklis , Dimitrakopoulos George
Published: March 2024

UAVs are currently conquering the skies as prominent tools for various data-intensive applications, in the economic, transport, military and civil sector. While initially found application in the military sector, technology progression allowed them to enter the recreational sector and are now gaining ground in the fringes of the commercial environment. In parallel, technical components and subsystems that are application-optimised focus on highly automated drones, benefit from expertise in other domains, especially when it comes to Electronic Components and Systems (ECS), such as the automotive one, to operate beyond the visual line of sight (BVLOS) with a rather high degree of autonomy. Such technological developments, as well as currents trends and societal needs have opened the way for an unparalleled expansion in the use of UAS for a great number of applications, where humans cannot reach or are unable to perform in a timely and efficient manner. This work aims to present a in-depth analysis of the current market trends that shape the existing landscape for the development of safe and reliable BVLOS operations.
Sustainable Urban Drone Operations: FF2020 view
Authors: Molinari Sara , Tomasello Filippo , Capasso Pasquale Junior , Dallau Arthur
Published: March 2024

Experts worldwide agree that development of operations of Unmanned Aircraft Systems (UAS, commonly known as drones) above populated areas, to remain socially acceptable, must satisfy a set of crucial criteria: safety, security, environmental sustainability (including noise and pollution reduction) and compliance with legal requirements (encompassing liability, privacy and alignment with urban land use regulations). However, for both commercial organisations and entities carrying flights in the public interest, these operations need to also be economically sustainable. This article considers two illustrative scenarios: (1) the urgent transport of medical equipment (e.g., defibrillators) on an ad-hoc basis, precisely when and where required, rather than on a routine schedule; (2) security or plant safety applications, where a drone remains on standby, recharging its batteries in a designated ‘nest,’ ready to take-off for capturing imagery or sensory data when triggered by security personnel or by automatic alerts (e.g., a camera detecting an individual penetrating a perimeter). Deploying one remote pilot for each ‘sleeping’ drone 24/7 would lead to enormous service costs, difficult to be sustained by any organisation. The drone hence needs to be completely autonomous, meaning that a remote pilot would no longer be necessary. The concept, often referred to as ‘Drones in the Box,’ is technically feasible and currently exists. Organisation of the operations, however, goes beyond technical feasibility. According to the Automation Concept by the Joint Authorities for Rulemaking on Unmanned Systems (JARUS), this falls under level 5 of automation. In this highest level, there is neither involvement of a remote pilot in aircraft flight functions, both on the ground and in the air, nor any human awareness of dynamic operational parameters. In essence, to ensure economic sustainability, the 24/7 operations must entirely eliminate the need for remote pilots. Nonetheless, a UAS operator would still exist as the legal entity responsible for organising and overseeing operations, securing necessary approvals and being accountable for the process. Therefore, a professional job profile would still be necessary, to possibly trigger the flight, receive the collected information and act upon or activate the Emergency Response Plan (ERP) when required. This professional would neither need to be trained nor licenced as Remote Pilot but the position should be 24/7. In scenarios such as the two mentioned examples, security personnel may already be on duty 24/7 to safeguard certain facilities (e.g., hospitals) or provide emergency medical services (e.g., 118 in Italy). These operations could thus become economically viable if these personnel were trained by the operator for this on-demand duty. The Flying Forward 2020 (FF2020) project has coined this role as the ‘Fleet Manager’ and intends to standardise it through ISO (International Organisation for Standardisation), for global harmonisation.
Using Eye-Tracking for Adaptive Human-Machine Interfaces for Pilots: A Literature Review and Sample Cases
Authors: Xenos Michalis , Mallas Andreas , Minas Dimosthenis
Published: March 2024

This paper explores the potential of eye-tracking technology in adaptive human-machine interfaces for pilots in aviation. We argue that an interface able to adjust its layout and elements based on pilots’ real-time eye-tracking data can prevent errors and enhance their performance. The study presents a literature review on the use of eye-tracking for various pilot cases, including flight simulator games, drone pilots, and cockpit pilots. Results in most cases showed that eye-tracking has been employed to improve interactions, enhance spatial awareness, guide pilots’ gaze to relevant areas, and provide insights into pilots’ information processing and task load. The paper discusses two sample cases demonstrating the potential of eye-tracking in adaptive human-machine interfaces. In the first case, during challenging drone simulations, eye-tracking identified areas where an adaptive human-machine interface could aid navigation and reduce cognitive load. In the second one, based on real drone flights, when signal loss incidents occurred, eye-tracking data showed that the interface should adapt to pilots’ needs by providing critical information to help them to improve situational awareness. The paper concludes that eye-tracking technology has significant potential in adaptive human-machine interfaces for aviation, emphasising the importance of refining these technologies to meet pilots’ specific needs and enhance flight safety.
Cardiodynamic adjustments in skilled civil aircraft pilots while unexpected emergency conditions appeared during a simulated flight within a homemade Airbus A300 cockpit
Authors: Concu A , Melis S , Marcello R , Dell’Osa AH , Fois A , De Pau A , Tocco F , Mattana D , Usai P , Serra C , Manuello Bertetto A
Published: March 2024

To highlight which cardiodynamic adjustments take place in civil aircraft pilots when unexpected mechanical accidents occur while they are in flight, in 8 skilled pilots we detected the mean blood arterial pressure (MAP) and heart rate (HR) while a unexpected failing of one engine occurred when they were engaged in a simulated flight with a homemade Airbus A300 cockpit. Comparing these two cardiovascular variables in a simulated flight test, just as when the accident happened, together with the values assessed in a simulated control flight without accidents, by the non-parametric Wilcoxon test for paired data it has been found a significant increase of MAP’s median (+ 20.3%, P = 0.008) without significant increase in HR one. However, in several tested pilots this sudden MAP increase tended to progressively recover baseline values while simulating the flight despite the event triggering this functional response was still present.

We concluded that the cardiovascular apparatus of skilled aircraft civil pilots adapts in such a way of sudden respond to unexpected emergency conditions by adjusting mean arterial blood pressure for adequate blood flow to limb muscles, and this happens without a concomitant tachycardia response in order to maintain an optimal mechanical/metabolic efficiency of the heart.
ATM strategies for, and impacts of, space launches
Authors: Robson N , Bolić T , Cook A
Published: March 2024

There is a rapid growth of national space launch ambitions and capabilities, e.g. delivering satellites into low-earth and sun-synchronous orbits. With vertical and horizontal delivery methods, and numerous locations under consideration in several continents, the industry has faced early challenges, such as failed launches and licencing timescales. This paper explores the increasing intersection between aviation and air traffic management (ATM) with higher airspace operations (HAOs). It introduces the background and principles of space launches, before addressing the particular impacts on aviation and ATM. The strategic challenges of planning launch windows to align both with orbiting asset congestion and ATM demands, plus promulgating such information to airspace users, is discussed. In the tactical phase, the consequences of impacts on airspace users (such as the re-routing of flights) and on air navigation service providers (such as the demands of coordinating airspace closures in the context of considerable re-entry/splashdown uncertainty) are discussed. A key contribution we make in this paper is the first aircraft-specific, fuel and operating cost analysis of HAO impacts, and the first such European cost assessment, with basic impact geometries. We also propose improved aircraft-specific impact models, which include passenger-centric costs.
Combustion Efficiency of Carbon-neutral Fuel using Micro-Combustor Designed for Aerospace Applications
Authors: De Giorgi M.G. , Cinieri G. , Marseglia G. , Ali Shah Z. , Mehdi Ghazanfar
Published: March 2024

Recent advancements in the field of micro combustor research are growing for achieving high-performance systems in micro power generation and microelectromechanical devices. To mitigate the hazardous emissions from carbon fuels, as an alternative, zero-carbon-free fuels ammonia, and hydrogen are being explored in micro combustion processes. The distinctive feature of a micro combustor lies in its significantly higher area to volume ratio in comparison with traditional combustion systems, leading to accelerated combustion reaction rates. However, the small size of micro combustors poses a challenge in achieving efficient mixing of highly reactive fuels like hydrogen and ammonia with oxidizers. The unique properties of micro combustors can lead to differences in the combustion behavior of hydrogen and ammonia compared to larger-scale combustion systems. Hence, examining the performance of carbon-free fuels in micro combustors is crucial for the advancement of clean energy combustion systems. A numerical investigation on a Y-shaped micro-combustor was carried out to identify the aspects of non-premixed combustion of ammonia/air and hydrogen/air. The findings reveal that in the case of hydrogen combustion, stable flames were reached, even at low equivalence ratios. Therefore, the distinct combustion properties of hydrogen and ammonia result in varying NOx emissions, with hydrogen generally leading to higher NOx levels due to its higher flame temperature and increased thermal NOx production.
Development of a leveling and loosening mechanism for fine sediments on a test track for planetary robots
Authors: Eisenmenger Jonas , Benz Jonas
Published: March 2024

Planetary robots must be extensively tested before they can be sent on a mission. Especially on loose soil, there is a need for tests with repeatable surface and soil properties to simulate the planetary use and to obtain reliable results for each test run. To achieve this, a leveling and loosening mechanism for a robotic test track is presented. By leveling and loosening in one motion, it enables easy and fast test preparation. Bio-inspired bear claws were designed and tested as loosening tools, which allow loosening with minimal resistance and a loosening effect of about 45%. The modular design allows the attachments to be easily interchanged to adapt the mechanism to different requirements or add additional functions like measurements of the soil properties. The paper provides details on the design and evaluation of the leveling and loosening mechanism.
On the use of cup anemometers as wind speed sensors in stratospheric balloon missions
Authors: Alfonso-Corcuera Daniel , Ogueta-Gutiérrez Mikel , Pindado Santiago , González-Bárcena David , Porras-Hermoso Ángel Luis , Marín-Coca Sergio , Zamorano Juan , Perez-Muñoz Ángel-Grover
Published: March 2024

Stratospheric balloon missions have emerged as a cost-effective alternative to space missions for scientific research and technology development. These missions enable the collection of critical data from the Earth’s upper atmosphere while reducing financial and logistical burdens associated with traditional space missions. One key challenge in these missions is the accurate measurement of the relative-to-the-gondola wind speed in the tropopause and the stratosphere. This paper explores the viability of using cup anemometers as wind speed sensors in stratospheric balloon missions, offering an easy-to-calibrate, low-cost, and accurate solution. The present paper provides a short overview of stratospheric balloon missions and their relevance in atmospheric research and outlines the challenges and limitations of existing wind speed sensing technologies. The cup anemometer is also described, detailing its working principle, advantages, and limitations, and propose a methodology for incorporating the instrument into stratospheric balloon missions. To validate the proposed methodology, a stratospheric balloon mission (the Tasec-Lab experiment, onboard a B2Space balloon launched in 2021), was equipped with a cup anemometer whose performance was analyzed. The results prove that cup anemometers can provide accurate and reliable relative wind speed measurements in the tropopause and the stratosphere. Furthermore, the low power consumption and the ease of development and calibration of cup anemometers make them an attractive option for stratospheric balloon missions.
Including AI experiments onboard the UPMSat-3 satellite mission
Authors: Pérez-Muñoz Ángel-Grover , Alonso Alejandro , Pérez María S. , Zamorano Juan , Valente Hugo , de la Puente Juan A. , Porras-Hermoso Angel , Bayón-Laguna Montserrat
Published: March 2024

Artificial Intelligence (AI) techniques are being used in general-purpose industrial computing systems. There is a great interest in expanding its use across other types of systems. However, they are not immediately applicable to embedded safety-critical systems. In particular, in spacecrafts, there are subsystems with high integrity requirements, which means that their failure could affect the overall behavior of the vehicle or even the loss of the complete mission. This paper deals with the use of some relevant AI techniques onboard space systems. Machine Learning and Neural Networks are potential techniques for these systems. The objective of this paper is to evaluate its applicability, select the most appropriate tools, and determine its feasibility to place onboard the satellite. Through the analysis of standards proposals, and a thermal estimation use case, we identify the issues, challenges, and guidelines to be considered for the use of AI, specifically machine learning, in UPMSat-3.
European Union Transnational R&I Aviation Funding: An AirTN Case Study
Authors: Reyes Sánchez Juan Francisco , Alonso Gustavo
Published: March 2024

One of the main objectives of the European Commission (EC) since the 70s has been to coordinate research policies and to enhance the transnational cooperation in order to reach efficiency in terms of funding and to match with Europe’s economic ambitions. It has been addressed through a centralized approach managed by the EC and a decentralized approach through the cooperation of member states. Regarding the aviation sector, the centralized financing has been successfully implemented under the EU Research & Innovation Framework Programmes, while the decentralized approach has been less successful through the initiative Air Transport Net (AirTN) ERA-NET. The intention of this paper is to analyse the AirTN case study and its methodology to launch transnational calls, the results, and the reasons why it was not completely successful. Following the identification of these main barriers, we provide a list of suggestions that could have been implemented for a more successful outcome.
Preparation and application of superhydrophobic polytetrafluoroethylene materials and micro/nanoindentation
Authors: Zhou Jianfeng , Zhou Xiangru , Zhou Jianjun , Mi Zengzhen
Published: March 2024

A method for preparing superhydrophobic polytetrafluoroethylene materials by micro- and nanoimprinting is discussed. Surfaces with superhydrophobic properties were prepared by designing and imprinting micro- and nano-structures on polytetrafluoroethylene materials. The experiments on weather resistance and durability revealed that the microstructure of screens of different mesh sizes was processed onto the surface of PTFE material by micro-nano thermal imprinting to make it hydrophobic and oleophobic, and retained the original excellent properties of corrosion resistance and low surface attachment, etc. The material processed by the new method has a wide range of application prospects in various fields.
Synthesis of Nano-aluminum Nitride powder at low temperature by Sol-gel method
Authors: Zhang Shuwei , Men Weiwei , Wu Xiao , Zhu Siyu , Xu Hui
Published: March 2024

In this paper, molecular-level mixed aluminum nitride has been prepared from aluminum sec-butyl alcohol, glucose, and urea by sol-gel processing. Then, the nano-aluminum nitride powder with uniform particle size distribution was obtained by carbothermal reduction nitridation reaction. The effects of different feed ratios, reaction temperatures, and holding times on the phase of AlN powder were systematically studied. The prepared nano-aluminum nitride powder has a uniform particle size and a near-spherical shape, and its grain size is approximately 20~30 nm. The preparation temperature in this method was significantly reduced from the same preparation method of aluminum nitride powder.
Research on maintenance-free design and low friction characteristics of industrial robot sliding components
Authors: Zhu Zhuomiao , Guo Junde
Published: March 2024

With the continuous progress of industrial automation, the application of industrial robots in various fields has become increasingly common, and ensuring their efficient and stable operation and reducing maintenance costs is crucial. This study used powder metallurgy technology, combined with multiple sintering-rolling processes and oil-immersed vacuum assistance, to successfully prepare Fe-Cu-Ni-Sn-graphite oil-immersed self-lubricating composite materials to meet this demand. In-depth microstructure and wear surface studies revealed that this porous oil-immersed self-lubricating composite material exhibits long-term low friction and high wear resistance and reduces the friction coefficient by 40% compared to untreated samples after a specific composite process. In addition, the material exhibits excellent friction performance in the high-temperature pin-on-disc friction and wear test machine. Even after continuous sliding for 24 hours, its friction coefficient remains low and stable. The study also found that its lubrication mechanism may be attributed to solid-liquid synergistic lubrication, thanks to the appearance of oil-graphite mixtures around the wear track. This design ensures high rigidity and reduced frictional loss, providing a strong reference for the design and optimization of sliding components of industrial robots, and is highly suitable for the widespread application of industrial robots.
Experimental and numerical study on flexural properties of glass fiber reinforced plastic sandwich plates
Authors: Wang Huijie , Zhang Bei , Qi Zehao , Wang Hong , Chai Yongsheng
Published: March 2024

Due to their high specific strength and stiffness, glass fiber reinforced plastic (GFRP) sandwich plates are widely used in various fields such as construction, aerospace, shipbuilding, and military. This paper studies the bending performance of FRP sandwich plates with reinforcement through experimental and numerical simulation methods. The study shows that the bending performance of unidirectional and bidirectional reinforced plates under the same concentrated load is similar, and bidirectional reinforcement cannot significantly reduce the bending deformation of the sandwich plate. Under uniform load, the four-sided supported bidirectional reinforced sandwich plate can significantly reduce the deformation of the plate, and the deformation can be reduced by 40% compared to the unidirectional reinforced plate.