bluuebunny/crossref_metadata_2025_split 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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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

Abstract
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.