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Journal articles on the topic 'Aircraft’s life'

Author: Grafiati

Published: 30 May 2022

Last updated: 31 July 2025

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1

Fu, Yueshuai, and Huimin Fu. "A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment." Machines 11, no. 11 (2023): 1016. http://dx.doi.org/10.3390/machines11111016.

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Individual life monitoring is crucial for ensuring aircraft flight safety. Conventional life-consumption-based monitoring methods ignore reliability, thus disjoining them from the aircraft’s reliable life determination and extension, where high confidence and reliability are required. Therefore, this paper proposes a reliable life consumption and individual life monitoring method for aircraft structure fatigue. In the paper, the P-S-N curve, i.e., the relationship between the aircraft structure’s life (N) and fatigue load (S) under a certain probability (P), is established, by which the lower

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2

Kuzmich, O., P. Arkushenko, M. Andrushko, and S. Ratushny. "REGARDING THE ORGANIZATION OF THE INFORMATION SECURITY PROCESS OF THE AIRCRAFT’S LIFE CYCLE COMPONENT." Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки 14, no. 4 (2022): 93–98. http://dx.doi.org/10.37701/dndivsovt.14.2022.10.

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In recent years a number of significant changes have taken place in the field of control, regulation and management in the development processes, manufacture and aircraft’s operation, new international requirements and standards in the field of ensuring flight safety have been put into effect. Large-scale implementation of information technologies in the supporting the technical operation processes of aircraft and monitoring safety of aviation activity is being carried out. The analysis of modern views on the provision in the information component of the aircraft life cycle indicates the

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Hasan, Yusra, Ishak Hasan, Amir A. Aliabadi, and Bahram Gharabaghi. "Comparative Life Cycle Assessment (LCA) in the Aerospace Industry Regarding Aviation Seat Frame Options." Sustainability 17, no. 7 (2025): 3188. https://doi.org/10.3390/su17073188.

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The aerospace industry is actively seeking sustainable solutions within the aviation sector to mitigate greenhouse gas (GHG) emissions driven by increasing population demands. This study presents the first environmental life cycle assessment (LCA) of economy-class seating frames, comparing conventional alloy steel with lightweight alternative materials, including magnesium alloy, aluminum alloy, and titanium. Seat frames account for an aircraft’s total weight, making them a critical component for innovation toward more sustainable solutions. Using SolidWorks V3.1, economy-class seat frames wer

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4

Gerhardinger, David, Anita Domitrović, and Ernest Bazijanac. "Fatigue Life Prognosis of a Light Aircraft Landing Gear Leg." Annual Conference of the PHM Society 12, no. 1 (2020): 9. http://dx.doi.org/10.36001/phmconf.2020.v12i1.1245.

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Aircraft components are subject to fatigue damage. The prediction of fatigue life has significant influence on maintenance and flight operations. Light aircraft, designed for recreational purposes, have vital components that are subject to a hard time maintenance approach. The focus of this article is on a simple method for predicting fatigue life. The method is applied to a light aircraft’s fixed landing gear leg. The landing gear leg is modelled in a computer aided design environment. The load spectrum is determined, based on a characteristic flight profile. Principal strains are determined

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5

Naeem, M. "Impacts of low-pressure (LP) compressor’s deterioration of a turbofan engine upon fuel-usage of a military aircraft." Aeronautical Journal 112, no. 1127 (2008): 33–45. http://dx.doi.org/10.1017/s0001924000001974.

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AbstractSome in-service deterioration in any mechanical device, such as an aircraft’s gas-turbine engine, is inevitable. However, its extent and rate depend upon the qualities of design and manufacture, as well as on the maintenance/repair practices followed by the users. Deterioration of an engine normally results in the engine seeking a different steady operating-point relative to that for an engine without any deterioration. The variation in engine’s steady operating point leads to changes in the specific fuel consumption (SFC) and/or fuel flow (FF). Any rise in SFC and/or FF and thereby th

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Natarajan, Balakrishnan, Amarnadha Reddy, and Nitin Sharma. "A Secure, Configurable, Wireless System for Transfer of Sensor Data from Aircraft to Ground." Defence Science Journal 72, no. 6 (2022): 771–82. http://dx.doi.org/10.14429/dsj.72.17713.

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Modern aircraft are complex systems, equipped with hundreds of embedded sensors that record a wide repertoire of data during flight, such as crucial engine and airframe parameters, status of flight control system, air conditioning system, landing gear, life-saving and emergency systems. The data from the sensors is stored in the Flight Data Recorder. Maintenance personnel routinely transfer this sensor data to a ground terminal device to analyze it for aircraft health and performance monitoring purposes. Manual methods of extracting sensor data can be tedious and error-prone when large fleets

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7

Ge, Zengwen. "Testing method for electrical properties on moving cables of civil aircraft." Journal of Physics: Conference Series 3026, no. 1 (2025): 012059. https://doi.org/10.1088/1742-6596/3026/1/012059.

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Abstract Moving cables of civil aircraft should meet the requirements of the aircraft’s whole life cycle, and the electrical property test is an important means to determine whether the cables are qualified. This paper introduces a test method for electrical properties, including building a test platform based on cable motion characteristics, establishing a test principle based on the relationship between voltage and resistance, clarifying the test idea, etc., and taking the development project of a domestic aircraft Moving cables as an example. This method has been proven to have important pr

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8

White, Paul, David Mongru, and Lorrie Molent. "A crack growth–based individual aircraft monitoring method utilising a damage metric." Structural Health Monitoring 17, no. 5 (2017): 1178–91. http://dx.doi.org/10.1177/1475921717738389.

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The need and benefits of individual aircraft fatigue monitoring are now well established. There are broadly two fatigue damage methods employed for this purpose, namely, crack growth and stress (or strain)-life. The crack growth methods tend to provide a relative comparison between an aircraft’s usage and a baseline usage, while the strain-life methods provide a measure of the amount of fatigue life consumed against that (generally) demonstrated through a fatigue test. In this article, a new crack growth–based tracking method is described that also includes a measure of the certified fatigue l

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9

Chen, Chui Xin, and Yang Hong Mao. "Design of Remote Control Aircraft Model Based on ARM." Applied Mechanics and Materials 568-570 (June 2014): 954–57. http://dx.doi.org/10.4028/www.scientific.net/amm.568-570.954.

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The system designs wireless remote control airplane model, operatie the keys of the remote controller, after the model aircraft receiving the instruction, and handle through the ARM, control the aircraft forward or backward. While the aircraft are working turn left and turn right and straight line, the system makes a judgment on the ultrasonic feedback information, and then control the aircraft’s direction of movement, and display the corresponding information on LCD. after several debugging and operating, System can work stable and reliable. This model can be widely used in the industry and a

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10

Venugopal, Arvinthan, Roslina Mohammad, Md Fuad Shah Koslan, Syed Roslee Sayd Bakar, and Alizarin Ali. "The Effect of Tropical Environment on Fatigue Failure in Royal Malaysian Airforce (RMAF) Aircraft Structure and Operational Readiness." Materials 14, no. 9 (2021): 2414. http://dx.doi.org/10.3390/ma14092414.

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The environmental condition in which the Royal Malaysian Airforce is currently operating its aircraft is prone to corrosion. This is due to the high relative humidity and temperature. With most of its aircraft being in the legacy aircraft era, the aircraft’s main construction consists of the aluminium 2024 material. However, this material is prone to corrosion, thus reducing fatigue life and leading to fatigue failure. Using the concept of either Safe Life or Damage Tolerance as its fatigue design philosophy, the RMAF adopts the Aircraft Structure Integrity Program (ASIP) to monitor its struct

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11

Yadav, Bharosh Kumar, Ramhit Yadav, and K. Sudhakar. "Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study." Orchid Academia Siraha 2, no. 1 (2023): 1–20. http://dx.doi.org/10.3126/oas.v2i1.65618.

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Landing gear failures are a major cause of aircraft failures because they are an integral part of the aircraft's development. According to the Federal Aviation Administration (FAA), 50% of all aircraft failures occur during take-offs and landing. The landing gear of a short take-offs and landing (STOL) aircraft has had its static and dynamic forces analyzed analytically and numerically. SOLIWORKS is used to model the landing gear, and ANSYS is used to perform the numerical simulation results. Following it, the model is examined for stress and deformation with the boundary conditions and comput

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12

Fu, Lei, Hui Li, Li Lin, et al. "Corrosion mechanism and fatigue behavior of 2A70-T6 aluminum alloy under alternating corrosion and fatigue." Anti-Corrosion Methods and Materials 68, no. 5 (2021): 422–37. http://dx.doi.org/10.1108/acmm-02-2020-2265.

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Purpose Most supersonic aircraft were manufactured using 2A70 aluminum alloy. The purpose of this paper is to study the corrosion mechanism and fatigue behavior of an aircraft in a semi-industrial atmospheric corrosive environment, alternating effects of corrosion and fatigue were used to simulate the aircraft’s ground parking corrosion and air flight fatigue. Design/methodology/approach For this purpose, the aluminum alloy samples were subjected to pre-corrosion and alternating corrosion-fatigue experiments. The failure mechanisms of corrosion and corrosion fatigue were analyzed using microsc

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13

Papantoni, Veatriki, Florian Linke, Katrin Dahlmann, et al. "Life Cycle Assessment of Power-to-Liquid for Aviation: A Case Study of a Passenger Aircraft." E3S Web of Conferences 349 (2022): 02003. http://dx.doi.org/10.1051/e3sconf/202234902003.

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The aviation sector is estimated to require a widespread deployment of sustainable fuels next to developments in aircraft technology and improvements in operations and infrastructure to efficiently reduce its climate impact. A possible pathway for more sustainable aviation fuels could be fuel production using hydrogen via water electrolysis with renewable energy followed by Fischer-Tropsch synthesis, also known as Power-to-Liquid (PtL). In order to investigate whether this fuel pathway contributes to the reduction in environmental impacts, we conduct an environmental Life Cycle Assessment (LCA

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14

Xu, Ying, Yu Zhao, Ting Wang, and Xiao Ping Hu. "The Modeling and Performance Analysis of Automatic Drilling & Riveting System Based on Modular Design." Advanced Materials Research 287-290 (July 2011): 2810–15. http://dx.doi.org/10.4028/www.scientific.net/amr.287-290.2810.

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Assembly deformation is one of the most important factors in the aircraft thin-walled parts’ riveting, which determines the plane’s fatigue life and assembly quality. Firstly, A new type of automatic drilling & riveting system used for aircraft’s panel component riveting was studied and designed based on function modular theory. It includes system designing, modeling and assembling by using PRO/E software. Then, Rivet’s stressed deformation was analyzed through finite element analysis. It also explored the law of riveting force which changed the whole process of automatic drilling & ri

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15

Tavares, Sérgio M. O., João A. Ribeiro, Bruno A. Ribeiro, and Paulo M. S. T. de Castro. "Aircraft Structural Design and Life-Cycle Assessment through Digital Twins." Designs 8, no. 2 (2024): 29. http://dx.doi.org/10.3390/designs8020029.

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Numerical modeling tools are essential in aircraft structural design, yet they face challenges in accurately reflecting real-world behavior due to factors like material properties scatter and manufacturing-induced deviations. This article addresses the potential impact of digital twins on overcoming these limitations and enhancing model reliability through advanced updating techniques based on machine learning. Digital twins, which are virtual replicas of physical systems, offer a promising solution by integrating sensor data, operational inputs, and historical records. Machine learning techni

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16

Tomaszek, Henryk, Ryszard Kaleta, and Mariusz Zieja. "A method to assess reliability and life of selected aircraft components suffering from cumulative effect of destructive processes – an outline." Research Works of Air Force Institute of Technology 30, no. 1 (2012): 91–108. http://dx.doi.org/10.2478/v10041-012-0006-0.

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There are two main directions to be distinguished while investigating into the wear-and-tear processes going on within the aircraft’s structural components throughout the operational phase. The first one covers the efforts to explain the physics of the wear-and-tear processes whereas the second one has been intended to generate mathematical models that describe the way how the effects of the wear-and-tear processes accumulate and provoke changes in values of diagnostic parameters. This paper represents the second line of interest and covers the model that formalises the process of the accumula

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17

Brzęczek, Józef, Jerzy Chodur, and Janusz Pietruszka. "Selected Aspects Related to Preparation of Fatigue Tests of a Metallic Airframe." Fatigue of Aircraft Structures 2014, no. 6 (2014): 95–101. http://dx.doi.org/10.1515/fas-2014-0009.

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AbstractThe basis for the computation of the service life of the PZL M28 was the results of the full-scale fatigue tests of the structure [1]. As the PZL M28 is a commuter category airplane according to the 14 CFR Part 23 and CS-23 regulations, the test objects were: (1) wing and wing load carry-through structure, (2) empennage and attached fuselage structure. Additionally, there were fatigue tests carried out for the landing gear and other selected elements including control system elements. The aircraft load carry-through structure is metallic and the cabin is unpressurized. The fatigue test

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18

Naeem, M. "Impacts of low-pressure (LP) compressor’s deterioration upon an aero-engine’s high-pressure (HP) turbine blade’s life consumption." Aeronautical Journal 110, no. 1106 (2006): 227–38. http://dx.doi.org/10.1017/s0001924000001202.

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AbstractSome in-service deterioration in any mechanical device, such as an aero-engine, is inevitable. As a result of experiencing a deterioration of efficiency and/or mass flow, an aero-engine will automatically adjust to a different set of operating characteristics; thereby frequently resulting in changes of rpm and/or turbine entry temperature in order to provide the same thrust. Rises in the turbine entry-temperatures and the high-pressure turbine’s rotational speed result in greater rates of creep and fatigue damage being incurred by the hot-end components and thereby higher engine’s life

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19

Venugopal, Arvinthan, Roslina Mohammad, Md Fuad Shah Koslan, Ashaari Shafie, Alizarin bin Ali, and Owi Eugene. "Crack Growth Prediction on Critical Component for Structure Life Extension of Royal Malaysian Air Force (RMAF) Sukhoi Su-30MKM." Metals 11, no. 9 (2021): 1453. http://dx.doi.org/10.3390/met11091453.

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The critical aircraft structure, being the load-bearing members, is a vital component for any aircraft. The effect of fatigue loading, operating conditions, and environmental degradation has caused the structural integrity of the airframe to be assessed for its airworthiness requirement. Using the fatigue design concept of Safe Life, the RMAF adopts the Aircraft Structure Integrity Program (ASIP) to monitor the structural integrity of its critical components. RMAF has produced the task card using the engineering analysis concept on the aircraft’s critical structure. Various Computer-Aided Engi

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20

Liu, Xiaofeng, Liuqi Xiong, Yiming Zhang, and Chenshuang Luo. "Remaining Useful Life Prediction for Turbofan Engine Using SAE-TCN Model." Aerospace 10, no. 8 (2023): 715. http://dx.doi.org/10.3390/aerospace10080715.

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Turbofan engines are known as the heart of the aircraft. The turbofan’s health state determines the aircraft’s operational status. Therefore, the equipment monitoring and maintenance of the engine is an important part of ensuring the healthy and stable operation of the aircraft, and it is vital to monitor the remaining useful life (RUL) of the engine. The monitored data of turbofan engines have high dimensions and a long time span, which cause difficulties in predicting the remaining useful life of the engine. This paper proposes a residual life prediction model based on Autoencoder and a Temp

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21

Wood, O. J., C. A. Featherston, D. Kennedy, Mark J. Eaton, and Rhys Pullin. "Optimised Vibration Energy Harvesting for Aerospace Applications." Key Engineering Materials 518 (July 2012): 246–60. http://dx.doi.org/10.4028/www.scientific.net/kem.518.246.

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Accurate knowledge regarding the ongoing condition of an aircraft’s structural condition together with future life predictions enable optimal use of material, hence reducing mass, cost and environmental effects. Previous work by the authors has demonstrated the potential for using energy harvested from vibrating aircraft panels to power a self contained health monitoring system based on the use of wireless sensor nodes for an aircraft structure. However the system proposed was far from optimal. Research is being undertaken to investigate the various factors affecting the power output of such a

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22

Fu, Yueshuai, Huimin Fu, and Sheng Zhang. "A Novel Safe Life Extension Method for Aircraft Main Landing Gear Based on Statistical Inference of Test Life Data and Outfield Life Data." Symmetry 15, no. 4 (2023): 880. http://dx.doi.org/10.3390/sym15040880.

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Safe life extension work is demanded on an aircraft’s main landing gear (MLG) when the outfield MLG reaches the predetermined safe life. Traditional methods generally require costly and time-consuming fatigue tests, whereas they ignore the outfield data containing abundant life information. Thus, this paper proposes a novel life extension method based on statistical inference of test and outfield life data. In this method, the MLG’s fatigue life is assumed to follow a right-skewed lognormal distribution with an asymmetric probability density function. In addition, the MLG’s new safe life can b

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Tian, Yu, Shifu Liu, Le Liu, and Peng Xiang. "Optimization of International Roughness Index Model Parameters for Sustainable Runway." Sustainability 13, no. 4 (2021): 2184. http://dx.doi.org/10.3390/su13042184.

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Pavement roughness is a critical airport pavement characteristic that has been linked to impacts such as safety and service life. A properly defined roughness evaluation method would reduce airport operational risk, prolong the life of aircraft landing gear, and optimize the decision-making process for pavement preservation, which together positively contribute to overall airport sustainability. In this study, we optimized the parameters of the International Roughness Index (IRI) model to resolve the current poor correlation between the IRI and aircraft vibration responses in order to adapt an

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24

Thakkar, Unnati, and Hicham Chaoui. "Remaining Useful Life Prediction of an Aircraft Turbofan Engine Using Deep Layer Recurrent Neural Networks." Actuators 11, no. 3 (2022): 67. http://dx.doi.org/10.3390/act11030067.

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The turbofan engine is a pivotal component of the aircraft. Engine components are susceptible to degradation over the life of their operation, which affects the reliability and performance of an engine. In order to direct the necessary maintenance behavior, remaining useful life prediction is the key. This research uses machine learning to provide a prediction framework for an aircraft’s remaining useful life (RUL) based on the entire life cycle data and deterioration parameter data (ML). For the engine’s lifetime assessment, a Deep Layer Recurrent Neural Network (DL-RNN) model is presented. T

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Wang, Yuhui, Peng Shao, Qingxian Wu, and Mou Chen. "Reliability analysis for a hypersonic aircraft’s wing spar." Aircraft Engineering and Aerospace Technology 91, no. 4 (2019): 549–57. http://dx.doi.org/10.1108/aeat-11-2017-0242.

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Purpose This paper aims to present a novel structural reliability analysis scheme with considering the structural strength degradation for the wing spar of a generic hypersonic aircraft to guarantee flight safety and structural reliability. Design/methodology/approach A logarithmic model with strength degradation for the wing spar is constructed, and a reliability model of the wing spar is established based on stress-strength interference theory and total probability theorem. Findings It is demonstrated that the proposed reliability analysis scheme can obtain more accurate structural reliabili

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Pinheiro Melo, Sofia, Alexander Barke, Felipe Cerdas, et al. "Sustainability Assessment and Engineering of Emerging Aircraft Technologies—Challenges, Methods and Tools." Sustainability 12, no. 14 (2020): 5663. http://dx.doi.org/10.3390/su12145663.

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Driven by concerns regarding the sustainability of aviation and the continued growth of air traffic, increasing interest is given to emerging aircraft technologies. Although new technologies, such as battery-electric propulsion systems, have the potential to minimise in-flight emissions and noise, environmental burdens are possibly shifted to other stages of the aircraft’s life cycle, and new socio-economic challenges may arise. Therefore, a life-cycle-oriented sustainability assessment is required to identify these hotspots and problem shifts and to derive recommendations for action for aircr

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Cui, Jianguo, Baosheng Liu, Guihua Wang, Mingyue Yu, and Yang Gao. "Life Trend Analysis of Aircraft’s Key Component Based on Power Spectral Envelope Energy and SVM." International Journal of Advanced Science and Technology 84 (November 30, 2015): 65–74. http://dx.doi.org/10.14257/ijast.2015.84.06.

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28

Tripathi, Veenu, and Stefano Caizzone. "Virtual Validation of In-Flight GNSS Signal Reception during Jamming for Aeronautics Applications." Aerospace 11, no. 3 (2024): 204. http://dx.doi.org/10.3390/aerospace11030204.

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Accurate navigation is a crucial asset for safe aviation operation. The GNSS (Global Navigation Satellite System) is set to play an always more important role in aviation but needs to cope with the risk of interference, possibly causing signal disruption and loss of navigation capability. It is crucial, therefore, to evaluate the impact of interference events on the GNSS system on board an aircraft, in order to plan countermeasures. This is currently obtained through expensive and time-consuming flight measurement campaigns. This paper shows on the other hand, a method developed to create a vi

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29

Донець, Олександр Дмитрович, Олександр Іванович Семенець, Євген Тимофійович Василевський, Олександр Григорович Гребеніков та Андрій Михайлович Гуменний. "КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ РІШЕННЯ ЗАБЕЗПЕЧЕННЯ СТАТИЧНОЇ МІЦНОСТІ ТА РЕСУРСУ РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ". Open Information and Computer Integrated Technologies, № 82 (19 грудня 2018): 4–26. http://dx.doi.org/10.32620/oikit.2018.82.01.

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Ensuring flight safety and aircraft structure lifetime is important today’s problem in development of up-to-date regional passenger aircraft. This paper deals with the aspects of providing static strength and lifetime of regional passenger aircraft. A series of factors and parameters were analyzed, which affect the aircraft static strength, lifetime, such as: fatigue, corrosion, wear, fretting-corrosion, human factor.n To ensure static strength, operational and design loads were determined for the entire range of design speeds and flight altitudes, overloads, aircraft weights and CG positions,

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Pohya, Ahmad Ali, Jennifer Wehrspohn, Robert Meissner, and Kai Wicke. "A Modular Framework for the Life Cycle Based Evaluation of Aircraft Technologies, Maintenance Strategies, and Operational Decision Making Using Discrete Event Simulation." Aerospace 8, no. 7 (2021): 187. http://dx.doi.org/10.3390/aerospace8070187.

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Current practices for investment and technology decision making in aeronautics largely rely on regression-based cost estimation methods. Although quick to implement and easy to use, they suffer from a variety of limitations, both in temporal space and scope of applicability. While recent research and development in this area addresses these to a certain extent, aerospace engineering still lacks a flexible and customizable valuation framework. To this end, a generic environment for economic and operational assessment of aircraft and related products named LYFE is presented. This tool employs a

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Cunha, Denner, Brooke Wheeler, Isaac Silver, and Gaspar Andre. "Electric Aircraft Battery Performance: Examining Full Discharge Under Two Conditions." Volume 04 Issue 01 vm04, is01 (2023): 5–13. http://dx.doi.org/10.23890/ijast.vm04is01.0101.

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The understanding of battery performance, particularly over the full course of discharge and over battery life is critical to allow pilots to maintain safety in electric aviation. In this study, an electric aircraft powered by two Lithium-Ion battery packs is used as a test article. The objectives of the current study are to build on previous work by conducting two full tests discharging both battery packs from a 100% charge. This allows examination of the battery performance a) under a constant power output and b) with periodic tests of the maximum power available. In addition to state of cha

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Hu, Zicheng, Liangchong Zhu, Xin Mo, and Keming Shen. "Numerical study on transonic shock wave buffeting of airfoil." Journal of Physics: Conference Series 2879, no. 1 (2024): 012032. http://dx.doi.org/10.1088/1742-6596/2879/1/012032.

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Abstract Modern transportation aircraft typically cruise at transonic speeds. However, under a specific combination of incoming flow Mach numbers and angles of attack, periodic self-excited oscillations of shock waves can lead to unsteady aerodynamic loads, causing sustained vibrations in the aircraft, which is known as transonic shock wave buffeting. Buffeting loads significantly impact the fatigue life of the aircraft’s structural materials and its handling performance. In severe cases, it causes structural damage or even leads to flight safety incidents, so we should pay more attention to t

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Deng, Kailun, Agusmian Partogi Ompusunggu, Yigeng Xu, Martin Skote, and Yifan Zhao. "A Review of Material-Related Mechanical Failures and Load Monitoring-Based Structural Health Monitoring (SHM) Technologies in Aircraft Landing Gear." Aerospace 12, no. 3 (2025): 266. https://doi.org/10.3390/aerospace12030266.

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The aircraft landing gear system is vital in ensuring the aircraft’s functional completeness and operational safety. The mechanical structures of the landing gear must withstand significant operational forces, including repeated high-intensity impact loads, throughout their service life. At the same time, they must resist environmental degradation, such as corrosion, temperature fluctuations, and humidity, to ensure structural integrity and long-term reliability. Under this premise, investigating material-related mechanical failures in the landing gear is of great significance for preventing l

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Liu, Shifu, Jianming Ling, Yu Tian, Tianxin Hou, and Xindong Zhao. "Random Vibration Analysis of a Coupled Aircraft/Runway Modeled System for Runway Evaluation." Sustainability 14, no. 5 (2022): 2815. http://dx.doi.org/10.3390/su14052815.

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Runway roughness is one of the most critical performance factors for runway evaluation, which directly impacts airport operation safety and pavement preservation cost. Properly evaluated runway roughness could optimize the decision-making process for runway preservation and therefore reduce the life cycle cost of the runway pavement asset. In this paper, the excitation effect of runway roughness is analyzed using a coupled aircraft/runway system. The coupled system is composed of a two degrees-of-freedom (2-DOF) aircraft model and a typical asphalt runway structure model established under runw

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Soysal, Aysun, Ibrahim Ozkol, and Erol Uzal. "An Analytical-Based Lightning-Induced Damage Model for an Aircraft Wing Exposed to Pressure Loading of Lightning." Mathematical Problems in Engineering 2024 (January 27, 2024): 1–17. http://dx.doi.org/10.1155/2024/8313135.

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Lightning is one of the natural hazards that any aircraft may encounter while navigating. If adequate precautions are not taken against lightning, structural damage, operational disruptions, and loss of life and property can occur. Thus, studying the mechanism of damage caused by lightning strikes in an aircraft’s structural material is necessary to optimize the structure, minimize the damage, and reduce the cost caused by lightning. In the present article, the lightning-induced damage behavior of an aircraft structural material was investigated from an analytical perspective. For this purpose

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Varyukhina, E. V., and V. V. Klochkov. "ASSESSING THE EFFECTIVENESS OF INTELLECTUAL TECHNOLOGIES FOR IDENTIFYING HAZARDOUS COMBINATIONS OF EVENTS IN CIVIL AVIATION FLIGHT SAFETY MANAGEMENT." Control Sciences, no. 2 (May 15, 2024): 59–65. http://dx.doi.org/10.25728/cs.2024.2.6.

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This paper proposes an approach to assessing the effectiveness of intellectual technologies (artificial intelligence and machine learning) for identifying hazardous combinations of events in air transport systems. The influence of such technologies on flight safety and the aircraft’s total cost of ownership is formalized. A simple model is developed to assess the effectiveness of implementing intellectual technologies when identifying a single hidden problem. This model is qualitatively analyzed to reveal the role of its parameters (the size and flight hours of the aircraft fleet, the duration

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Pinto, Joseph Ciano, Siva Marimuthu, Parvathy Rajendran, Manikandan Natarajan, and Rajadurai Murugesan. "Computational Analysis of Blended Winglet Designs to Reduce the Wake Turbulence on the Airbus A380 Wingtip." Eng 6, no. 4 (2025): 68. https://doi.org/10.3390/eng6040068.

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The aviation sector faces a significant challenge in balancing the rising demand for air travel with the need to reduce its environmental impact. Because air travel accounts for approximately 2.5% of global carbon emissions, there is a need to find sustainable solutions to reduce its environmental impact. Improving aerodynamic performance is a crucial area for reducing fuel consumption and emissions. Nowadays, more focus is given to commercial aviation, which contributes to global aviation emissions. The A380 is the largest passenger aircraft in the world at the moment. It was observed in real

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Skorupka, Zbigniew. "Dynamic Fatigue Tests Of Landing Gears." Fatigue of Aircraft Structures 2020, no. 12 (2020): 69–77. http://dx.doi.org/10.2478/fas-2020-0007.

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Abstract Landing gears are one of the main components of an aircraft. The landing gear is used not only during take-off and landing but also, in most cases, during ground manoeuvres. Due to its function, the landing gear is also one of the key safety components of the aircraft due to dissipating landing loads acting on the aircraft. The mentioned loads come from both the vertical and horizontal speeds during touchdown and by the aircraft’s losing the speed by braking. The landing gear is then loaded with constantly changing forces acting in various directions during every landing, with the onl

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DUEE, Raphael, Alexis MARTIN, Hugo VASSEUR, and Jean-Frédéric DESJARDINS. "Aircraft automatic detection on Station7hz interface using signal processing and artificial intelligence - ACOUDET - First method." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 270, no. 6 (2024): 5767–75. http://dx.doi.org/10.3397/in_2024_3644.

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The global project is to design a automatic noise event detection and classification system in real time using signal processing and artificial intelligence (AI). The first phase focuses on transport noise (aircrafts, trains, road vehicles, etc.). Secondly, the plan is to extend detection to construction site noise and any natural or life sources. This paper presents the first method developed to detect audible aircrafts pass-by. It focused on the development of a prototype detection algorithm, its results in situ conditions, and insights on future developments to create a robust aircraft and

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Fadlelbari, M. Faisal. "Efficiency of Vierendeel Girder, Post-tensioned Girders and Steel Beams for Long Cantilevers in Buildings." FES Journal of Engineering Sciences 9, no. 1 (2021): 79–85. http://dx.doi.org/10.52981/fjes.v9i1.662.

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Cantilevers are a part of our life, they are everywhere: bridg–es, building’s balconies, traffic signs, car parking shades even the aircraft’s wings. The long cantilevers of the buildings always present as a big challenge to structural engineers in their practice life. The structural behavior of these cantilevers depends on a several factors, such as rigidity of the slab, rigidity of columns or walls, span continuity... etc. But the real dilemma lies in the economical choice. This paper focused on the cantilever’s structural analysis according to the used structural. Moreover, it shows a compa

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Nan, Guofang, Ying Wang, Yihui Zhou, Haoyu Wang, and Yao Li. "Dynamic Modeling and Safety Analysis of Whole Three-Winch Traction System of Shipboard Aircraft." Aerospace 12, no. 7 (2025): 579. https://doi.org/10.3390/aerospace12070579.

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The winch traction system for shipboard aircraft, when operating in a marine environment, is subjected to additional forces and moments due to the complex motion of the hull. These loads pose significant threats to the safety of the aircraft during the traction process. To address the safety issues under complex sea conditions, this paper adopts harmonic functions to describe the rolling, pitching, and heaving motions of the hull. A theoretical analytical model of the three-winch traction system, considering the intricate coupling motions of the ship, is established. Unlike previous studies th

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Roques, Axel, Yannick James, Nicolas Vayatis, and Pierre-Paul Vidal. "Beware of physiology: Anthropomorphism as a simplification mechanism for mastering complex human-machine interfaces." PLOS ONE 20, no. 4 (2025): e0321580. https://doi.org/10.1371/journal.pone.0321580.

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Humans’ remarkable technical reasoning skills have led to the development of increasingly sophisticated tools. In particular, society has welcomed the advent and democratization of machines that produce effects through indirect causal chains. Intuitively, perfect mastery of such systems should require a detailed understanding of their underlying processes. This raises the question of the boundaries of human cognitive abilities in the context of tool use. In other words, can the human brain integrate the characteristics of any tool, or are there inherent limitations? The present study investiga

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Novikov, Sergey, and Andrey Sazonov. "Description of the Determination Processes for the Typical Research and Development Intensity Normative Indicators." Research in World Economy 11, no. 1 (2020): 64. http://dx.doi.org/10.5430/rwe.v11n1p64.

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The article is devoted to description of the determination processes for the typical research and development (R&D) intensity normative indicators. In the theoretical part, the authors consider the standards system formation and labor costs norms for R&D. The main composit element (CE) hierarchy of the R&D technology is given. The scheme of the development algorithm for the R&D labor costs standards is drawn. The labor costs norming technique for research works is considered. The procedure for determining the labor costs normative volume for a standardized object is determined.

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Sui, Dong, Chenyu Ma, and Chunjie Wei. "Tactical Conflict Solver Assisting Air Traffic Controllers Using Deep Reinforcement Learning." Aerospace 10, no. 2 (2023): 182. http://dx.doi.org/10.3390/aerospace10020182.

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To assist air traffic controllers (ATCOs) in resolving tactical conflicts, this paper proposes a conflict detection and resolution mechanism for handling continuous traffic flow by adopting finite discrete actions to resolve conflicts. The tactical conflict solver (TCS) was developed based on deep reinforcement learning (DRL) to train a TCS agent with the actor–critic using a Kronecker-factored trust region. The agent’s actions are determined by the ATCOs’ instructions, such as altitude, speed, and heading adjustments. The reward function is designed in accordance with air traffic control regu

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Tang, Haihong, Panglun Liu, Jianbin Ding, Jinsong Cheng, Yiyao Jiang, and Bingyan Jinag. "Numerical Prediction of Fatigue Life for Landing Gear Considering the Shock Absorber Travel." Aerospace 12, no. 1 (2025): 42. https://doi.org/10.3390/aerospace12010042.

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Due to the complexity of the landing gear’s (LG) structural integrity and its loads under various static or dynamic working conditions, the fatigue life assessment for LG is a highly challenging task. On the basis of the whole geometric model of a large passenger aircraft’s main landing gear (MLG), the quasi-static finite element model (FEM) of the whole MLG is established, and the high-cycle fatigue issue of the Main Fitting (MF) is studied by considering the variation in shock absorber travel (SAT). Firstly, the ground loads under actual fatigue conditions are equivalently converted into the

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Meissner, Robert, Patrick Reichel, Peter Schlick, Christian Keller, and Kai Wicke. "Engine Load Prediction during Take-Off for the V2500 Engine." PHM Society European Conference 5, no. 1 (2020): 12. http://dx.doi.org/10.36001/phme.2020.v5i1.1214.

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The aviation industry faces an ever increasing pressure to reduce its cost in order to gain competitive advantages. Since aircraft maintenance contributes strongly with about 17% to the overall direct operating cost (DOC), maintenance providers are required to continuously reduce their cost share as well. As a result, a lot of effort is put into the exploitation of the potential of emerging digitalization technologies to predict upcoming system faults and, therefore, reduce the projected maintenance impact. The detection of early stage faults and prediction of remaining useful lifetimes (RUL)

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Jain, Shubham. "Applications of Additive Manufacturing in Aerospace: Reducing Weight and Cost in Aircraft Design." International Journal of Research in Modern Engineering & Emerging Technology 10, no. 4 (2022): 18–25. https://doi.org/10.63345/ijrmeet.org.v10.i4.3.

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Additive manufacturing (AM), commonly known as 3D printing, has emerged as a transformative technology in aerospace engineering, enabling the fabrication of complex geometries, lattice structures, and multi‐material components that were previously unachievable through conventional subtractive processes. This manuscript investigates the applications of AM in reducing both weight and cost in aircraft design, with a focus on technologies and materials developed up to 2022. A systematic methodology comprising design selection, process parameter optimization, and mechanical testing was employed to

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Варюхина, Е. В., and В. В. Клочков. "ASSESSING THE EFFECTIVENESS OF INTELLECTUAL TECHNOLOGIES FOR IDENTIFYING HAZARDOUS COMBINATIONS OF EVENTS IN CIVIL AVIATION FLIGHT SAFETY MANAGEMENT." Проблемы управления, no. 2 (April 27, 2024): 74–82. http://dx.doi.org/10.25728/pu.2024.2.6.

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Предложен подход к оценке эффективности интеллектуальных технологий выявления опасных сочетаний обстоятельств в авиатранспортных системах. Формализовано влияние таких технологий на безопасность полетов и общую стоимость владения авиационной техникой. Разработана простая модель оценки эффективности внедрения интеллектуальных технологий (для выявления единичной скрытой проблемы). Качественный анализ этой модели позволил выявить роль различных ее параметров – таких как численность и налет парка авиационной техники, длительность и стоимость устранения системной проблемы, ущерб от событий различной

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Kolanjiappan, S. "Innovative Approach in Introducing Lean Manufacturing Tools in Maintenance of Aircraft." Applied Mechanics and Materials 766-767 (June 2015): 1190–95. http://dx.doi.org/10.4028/www.scientific.net/amm.766-767.1190.

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Lean manufacturing was initially introduced successfully in Japan to enhance the production standard of cars in Toyota Company. These lean principles were initially known as Toyota Production system (TPS)[2]. Lean seeks to eliminate all forms of waste in the manufacturing process—including waste in the maintenance operation[1].This present study about lean principles if could be introduced in maintenance of aircraft the standard of maintenance process could be significantly improved. Hence study of experimental research was carried out on pre-matured failure of lifed hydraulic components of te

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Żyluk, Andrzej, Mariusz Zieja, Justyna Tomaszewska, Mariusz Michalski, and Krzysztof Kordys. "Service Life Prediction for Rotating Electrical Machines on Aircraft in Terms of Temperature Loads." Energies 16, no. 1 (2022): 218. http://dx.doi.org/10.3390/en16010218.

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This article is focused on the research concerning the calculation of the durability of electrical machines installed in the electrical system of M-28 and C-130 Hercules aircraft. The article presents a method of predicting the service life of aircraft commutator machines, which are the primary source of electrical energy. The result of the research was the determination of the durability of bearings and coils of electrical machines operated on aircraft based on a flight profile analysis. It is problematic to directly measure the wear of bearings and windings of an electric machine on the airc

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