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Journal articles on the topic 'Aircraft structure'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Xia, Liang, Xuhui Lan, Jinsong Chen, Xin Chen, Ran Wang, and Jiaxun Wu. "Research on the design laws of stealth structures for typical components of aircraft leading edges." Journal of Physics: Conference Series 2820, no. 1 (2024): 012013. http://dx.doi.org/10.1088/1742-6596/2820/1/012013.

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Abstract Considering the design of stealth structures for typical components of aircraft leading edges, this article selects typical aircraft’s leading edge structures. Firstly, the stealth mechanism of the aircraft’s leading edge structure is analyzed. Then, by adjusting the height, length, and angle of the leading edge structure item by item, the relationship between RCS value changes and the stealth performance of typical components of the leading edge is studied from the perspective of metal electromagnetic characteristics. Finally, the design rules of stealth structures for typical compon

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2

Wang, X., H. Yu, and D. Feng. "Pose estimation in runway end safety area using geometry structure features." Aeronautical Journal 120, no. 1226 (2016): 675–91. http://dx.doi.org/10.1017/aer.2016.16.

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ABSTRACTA novel image-based method is presented in this paper to estimate the poses of commercial aircrafts in a runway end safety area. Based on the fact that similar poses of an aircraft will have similar geometry structures, this method first extracts features to describe the structure of an aircraft's fuselage and aerofoil by RANdom Sample Consensus algorithm (RANSAC), and then uses the central moments to obtain the aircrafts’ pose information. Based on the proposed pose information, a two-step feature matching strategy is further designed to identify an aircraft's particular pose. In orde

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3

Shi, Qiongyan, and Jianghua Zhang. "Mechanical Structure Design of the Aircraft ASD Control Isolation Control." Journal of Applied Mathematics 2022 (November 16, 2022): 1–16. http://dx.doi.org/10.1155/2022/8306216.

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Aircraft control system is of key importance for flight attitude control of aircrafts. Its normal function directly determines whether the aircraft flies safely, flight delay, and dispatch reliability. Therefore, this paper designs the mechanical structure of the aircraft ASD control isolation control. Firstly, the mechanical control principle of the driving rod system is analyzed, and the isolation mechanism of pitch and roll control is designed; secondly, the control lines are classified, the transmission characteristic requirements of the aircraft control isolation system are given, the tra

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4

Yao, Man. "Water Impact Analysis for Aircraft over Sea." Applied Mechanics and Materials 341-342 (July 2013): 563–66. http://dx.doi.org/10.4028/www.scientific.net/amm.341-342.563.

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The modern aircrafts flying height is strictly limited by the conditions on the sea. Terrible conditions may lead overturning or dropping into the water to the aircraft. Whats more, the structure of the aircraft may be broken by water-impact force. The affection of the water impact must be considered to promise the safety of the aircraft. This paper focuses on the water impact to a typical symmetrical aircraft flying above sea. The water impact force related to the trajectory angle and equivalent pitch angle is researched based on the water impact force model of a two-dimensional wedge. In add

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Li, ying-lei, zong-jie Cao, and Zi-li Wang. "Topological Optimization of Aircraft Frame Structures with the Variable Density Method." MATEC Web of Conferences 198 (2018): 05008. http://dx.doi.org/10.1051/matecconf/201819805008.

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In this paper, a variable density topological optimization method is derived on the basis of Lagrange function, and the RAMP interpolation model is selected to optimize the frame structure of aircrafts with variable density method. For an example, the ordinary frame structure of the domestic planes is taken to illustrate validity of the presented method. The numerical model of the aircraft frames is obtained. The optimal design analysis of the model structural distribution and the weight loss requirement of the aircraft frame structures are realized. In conclusion, the structural distribution

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6

Ni, Junfei, and Jun Li. "Research on Modal Test Method for Civil Aircraft Structure." Journal of Physics: Conference Series 2658, no. 1 (2023): 012059. http://dx.doi.org/10.1088/1742-6596/2658/1/012059.

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Abstract In the process of civil aircraft development, it is of great significance to carry out a modal analysis of aircraft component structures and obtain modal parameters to verify whether the dynamic characteristics of aircraft structures meet the design requirements. This paper takes the structural modal of aircraft components as the research object and proposes the modal test method of aircraft structure, which provides effective modal test data support for the design and optimization of aircraft component structure.

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Broer, Agnes A. R., Rinze Benedictus, and Dimitrios Zarouchas. "The Need for Multi-Sensor Data Fusion in Structural Health Monitoring of Composite Aircraft Structures." Aerospace 9, no. 4 (2022): 183. http://dx.doi.org/10.3390/aerospace9040183.

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With the increased use of composites in aircraft, many new successful contributions to the advancement of the structural health monitoring (SHM) field for composite aerospace structures have been achieved. Yet its application is still not often seen in operational conditions in the aircraft industry, mostly due to a gap between research focus and application, which constraints the shift towards improved aircraft maintenance strategies such as condition-based maintenance (CBM). In this work, we identify and highlight two key facets involved in the maturing of the SHM field for composite aircraf

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8

Maricic, N. "Influence of structural backlash and friction in command system on the aircraft flutter." Theoretical and Applied Mechanics 31, no. 3-4 (2004): 317–44. http://dx.doi.org/10.2298/tam0404317m.

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Experience has shown that aircraft structures are generally affected by structural nonlinearities. The focus in this paper is concentrated on backlash and friction described in hysteresis loop of the classical aircraft command systems and their influence on flutter of aircraft. Based on AGARD No. 665 in paper is done nonlinear flutter velocity analysis in function of backlash and friction in the classical command system of aircraft. Unsteady aerodynamic forces are calculated based on well known Doublet- Lattice Method (DLM). Structural input data are taken from AGARD No. 665. Flutter eigenvalu

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Li, Jun, Wei Yang, and Yang Pei. "Vulnerability Assessment for Fire and Explosion Suppression Measures of Aircraft Fuel System." Advanced Materials Research 510 (April 2012): 64–69. http://dx.doi.org/10.4028/www.scientific.net/amr.510.64.

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Fuel system is the most vulnerable system on fixed wing aircraft. When penetrated by threat propagators, it is liable to be damaged by combustion and explosion. Thus, fire/explosion suppression for fuel system are important measures to improve the aircrafts survivability. In this paper, the whole aircraft vulnerability model which consists of aircraft configuration, structure, and systems is constructed by CATIA software, the basic steps for vulnerability quantitative computation are descried, and the computing formulas of three kill modes are presented. The vulnerability of one aircraft befor

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10

Purnomo, Muhamad Jalu. "ANALISIS STATIK KEKUATAN STRUKTUR FITTING PADA LANDING GEAR PADA PESAWAT N-219." Angkasa: Jurnal Ilmiah Bidang Teknologi 7, no. 2 (2017): 105. http://dx.doi.org/10.28989/angkasa.v7i2.154.

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Aircraft structures to be made stronger in order to be able to withstand the force received. The forces acting on the structure can cause deformation and result in structural failure. All components o f the structure o f the aircraft is an important part and it requires a good working resilience to maintain the security (safety). One important component of the aircraft that must be considered is the structure of the landing gear fittings. Fitting is contained in the structure that functions held their landing gear load received all the landing gear and as an intermediary for the landing gear a

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11

Lu, Fei, Tian Wang, and Zhaoning Zhang. "From Route Structure to Human Factors: A Comprehensive Study of Safe Separation on Intersecting Air Routes." Applied Sciences 14, no. 3 (2024): 1089. http://dx.doi.org/10.3390/app14031089.

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The assessment of collision risk at intersecting air routes is a crucial method for determining safe separation during aircraft route flights. This paper employs the Monte Carlo method to analyze the operational characteristics of aircraft on intersecting air routes in two stages, integrating the influence of the human-operated adjustment process on the distance between the two aircrafts, so as to propose a collision risk assessment model more aligned with the actual operational process. The initial stage considers the positional errors to establish a distance distribution function between tra

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Wang, Lin Lin, and Zhi Wen Wu. "Civil Unmanned Aircraft System Maintenance Structure." Advanced Materials Research 734-737 (August 2013): 2742–45. http://dx.doi.org/10.4028/www.scientific.net/amr.734-737.2742.

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Three maintenance structures of avionics were investigated in the article, including centralized intermediated repair concept, three-level maintenance structure, and the two-level maintenance structure. Both the advantages and disadvantages of these three maintenance structures were fully discussed, especially the potential in civil UAS maintenance. The investigation result shows that the two-level maintenance structure is the best choice for the civil unmanned aircraft maintenance at present. Key technologies of the two-level maintenance structure used for civil UAS were also discussed in thi

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13

Ren, Y., and J. Xiang. "Energy absorption structures design of civil aircraft to improve crashworthiness." Aeronautical Journal 118, no. 1202 (2014): 383–98. http://dx.doi.org/10.1017/s0001924000009180.

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AbstractTo improve the crashworthiness of civil aircraft, the design concept of energy absorption structure for civil aircraft is investigated. Two typical different design principles could be identified. The first category includes Helicopter and Light fixed-wing Aircraft (HLA), and Transport, Mid-size and Commuter type Aircraft (TMCA) are classified into the second group. Frame, strut and bottom structure are the three kinds of energy absorption structure for TMCA. The strut layout of conventional civil aircraft is studied and some energy absorption devices are adopted. High efficiency energ

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He, Y., C. Li, T. Zhang, et al. "Service fatigue life and service calendar life limits of aircraft structure: aircraft structural life envelope." Aeronautical Journal 120, no. 1233 (2016): 1746–62. http://dx.doi.org/10.1017/aer.2016.93.

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ABSTRACTThe service life of aircraft structure includes the fatigue life and calendar life. The Aircraft Structural Life Envelop (ASLE) is a safe and reliable life scope of aircraft structures in service. The specific steps to establish the ASLE are developed, and a residual life prediction method for aircraft structure under service environments is established by combining the ASLE with the Miner theory. Furthermore, a service life extension method of aircraft structure is proposed based on a scope extension of the ASLE, including methods based on reliability analysis and structural repair. F

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15

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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Kim, Min-Seong, Byung Hyuk Kwon, and Tae-Young Goo. "Comparisons between Mean and Turbulent Parameters of Aircraft-Based and Ship-Based Measurements in the Marine Atmospheric Boundary Layer." Atmosphere 12, no. 9 (2021): 1088. http://dx.doi.org/10.3390/atmos12091088.

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The Structure des Echanges Mer-Atmosphère, Propriétés Océaniques/ Recherche Expérimentale (SEMAPHORE) experiment was conducted over the oceanic Azores current located in the Azores Basin. The evolution of the marine atmospheric boundary layer (MABL) was studied based on the evaluation of mean and turbulent data using in situ measurements by a ship and two aircrafts. The sea surface temperature (SST) field was characterized by a gradient of approximately 1 °C/100 km. The SST measured by aircraft decreased at a ratio of 0.25 °C/100 m of altitude due to the divergence of the infrared radiation fl

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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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Zhang, Li Jun, Xiao Jiao Chen, Jia Wang, and Min Li. "Vibro-Acoustic Coupling Analysis of High Velocity Aircraft Based on Hybrid Acoustic Simulation Method." Applied Mechanics and Materials 530-531 (February 2014): 967–70. http://dx.doi.org/10.4028/www.scientific.net/amm.530-531.967.

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High-speed aircraft is in service condition of high temperature, high pressure and strong noise during flight. Strong noise will damage structures and equipments of an aircraft, and the existence of high temperature and high pressure will greatly increase the damage degree. Therefore, research on aircraft structure characteristic and surface acoustic characteristic is very significant. The hybrid method of CFD and acoustic solver combination method can accurately obtain aerodynamic noise load on the aircraft structure surface in a high velocity environment. The hybrid method can make acoustic

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Reddy, D. Ramana, M. V. Aditya Nag, and M. S. N. Gupta. "Stress and Deformation Analysis of Aircraft's Fuel Tank under Different Inertia Load Cases in Addition to a Static Test Pressure Using FEA." Advanced Materials Research 1115 (July 2015): 527–30. http://dx.doi.org/10.4028/www.scientific.net/amr.1115.527.

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In the modern era the aerospace technology plays a very significant role in the development of the mankind. The evolution of the light weight aircraft has a special focus in the present industrial trends. Several research organizations are in the process of developing Light Weight Aircraft, which is ideally suited for civil transport, aerial survey, training etc. This Light Weight Aircrafts are to be designed accordance to Federal Aviation Regulations part 23 (FAR-23). This paper deals with the analysis of the Aircraft's Fuel Tank under variable conditions. The analysis of aircraft fuel tank i

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Kalinowski, Miłosz. "Aero-Structural Optimization of Joined-Wing Aircraft." Transactions on Aerospace Research 2017, no. 4 (2017): 48–63. http://dx.doi.org/10.2478/tar-2017-0028.

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Abstract Joined-wing aircraft due to its energy characteristics is a suitable configuration for electric aircraft when designed properly. However, because of the specific for this aircraft phenomenons (e.g. static indeterminacy of structure, aerodynamic interference of lifting surfaces) it demands more complicated methods to model its behavior than a traditional aircraft configurations. For these reasons the aero-structural optimization process is proposed for joined-wing aircrafts that is suitable for preliminary design. The process is a global search, modular algorithm based on automatic geo

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Zhang, X., B. Xiong, and G. Kuang. "AIRCRAFT SEGMENTATION IN SAR IMAGES BASED ON IMPROVED ACTIVE SHAPE MODEL." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-3 (April 30, 2018): 2331–35. http://dx.doi.org/10.5194/isprs-archives-xlii-3-2331-2018.

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In SAR image interpretation, aircrafts are the important targets arousing much attention. However, it is far from easy to segment an aircraft from the background completely and precisely in SAR images. Because of the complex structure, different kinds of electromagnetic scattering take place on the aircraft surfaces. As a result, aircraft targets usually appear to be inhomogeneous and disconnected. It is a good idea to extract an aircraft target by the active shape model (ASM), since combination of the geometric information controls variations of the shape during the contour evolution. However

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Teng, Xichao, Qifeng Yu, Jing Luo, Xiaohu Zhang, and Gang Wang. "Pose Estimation for Straight Wing Aircraft Based on Consistent Line Clustering and Planes Intersection." Sensors 19, no. 2 (2019): 342. http://dx.doi.org/10.3390/s19020342.

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Aircraft pose estimation is a necessary technology in aerospace applications, and accurate pose parameters are the foundation for many aerospace tasks. In this paper, we propose a novel pose estimation method for straight wing aircraft without relying on 3D models or other datasets, and two widely separated cameras are used to acquire the pose information. Because of the large baseline and long-distance imaging, feature point matching is difficult and inaccurate in this configuration. In our method, line features are extracted to describe the structure of straight wing aircraft in images, and

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D., Srinivasa Rao, K.Venkatesh, Krishna Veni M.N.V., and Amareswari Reddy M. "Optimization of a Simple Aircraft Wing by Weight Minimization using ANSYS." Journal of Industrial Mechanics 4, no. 2 (2019): 34–40. https://doi.org/10.5281/zenodo.3361508.

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In the current generation, aircrafts became the fastest mode of transportation for goods and passengers. In such a situation, sophistication of the airplanes is also moving at a rapid pace. The main reason for the flight of airplane is the lift force over the wings. The better the wings are, the better the lift will be. The improvement in the flight of aircraft and efficiency of aircraft can be done by proper design of these wings. This can be done by either optimization of wing structure which reduces the drag force over the aircraft or by optimizing the weight of the wings which enable the a

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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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Shen, Wei Guo, Jun Wei Han, and Xin Tong Zhao. "Equipment/System Safety Design Process in Civil Aircraft Considering Structure-Support Requirements." Advanced Materials Research 712-715 (June 2013): 2076–79. http://dx.doi.org/10.4028/www.scientific.net/amr.712-715.2076.

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For safety-designing an equipment/system in civil aircraft, ARP4761 & SAE ARP 4754 is important common standard. But in these standards there has no clear description aircraft structures effect on the equipment/system. In this present paper, aircraft structures effect on design an equipment/system is considered by methods of FHA-FMEA-FTA-SSA quantitatively by conservative assumption. A flow chart of requirement considering structure-support effect is developed.

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Wang, Yitao, Teng Zhang, Yuting He, Jiyuan Ye, Hanzhe Zhang, and Xianghong Fan. "Analysis of Damage of Typical Composite/Metal Connecting Structure in Aircraft under the Influences of High-Velocity Fragments." Applied Sciences 12, no. 18 (2022): 9268. http://dx.doi.org/10.3390/app12189268.

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A two-stage light gas gun was used to conduct a high-velocity impact test on the aircraft’s typical composite/metal connecting structure (CFRP/AL). The battle damage simulations used for the CFRP/AL connecting structure were carried out under different intersection conditions. Then, the damage morphology and mechanism of high-velocity prefabricated spherical fragments on typical structures, the dynamic process of hyper-velocity impact, and the formation of debris clouds on the secondary damage morphology of different component structures were investigated. Next, based on the X-ray computerized

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Кушнір, Д. І., та Д. І. Конотоп. "АВТОМАТИЗОВАНЕ ПРОЄКТУВАННЯ ЛОНЖЕРОНУ КРИЛА БЕЗПІЛОТНОГО ПОВІТРЯНОГО СУДНА". Open Information and Computer Integrated Technologies, № 98 (15 квітня 2024): 21–35. http://dx.doi.org/10.32620/oikit.2023.98.02.

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One of the most crucial objective in designing aircraft structures is to ensure their strength while meeting the requirement for minimal weight. In operation, the structure must withstand loads without failure, as well as be designed with the lowest possible weight and, in most cases, volume.The determined geometric model of the structure based on the minimum weight criteria, reduces the overall weight of the aircraft which leads to: reducing the power requirements of the engine, and thus the cost of the aircraft; decreasing fuel consumption, making the aircraft cheaper in operation.The weight

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Hartini, Dwi, Buyung Junaidin, and Habibi Habibi. "STRENGTH ANALYSIS OF CARGO-X UAV WING STRUCTURE USING SANDWICH COMPOSITE MATERIALS." Vortex 3, no. 1 (2022): 1. http://dx.doi.org/10.28989/vortex.v3i1.1153.

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The Cargo-X UAV aircraft is a UAV aircraft designed to carry medicines, packages and blood bags in areas that require fast and efficient handling. One of the important components of the Cargo-X UAV aircraft is the wing, so the strength of the wing structure must be seriously considered to ensure safety during flight under unexpected conditions. The purpose of this study was to analyze the wing structure of the UAV Cargo-X aircraft made of sandwich composite material to determine the level of safety of the wing structure. The loading of the wing structure uses the load due to the lift. The wing

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Фомичов, Петро Олександрович, Тетяна Сергіївна Бойко та Олександр Олександрович Севостьянов. "Метод расчета усталостного повреждения регулярных зон крыла самолета при случайном нагружении на этапах типового полета". Aerospace technic and technology, № 3 (27 травня 2021): 13–23. http://dx.doi.org/10.32620/aktt.2021.3.02.

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In accordance with the airworthiness standards, the aircraft structure must be operationally survivable, it means that structure must be able to remain efficiency in the presence of admissible damage. But, accumulating above than a certain level, damages cause fatigue failure of the structure, in the form of micro- and submicrocracks, thus reducing its strength characteristics. Currently, several approaches have been formed to ensure the safety of an aircraft structures in terms of strength. One of them is ensuring a safe resource (safe durability). This principle implies that during the speci

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Zhang, Jia Rui, Zhen Yu Feng, and Tian Chun Zou. "Certification for Effect of Environment on Composite Properties." Advanced Materials Research 284-286 (July 2011): 396–400. http://dx.doi.org/10.4028/www.scientific.net/amr.284-286.396.

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The environment which can have a great effect on the composite aircraft structure performances must be considered during the design and certification process. In this paper, the extreme temperature and humidity span of the worst environment conditions in aircraft structure design and certification are investigated, and some test methods involving environment influences are also discussed. The studying results can be used in design and certification for environment influences of composite aircraft structures.

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Niepokólczycki, Antoni, and Andrzej Szot. "Application of Finite Element Method for Determining Loads for the New Method of Acoustic Fatigue Testing of Aircraft Structures." Fatigue of Aircraft Structures 2009, no. 1 (2009): 140–49. http://dx.doi.org/10.2478/v10164-010-0013-y.

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Application of Finite Element Method for Determining Loads for the New Method of Acoustic Fatigue Testing of Aircraft Structures For aircraft structures the failures due to acoustic fatigue are very important, particularly for new supersonic or short take-off aircraft. The majority of acoustic fatigue life test methods are based on the reproduction of noise acting on the structure - in reverberation chambers or progressive wave tubes. The method described in this paper is based on the reproduction of dynamic response of the structure subjected to random acoustic loading.

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Lv, Cheng, Kejie Wang, Xiang Zhao, and Fenghui Wang. "Damage-Accumulation-Induced Crack Propagation and Fatigue Life Analysis of a Porous LY12 Aluminum Alloy Plate." Materials 17, no. 1 (2023): 192. http://dx.doi.org/10.3390/ma17010192.

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Rivets are usually used to connect the skin of an aircraft with joints such as frames and stringers, so the skin of the connection part is a porous structure. During the service of the aircraft, cracks appear in some difficult-to-detect parts of the skin porous structure, which causes great difficulties in the service life prediction and health monitoring of the aircraft. In this paper, a secondary development subroutine in PYTHON based on ABAQUS-XFEM is compiled to analyze the cracks that are difficult to monitor in the porous structure of aircraft skin joints. The program can automatically a

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IMAMURA, Tsugio. "Light metal for aircraft structure." Journal of Japan Institute of Light Metals 41, no. 9 (1991): 623–34. http://dx.doi.org/10.2464/jilm.41.623.

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YOSHIDA, Osamu. "Bonded structure application for aircraft." Journal of the Japan Welding Society 60, no. 3 (1991): 212–18. http://dx.doi.org/10.2207/qjjws1943.60.212.

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Chernov, Andrey, Ivan Kondakov, and Yury Mirgorodskiy. "Experimental Study of Impact-Protective Elements for Unidirectional Ribs of Lattice Composite Aircraft Structures." MATEC Web of Conferences 304 (2019): 01016. http://dx.doi.org/10.1051/matecconf/201930401016.

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Lattice structures based on unidirectional composite ribs is currently one of the most promising directions of research aiming to create lightweight and reliable structure of future aircrafts [1]. Hybrid structure concepts based on lattice layouts have been developed for a number of conventional and non-conventional civil aircraft configurations, giving up to 15-20% weight saving as compared to conventional composite structures based on laminated skin and stiffeners [2]. One of the most critical problems of load-bearing lattice composite structures is very high sensitivity to impact loads, whi

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HE, Erming, Wei LI, Xiaofeng XUE, Zhiyan JIA, and Yunwen FENG. "Damage tolerance analysis of wading structures of amphibious aircraft based on Franc3D." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 40, no. 3 (2022): 476–84. http://dx.doi.org/10.1051/jnwpu/20224030476.

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Aiming at the combined action effect of the corrosive environment of amphibious aircraft wading structures and random loads including water surface take-off and landing impact, based on the standard load spectrum TWIST of transport aircraft, considering the load level and frequency corresponding to the hydrodynamic load, the simulated random load spectrum of the wading structure was first compiled; the Willenborg/Chang high-load hysteresis model was used to consider the hysteretic effect of hydrodynamic high-amplitude overload on structural crack propagation, and an engineering method for dama

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Sutiawan, Sutiawan, Dena Hendriana, Hanny J. Berchmans, Henry Nasution, and Gembong Baskoro. "Design and Analysis of Warning System for Aircraft Wingtip Proximity to Hangar Column using Ultrasonic Sensor." Proceedings of The Conference on Management and Engineering in Industry 2, no. 1 (2020): 7–10. http://dx.doi.org/10.33555/cmei.v2i1.33.

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Aircraft maintenance is using very large hangar as a place to work on the aircrafts and the hangar can fit several aircrafts at the same time. The aircrafts are moved using tow cars in and out of the hangar. The hangar is so big that it requires columns for its structure and these columns present risk to the aircrafts for having wingtip collitions during towing in and out of the hangar. In this study, warning system for aircraft wingtip proximity to the hangar columns is designed. This warning system is using ultrasonic sensors attached to the columns and controlled by Arduino micro processor

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Jaffar Syed Mohamed Ali, Wan Muhammad Hafizuddin W. Embong, and Abdul Aabid. "Effect of Cut-Out Shape on the Stresses in Aircraft Wing Ribs under Aerodynamic Load." CFD Letters 13, no. 11 (2021): 87–94. http://dx.doi.org/10.37934/cfdl.13.11.8794.

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Ribs in aircraft wings maintain the airfoil shape of the wing under aerodynamic loads and also support the resulting bending and shear loads that act on the wing. Aircrafts are designed for least weight and hence the wings are made of hollow torsion box and the ribs are designed with cut-outs to reduce the weight of the aircraft structure. These cut-outs on the ribs will lead to higher stresses and stress concentration that can lead to failure of the aircraft structures. The stresses depend on the shape of the cut-outs in the ribs and thus in the present work, the commercial software ANSYS was

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M., Dyuthi Priya, R. Vijaya Prakash Dr., and Purna Chandra Sekhar B. "Modeling and Structural Analysis of Aircraft Wing with Different Materials Using FEM." Advancement in Mechanical Engineering and Technology 5, no. 3 (2022): 1–14. https://doi.org/10.5281/zenodo.7439946.

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<em>Aircraft Wing structure consists of skin, ribs and spar sections. The spar carries flight loads and the weight of the wings while on the ground. Other structural and forming members such as ribs are attached to the spars, with stressed skin. The wings are the most important lift producing part of the aircraft. The design of wings may vary according to the type of aircraft and its purpose. Experimental testing of wing structure is more expensive and time consuming process. In this project detailed design of aircraft wing structure made by using CATIA V5 R20. Then structural analysis of the

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Reymer, Piotr, Wojciech Zieliński, and Artur Kurnyta. "Influence of source data on fatigue estimation of a fighter aircraft." Journal of KONBiN 48, no. 1 (2018): 301–22. http://dx.doi.org/10.2478/jok-2018-0057.

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Abstract Aircraft structures during operation are exposed to fluctuating loads caused both by aerodynamic and inertial loads. This fluctuation leads to the creation of fatigue cycles, which gradually diminish the residual durability of the structure. During the design process, the flight envelope is defined as well as the design load spectrum, which then defines the durability of the structure (often expressed in means of flight hours). However, during the operation of an individual aircraft the actual load cycles can be significantly lower or higher than the designed; therefore, load monitori

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Li, Jinxian. "Aerodynamics-based forward-swept wing structure optimization." Applied and Computational Engineering 10, no. 1 (2023): 297–306. http://dx.doi.org/10.54254/2755-2721/10/20230134.

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This paper reviews and evaluates the most recent studies on forward-swept wing technology. A number of experimental plans and applications for forward-swept wing aircraft have been produced as a result of the study of forward-swept wings, the investigation of aerodynamic circumstances, and the creation of related designs. The related theories and exposed problems of the forward-swept wing aircraft, such as the problem of aeroelastic divergence, structural strength, and the descent of transonic flight state, are gradually solved. It will be demonstrated that forward-swept wing aircraft have out

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Wang, Wenbo, and Guoqing Yuan. "Review on the Structure Design of Morphing Winglets." Aerospace 11, no. 12 (2024): 1004. https://doi.org/10.3390/aerospace11121004.

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Winglets have a significant impact on the aerodynamic performance of aircraft. When aircraft are in different flight phases such as takeoff, climb, cruise, descent, and landing, traditional fixed winglets often cannot provide optimal performance gains. If winglets that can morph according to different flight conditions are employed, it is expected that the aircraft’s lift-to-drag ratio and control performance can be optimized throughout the entire flight process. This paper reviews the current research status, from theoretical studies on the performance gains of morphing winglets and design st

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Vaivads, Andris, Jevgēnijs Tereščenko, and Vladimirs Šestakovs. "A Model of Interconnection Between Aircraft Equipment Failures and Aircraft “States” in Flight." Transport and Aerospace Engineering 6, no. 1 (2018): 30–36. http://dx.doi.org/10.2478/tae-2018-0004.

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Abstract The article presents a semiotic model of “aircraft conditions” in flight and multilevel structures of an aircraft. The hierarchical structure of abstract models is divided into blocks and levels that make them more compact by applying a mathematical apparatus corresponding to the goals sated. The above models were tested on the basis of statistical data on TU-154 aircraft failures for 10 years. Various aircraft functional system failures in flight were examined. The state of the aircraft is identified by normative indicators recorded in the “Aircraft Technical Operation Manual”.

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Yuan, Xinyang, Daoyong Fu, and Songchen Han. "LRF-SRNet: Large-Scale Super-Resolution Network for Estimating Aircraft Pose on the Airport Surface." Sensors 23, no. 3 (2023): 1248. http://dx.doi.org/10.3390/s23031248.

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The introduction of various deep neural network architectures has greatly advanced aircraft pose estimation using high-resolution images. However, realistic airport surface monitors typically take low-resolution (LR) images, and the results of the aircraft pose estimation are far from being accurate enough to be considered acceptable because of long-range capture. To fill this gap, we propose a brand-new, end-to-end low-resolution aircraft pose estimate network (LRF-SRNet) to address the problem of estimating the pose of poor-quality airport surface surveillance aircraft images. The method suc

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Gębura, Andrzej, Andrzej Szelmanowski, Wojciech Zieliński, and Andrzej DŁUGOŁĘCKI. "Development of airfield electrical power systems for military aircrafts." Journal of Konbin 54, no. 3 (2024): 75–98. http://dx.doi.org/10.5604/01.3001.0054.7682.

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The article presents selected problems in the operation of airport power supply systems (LZE), resulting from the growing needs in terms of increasing power and ensuring the appropriate quality of electrical energy supplied to aircraft installations and receivers. The main stages of development of airport power supply systems for aircraft are reviewed. The basic technical structures of airport power supplies for aircraft were presented, divided into two groups: stationary (without the possibility of moving and with the possibility of moving) and mobile (placed on wheels that are an integral pa

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BOIKO, Sergey, Alona HEBDA, Yurii STUSHCHANSKY, Serhiy GOLOVANOV, and Myhailo RUZHUK. "APPROACH TO THE IMPROVEMENT OF THE CONTROL SYSTEM OF THE ELECTRIC POWER PLANT OF THE AIRCRAFT." Herald of Khmelnytskyi National University. Technical sciences 315, no. 6 (2022): 20–24. http://dx.doi.org/10.31891/2307-5732-2022-315-6(2)-20-24.

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The paper proposes an approach to improving the adaptive system of aircraft with an electric propulsion system. Modern aircraft are inextricably linked with electronics that ensure the functioning of the entire air transport system. Modern aircraft avionics is a complex of hardware and software that is part of the automatic control system of the aircraft and functionally combines the glider with the drive of the executive body. One of the main functions of modern avionics is the automation of aircraft control processes, which aims to ensure the proper execution of a safe flight with the smalle

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Birbraer, Adolf N., and George D. Kostrov. "Probability of a High-Speed Military Aircraft Falling at a Nuclear Power Plant and Setting of Design Loads on Building Structures." Earthquake Engineering. Construction Safety, no. 6 (December 25, 2020): 10–26. http://dx.doi.org/10.37153/2618-9283-2020-6-10-26.

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The article is devoted to issues related to the probabilistic justification of the safety of nuclear power plants (NPP) when a high-speed military aircraft falls. The random parameters are the recurrence of falls and the direction of the aircraft's trajectory. The conservative value of the recurrence of falls, given in the IAEA documents, was used, which ensures a high degree of NPP safety. The aircraft approach is assumed to be equally probable from either side. The trajectory slope is specified taking into account the IAEA documents and statistics of aviation accidents.  The airc

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Sleesongsom, Suwin, Sumit Kumar, and Sujin Bureerat. "Multi-Objective Reliability-Based Partial Topology Optimization of a Composite Aircraft Wing." Symmetry 15, no. 2 (2023): 305. http://dx.doi.org/10.3390/sym15020305.

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Reliability-based partial topology optimization (RBPTO) is a new approach for aircraft structural design; however, it brings computational complexity and makes aeroelasticity analysis quite challenging. Therefore, the present study proposed the multi-objective reliability-based partial topology optimization of a composite aircraft wing using a fuzzy-based metaheuristic (MRBPTOFBMH) approach. The objective is to obtain an optimal layout including partial topology and sizing of the aircraft wing structure. Here, an optimal aeroelastic structure is designed by taking into account the uncertain na

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Wu, Yang, Xudong Qiu, Chunyu Bai, and Hu Liu. "Connection strength analysis for composite fuselage gate structures of civil aircraft." Journal of Physics: Conference Series 2730, no. 1 (2024): 012003. http://dx.doi.org/10.1088/1742-6596/2730/1/012003.

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Abstract Civil aircraft boarding gate is an important channel for passengers to enter and exit the aircraft, and is also an important part of the aircraft structure, with the function of maintaining cockpit pressure. Traditional boarding doors are made of metal, and with the large number of composite materials used in the bearing structure of civil aircraft, composite boarding doors are also used in new civil aircraft. The strength of the connection inside the new composite boarding gate is related to the safety of passengers and crew. This paper focuses on the connection problem of the intern

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Özen, Enes, and Tugrul Oktay. "Aircraft Designed for Cargo Transportation and Investigation of its Benefits." ENERGY, ENVIRONMENT & STORAGE 4, no. 2 (2024): 21–26. http://dx.doi.org/10.52924/zqjp9091.

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In this study, an Octorotor UAV capable of carrying 10 desi/2 kg cargo was designed. It is an eight-rotor rotary wing aircraft and its body consists of eight arms connected to each other by two moving mechanisms. When requested in emergency situations, the fastest intervention can be provided by aircrafts. The auxiliary battery and generator system carried by the aircraft is to provide enough energy to reach the nearest electric charging station for the stranded vehicles. In cases such as disasters, the rapid delivery of health supplies can also be provided by this method. The aircraft designe

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