Journal articles: 'Aircraft structure'

1

Wang, X., H. Yu, and D. Feng. "Pose estimation in runway end safety area using geometry structure features." Aeronautical Journal 120, no. 1226 (April 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 order to validate the accuracy of the pose estimation and the effectiveness of the proposed algorithm, we construct a pose database of two common aircrafts in Asia. The experiments show that the designed low-dimension features can accurately capture the aircraft's pose information and the proposed algorithm can achieve satisfied matching accuracy.

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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 addition, concerning with the limitation of the aircrafts overload, the water-contact condition is proposed to avert attitude overturning and structure broken of the aircraft.

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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 law of the topology optimization is summarized according to the topology optimization structures.

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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 this article. The advisements were given in these discussions.

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5

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 eigenvalues are obtained by modified k-method. The flutter model of nonlinear aircraft structure is developed on base of harmonic linearization. The aim of paper is to achieve useful and relatively reliable tool for critical observations on different recommendations given in the various airworthiness regulations for nonlinear characteristics of hysteresis loops in the classical command systems of aircrafts. .

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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 before and after adopting fire/explosion suppression measures are analyzed. The results show that fire/explosion suppression measures can effectively decrease the aircrafts vulnerable area and kill probability.

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7

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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9

He, Y., C. Li, T. Zhang, J. Liu, C. Gao, B. Hou, and L. Wu. "Service fatigue life and service calendar life limits of aircraft structure: aircraft structural life envelope." Aeronautical Journal 120, no. 1233 (September 19, 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. Finally, an application example of the ASLE is presented.

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Purnomo, Muhamad Jalu. "ANALISIS STATIK KEKUATAN STRUKTUR FITTING PADA LANDING GEAR PADA PESAWAT N-219." Angkasa: Jurnal Ilmiah Bidang Teknologi 7, no. 2 (September 13, 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 and airframe structure of the aircraft. Because Landing Gear is one important component in the structure of the aircraft. Strength landing gear fittings will be calculated at the time of landing, the burden derived from the speed of the aircraft landing and aircraft load.

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Ren, Y., and J. Xiang. "Energy absorption structures design of civil aircraft to improve crashworthiness." Aeronautical Journal 118, no. 1202 (April 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 energy absorption structures such as the foam and sine-wave beam are employed as the bottom structure for both of HLA and LMCA. The finite element method is used to analyse and design energy absorption structure in aircraft crashworthiness problem. Results show that the crashworthiness of civil aircraft could be largely improved by using proper strut layout and excellent energy absorption device. The stiffness combination of frame and strut should be considered to get better global aircraft deformation. Supporting platform and failure model are the two core problems of bottom energy absorption structure design. Foam and sine-wave beam under the lifted frame could improve the crashworthiness of civil aircraft.

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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 (August 24, 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 flux from the surface. With the exception of temperature, the mean parameters measured by the two aircrafts were in good agreement with each other. The sensible heat flux was more dispersed than the latent heat flux according to the comparisons between aircraft and aircraft, and aircraft and ship. This study demonstrates the feasibility of using two aircraft to describe the MABL and surface flux with confidence.

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13

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 (May 6, 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 structural integrity. With the current problem of not having the structural limitation on corrosion-damaged structure, the RMAF has embarked on its fatigue testing method. Finite Element (FE) studies and flight tests were conducted, and the outcome is summarized. The conclusion is that the longeron tested on the aircraft can withstand the operational load, and its yield strength is below the ultimate yield strength of the material. These research outcomes will also enhance the ASIP for other aircraft platforms in the RMAF fleet for its structure life assessment or service life extension program.

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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 is carried out for different inertia load cases in addition to a test pressure of 3.5psi (24KPa), to validate whether the structure is safe or not. The size of the fuel tank has been taken as per the FAR-23 guidelines. The Finite Element Analysis is carried out to arrive at stresses and displacements in critical components using the Ansys software. The maximum shear stresses included are observed to be much less than the Yield strength of materials.

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15

Донець, Олександр Дмитрович, Олександр Іванович Семенець, Євген Тимофійович Василевський, Олександр Григорович Гребеніков, and Андрій Михайлович Гуменний. "КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ РІШЕННЯ ЗАБЕЗПЕЧЕННЯ СТАТИЧНОЇ МІЦНОСТІ ТА РЕСУРСУ РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ." Open Information and Computer Integrated Technologies, no. 82 (December 19, 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, fuel weight, cargo weight and various possible combinations of their distribution, taking into account the following: dynamic load and elastic characteristics of the aircraft’s design flying in disturbed air and while landing; dynamic load of the control system structure during maneuvering and under wind gusts; failures and malfunctions of systems that directly affect the strength characteristics. The results of flight tests showed that the An-148 100 / An-158 typical structure under the terms of static strength does not have features and parts that create emergency conditions or are unreliable, and confirmed the correctness of the choice of the established operational limitations presented for inclusion in the Flight Operation Manual. Conditions for operation of the An-148-100 / An-158 family during a design life of 30 years were determined on the basis of a comparative analysis of the corrosion resistance of the aircraft structures, whose service life exceeds 30 years. An-148-100 / An-158 airplanes are designed and manufactured in all-climate version in compliance with all the requirements for anti-corrosion protection. The aircraft used design and technological solutions to protect against loss of strength during operation from weathering, corrosion and abrasion, which allowed to state that the main power elements of the An-148-100 / An-158 aircraft typical structure are protected from reduction or loss of strength in operation for any reason, including weathering, corrosion and abrasion, as well as adequate ventilation and drainage. The provision of static strength and lifetime of regional passenger aircraft is confirmed by static, fatigue and flight tests of airplanes, reflected in technical reports with regard to strength, lifetime and service life of the An-148-100 / An-158 aircraft.

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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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17

Kalinowski, Miłosz. "Aero-Structural Optimization of Joined-Wing Aircraft." Transactions on Aerospace Research 2017, no. 4 (December 1, 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 geometry generator, FEM solver and aerodynamic panel method. The range of aircraft was assumed as an objective function. The algorithm was successfully tested on UAV aircraft. The improvement of 19% of total aircraft range is achieved in comparison to baseline aircraft. Time of evaluation of this global search algorithm is similar to the time characteristic for local optimization methods. It allows to reduce the time and costs of preliminary design of joined-wing.

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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, linear dimensionality reduction, used in classic ACM, makes the model rigid. It brings much trouble to segment different types of aircrafts. Aiming at this problem, an improved ACM based on ISOMAP is proposed in this paper. ISOMAP algorithm is used to extract the shape information of the training set and make the model flexible enough to deal with different aircrafts. The experiments based on real SAR data shows that the proposed method achieves obvious improvement in accuracy.

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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 and vibration analysis for aircraft structure, and get influence of noise load on it. The simulated results show that the presence of high temperature and high pressure can make the natural frequency of typical components and whole machine model reduction, and the acoustic load on the aircraft structure model surface is larger at low frequency, smaller at high frequency.

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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, which is even more crucial than for the laminated composite structures. At the same time, topology of lattice grid makes it possible to create reliable protective system for the ribs, which can be effective in terms of weight expenses.

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Lopez, Manuel J., and Luis Garcia. "Variable Structure H∞ Controller for Aircraft." International Journal of Scientific Engineering and Technology 6, no. 5 (2017): 155. http://dx.doi.org/10.5958/2277-1581.2017.00008.0.

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Schmidt, R. K. "Monitoring of aircraft landing gear structure." Aeronautical Journal 112, no. 1131 (May 2008): 275–78. http://dx.doi.org/10.1017/s0001924000002220.

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Abstract Landing gear structure is developed predominantly using safe life design criteria. Health monitoring and structural prognosis techniques for landing gear cannot focus on crack detection; techniques for determining input loads and calculating damage or methods for directly measuring material damage must be employed. This paper will discuss Messier-Dowty’s research into structural monitoring over the past several years. Principally, direct damage detection systems and load monitoring systems will be discussed.

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Kamiyama, Takayuki, and Yujiro Yoshida. "Reliability of adhesive for aircraft structure." Kobunshi 35, no. 7 (1986): 666–69. http://dx.doi.org/10.1295/kobunshi.35.666.

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NAKAJIMA, Masanori. "Manufacturing Technology of Aircraft Airframe Structure." Journal of the Japan Society for Precision Engineering 75, no. 8 (2009): 941–44. http://dx.doi.org/10.2493/jjspe.75.941.

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Grant, Carroll. "Automated processes for composite aircraft structure." Industrial Robot: An International Journal 33, no. 2 (March 2006): 117–21. http://dx.doi.org/10.1108/01439910610651428.

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Armstrong, Keith. "Civil Aircraft Composite Structure Repair Technology." Materials Technology 14, no. 4 (January 1999): 198–210. http://dx.doi.org/10.1080/10667857.1999.11752840.

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CISE. "Acoustic emission tracks aircraft structure fatigue." International Journal of Fatigue 9, no. 4 (October 1987): 247. http://dx.doi.org/10.1016/0142-1123(87)90031-4.

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Pratama, Fandi Syafri. "STRUCTURE POWER AIRCRAFT FUSELAGE 5774 TRAINER." Vortex 2, no. 2 (June 30, 2021): 82. http://dx.doi.org/10.28989/vortex.v2i2.1010.

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The analysis process using software aims to determine whether an object or material is suitable for use or not before carrying out the manufacturing process. To find out whether the material is strong or not when applied to the aircraft, an analysis is carried out using the ABAQUS CAE 6.14 software. This software will show the stress value that occurs in the sandwich composite structure when it receives the load experienced by the aircraft.

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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 (January 16, 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 pose estimation is performed based on the common geometry constraints of straight wing aircraft. The spatial and length consistency of the line features is used to exclude irrelevant line segments belonging to the background or other parts of the aircraft, and density-based parallel line clustering is utilized to extract the aircraft’s main structure. After identifying the orientation of the fuselage and wings in images, planes intersection is used to estimate the 3D localization and attitude of the aircraft. Experimental results show that our method estimates the aircraft pose accurately and robustly.

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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 (November 23, 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 and wirelessly connected as Internet of Things system to warn the driver of the tow car. The ultrasonic sensors are placed in the columns based on dimension and elevation of 2 different most common aircraft wingtips to get effective column warning system. The speed of tow car affects the driver time to response the warning and based on calculations and experiments, the tow car driver should have enough time to respond the warning system.

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Фомичов, Петро Олександрович, Тетяна Сергіївна Бойко, and Олександр Олександрович Севостьянов. "Метод расчета усталостного повреждения регулярных зон крыла самолета при случайном нагружении на этапах типового полета." Aerospace technic and technology, no. 3 (May 27, 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 specified service life of the product, no damage will occur in it, reducing the strength below the permissible level. The aircraft resource is limited “from above” by the durability of the regular zones of airframe. Therefore, predicting the durability of an aircraft wing structure at the design stage is a fundamental engineering problem to ensure its safety and economic efficiency. At the same time, the first step in dealing with aircraft fatigue damage at the design stage is the collection and assessment of the operational loads of the analog aircraft. However, at the design stage of a new aircraft model, obtaining such data is not always possible. Therefore, the purpose of this article is to develop a method for calculating fatigue damage at the stage of cracking and assessing the durability of regular zones of a transport aircraft wing, taking into account the conditions of its operation. The tasks to be solved are: to isolate the factors that determine the durability of the aircraft at flying in turbulent air; to take into account the asymmetry of loads and accumulated damage that occurs at each stage during the entire flight of the aircraft; to determine the aircraft's resource depending on the profile of a typical flight. The method is based on a standardized atmospheric turbulence model, typical flight profiles, fatigue characteristics of materials, the hypothesis of linear summation of damages and calculation based on nominal stresses. As result, comparison between the calculated integral repeatability of overloads and equivalent bending moments with the results of processing flight test data showed good agreements. Conclusions. The scientific novelty of the work lies in the fact that a method for calculating the fatigue damage of the regular wing zones, taking into account the expected flight profile of the aircraft was developed. This means that the proposed method makes it possible to carry out a preliminary assessment of the resource when designing an airplane without using data on the operational loads of an analogue airplane, and also estimate the residual resource of the airplane during its operation.

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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 (June 6, 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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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 (July 26, 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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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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Li, Yadan, Zhenqi Han, Haoyu Xu, Lizhuang Liu, Xiaoqiang Li, and Keke Zhang. "YOLOv3-Lite: A Lightweight Crack Detection Network for Aircraft Structure Based on Depthwise Separable Convolutions." Applied Sciences 9, no. 18 (September 10, 2019): 3781. http://dx.doi.org/10.3390/app9183781.

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Due to the high proportion of aircraft faults caused by cracks in aircraft structures, crack inspection in aircraft structures has long played an important role in the aviation industry. The existing approaches, however, are time-consuming or have poor accuracy, given the complex background of aircraft structure images. In order to solve these problems, we propose the YOLOv3-Lite method, which combines depthwise separable convolution, feature pyramids, and YOLOv3. Depthwise separable convolution is employed to design the backbone network for reducing parameters and for extracting crack features effectively. Then, the feature pyramid joins together low-resolution, semantically strong features at a high-resolution for obtaining rich semantics. Finally, YOLOv3 is used for the bounding box regression. YOLOv3-Lite is a fast and accurate crack detection method, which can be used on aircraft structure such as fuselage or engine blades. The result shows that, with almost no loss of detection accuracy, the speed of YOLOv3-Lite is 50% more than that of YOLOv3. It can be concluded that YOLOv3-Lite can reach state-of-the-art performance.

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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 aircraft impact load is applied to one of the structures, therefore the impact probability must be determined independently for each of them. It is proportional to the equivalent area of the building structure, depending on its size, shape, position in space and in relation to other structures. Expressions are given for the equivalent areas of structures of various shapes, typical for NPP. It is shown that if the aircraft crash is unintentional (accident), then with the usual dimensions of structures, the probability of an impact in them is less than the value, starting from which, according to Russian standards, it must be taken into account in the design basis of the NPP, i.e. it can be ignored. Dependencies are given for calculating the probability of an aircraft strike in the case of a deliberately organized accident (terrorist attack), in which the aircraft will surely fall on the territory of “Nuclear Island” of the NPP. The procedure for setting the design loads on the building structures of a NPP in the case of a deliberate aircraft fall based on the allowed probability of their realization is described. It is shown that this method of setting the loads makes it possible to substantiate their significant reduction, which leads to a reduction in the cost of the NPP while guaranteeing its safety. A probabilistic assessment of structures safety of existing NPP in the event of an aircraft impact is discussed.

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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 (December 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 monitoring is essential for safe operation of aircraft structures. The following article shows the results of fatigue analysis based on flight data from different flight data recorders for the Su-22 fighter aircraft.

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Teng, Xichao, Qifeng Yu, Jing Luo, Gang Wang, and Xiaohu Zhang. "Aircraft Pose Estimation Based on Geometry Structure Features and Line Correspondences." Sensors 19, no. 9 (May 9, 2019): 2165. http://dx.doi.org/10.3390/s19092165.

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A robust and accurate aircraft pose estimation method is proposed in this paper. The aircraft pose reflects the flight status of the aircraft and accurate pose measurement is of great importance in many aerospace applications. This work aims to establish a universal framework to estimate the aircraft pose based on generic geometry structure features. In our method, line features are extracted to describe the structure of an aircraft in single images and the generic geometry features are exploited to form line groups for aircraft structure recognition. Parallel line clustering is utilized to detect the fuselage reference line and bilateral symmetry property of aircraft provides an important constraint for the extraction of wing edge lines under weak perspective projection. After identifying the main structure of the aircraft, a planes intersection method is used to obtain the 3D pose parameters based on the established line correspondences. Our proposed method can increase the measuring range of binocular vision sensors and has the advantage of not relying on 3D models, cooperative marks or other feature datasets. Experimental results show that our method can obtain reliable and accurate pose information of different types of aircraft.

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Zhang, Qian, Gang Liu, and Cun Li Wu. "Sustainment Engineering and Residual Life Prediction of Aluminum Alloy Structure at Service Environment." Advanced Materials Research 661 (February 2013): 124–27. http://dx.doi.org/10.4028/www.scientific.net/amr.661.124.

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The effects of service environment will cause corrosion damage and fatigue cracks to initiate and grow, compromising structural integrity of the aircraft aluminum alloy structure. To develop an effective inspection and maintenance-scheduling program that takes advantage of life extension technologies, the sustainment engineering and residual life prediction method of aging aircraft aluminum alloy structure at service environment was proposed in this article. The whole algorithm of the sustainment engineering was described and the included situations of repairs, corrosion damage and widespread fatigue damage on aircraft structures were presented. At last, combining the results of FEM calculation with the AFGROW software of crack growth analyses, the residual life of corroded aluminum alloy structure was estimated.

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Venugopal, Arvinthan, Roslina Mohammad, Md Fuad Shah Koslan, Ashaari Shafie, Alizarin Ali, and Owi Eugene. "Structure Life Extension towards the Structural Integrity of Sukhoi Su-30MKM." Materials 14, no. 19 (September 25, 2021): 5562. http://dx.doi.org/10.3390/ma14195562.

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The airframe structures of most fighter aircraft in the Royal Malaysian Airforce have been in service for 10 to 20 years. The effect of fatigue loading, operating conditions, and environmental degradation has led to the structural integrity of the airframe being assessed for its airworthiness. Various NDT methods were used to determine the current condition of the aircraft structure after operation of beyond 10 years, and their outcomes are summarized. In addition, although there are six critical locations, the wing root was chosen since it has the highest possibility of fatigue failure. It was further analyzed using simulation analysis for fatigue life. This contributes to the development of the maintenance task card and ultimately assists in extending the service life of the fighter aircraft. Using the concept of either safe life or damage tolerance as its fatigue design philosophy, the RMAF has adopted the Aircraft Structural Integrity Program (ASIP) to monitor the structural integrity of its fighter aircraft. With the current budget constraints and structural life extension requirements, the RMAF has embarked on the non-destructive testing method and engineering analysis. The research outcome will enhance the ASIP for other aircraft platforms in the RMAF fleet for its structure life assessment or service life extension program.

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Triani, Suciari Dewi, Moh Ardi Cahyono, and Lazuardy Rahendra Pinandhita. "STRUCTURE ANALYSIS AND MANUFACTURING OF WINGS TRAINER-5774." Vortex 1, no. 2 (January 26, 2021): 107. http://dx.doi.org/10.28989/vortex.v1i2.894.

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Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.

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Shcherban, K. S., A. A. Surnachev, S. M. Naumov, A. Ya Sterlin, A. G. Kalish, and O. V. Chuvilin. "Static and fatigue testing using the same full-scale transport aircraft structure." Industrial laboratory. Diagnostics of materials 86, no. 12 (December 17, 2020): 54–63. http://dx.doi.org/10.26896/1028-6861-2020-86-12-54-63.

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The entire cycle of strength tests of the aircraft structure requires large expenditures of time and effort attributed to the manufacture of two full-size aircraft structures and two test rigs. The pace of development of modern aviation technology dictates strict requirements for timing and quality of testing, which allows us to ensure competitiveness in the world aircraft market. Therefore, when conducting a full cycle tests, shortening of the testing period becomes of particular importance. We consider a novel approach to strength testing of a full-scale transport aircraft structure which consists in static and fatigue tests carried out on the same object. The developed approach was tried out when testing the full-scale wing structure of a transport aircraft. The tests were carried out on a set-up that allowed reproducing both cases of static loading and variable loads of flight cycles. At the first stage, the static strength was proved by the results of finite-element calculation of the stress state of the structure at ultimate loads using a model verified by the strain measurements of one of the wing consoles under limit loads, as well as by testing typical and critical airframe elements. Samples of full-scale panels were additionally tested for buckling to confirm the load capacity of the upper wing panels. Fatigue tests were carried out in the time span of two design service life. The obtained results showed the possibility of conducting both static and fatigue tests using one and the same full-scale aircraft structure.

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Lü, Zhi, Zhan Gao, and Yi Lü. "A Flight Simulator that Grouping Aircrafts Simultaneously Take off and Land in Open Grid Computing Environment." Applied Mechanics and Materials 182-183 (June 2012): 1292–97. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.1292.

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The performance of airplane in commercial airline environment is determined by, and therefore an indicator of performance measure of, the thermodynamic properties of airplane. The aim of this study was to establish the use of simulators to determine aircraft accident for a flight of airplanes and evaluate the potential of new airspace structure and airport’s runway. This indicates that there is a possibility of obtaining airplane performance from analysis and verification simulating airplane. As compared with AIRBUS Full Flight Simulator, a multiple aircrafts flight simulator that grouping aircrafts simultaneously take off and land was presented, which is basis on a parallel distributed computing in Open Grid Computing Environment (OGCE), and service oriented architecture (SOA) of software in multiple aircraft simulator, the performance of collaborative flight of multiple aircrafts is evaluated.

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Lu, Xiao Hua, and Hong Fu Zuo. "A New Technology of Aircraft Structural Health Monitoring." Advanced Materials Research 764 (September 2013): 71–74. http://dx.doi.org/10.4028/www.scientific.net/amr.764.71.

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A new technique of aircraft structural health monitoring so-called Comparative Vacuum Monitoring (CVM) is introduced in this paper. Compared with the traditional and some novel Non-Destructive Testing (NDT) techniques, it is capable of real-time crack initiation and growth detection reliably and accurately, and especially suitable to monitor the interior locations with hard accessibility. With the advantages of this technique, the aircraft manufacturers (such as Boeing, Airbus, Bombardier, Embraer, ect.) are much interested in applying it into aircraft structural health monitoring and have carried out verification tests on aircrafts or technology ready for the future usage. Through the use of CVM technique, it is possible to quickly, routinely and remotely monitor the integrity of a structure in service.

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Kovalenko, S. M., G. V. Petushkov, and O. V. Platonova. "Structure Selection Technique of Multi-Processor Computing Systems." International Journal of Engineering & Technology 7, no. 4.36 (December 1, 2018): 29. http://dx.doi.org/10.14419/ijet.v7i4.36.22707.

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This paper discusses construction of modern microprocessor structures and computing modules, including microprocessors and RAM, as well as computing systems containing computing modules combined by network means. Also, the "overhead" expenditure of time used for data transmission in the considered subsystems is analyzed. Estimates of the time spent on calculations and data exchange in multiprocessor computing systems (VS) are considered. An expression is derived for estimating the optimal number of computational modules in an aircraft that provides the minimum program execution time. Implementation of an aircraft with the structure recommended in the work, allows us to increase the overall performance of the system when performing the tasks that require intensive data exchange between individual computing modules. The results of research are expected to be used in the design and development of high-performance aircraft structures.

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Griggs, S. C., and A. Haji-Sheikh. "Parametric Study of Actively Cooled Aircraft Structure." Journal of Thermophysics and Heat Transfer 12, no. 3 (July 1998): 350–57. http://dx.doi.org/10.2514/2.6368.

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Unruh, James F. "Structure-borne noise control for propeller aircraft." Journal of Aircraft 25, no. 8 (August 1988): 752–57. http://dx.doi.org/10.2514/3.45654.

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Chester, R. J., K. F. Walker, and P. D. Chalkley. "Adhesively bonded repairs to primary aircraft structure." International Journal of Adhesion and Adhesives 19, no. 1 (February 1999): 1–8. http://dx.doi.org/10.1016/s0143-7496(98)00014-1.

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Bohne, Alan R., and Albert C. Chmela. "Storm structure during aircraft lightning strike events." Journal of Geophysical Research 91, no. D12 (1986): 13291. http://dx.doi.org/10.1029/jd091id12p13291.

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OKADA, Takao. "Prediction of Fatigue Life for Aircraft Structure." Journal of the Society of Mechanical Engineers 113, no. 1094 (2010): 24–27. http://dx.doi.org/10.1299/jsmemag.113.1094_24.

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Journal articles on the topic 'Aircraft structure'

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