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Journal articles on the topic 'Aircraft analysis'

Author: Grafiati

Published: 4 June 2021

Last updated: 3 February 2022

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1

Fujita, Etsushi, Taichi Higashioka, Manabu Sugiura, and Osamu Kohashi. "Evaluation method of military aircraft noise using AI analysis of aircraft images." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 6 (2021): 854–62. http://dx.doi.org/10.3397/in-2021-1668.

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In recent aircraft noise survey in Japan, noise data is associated with each aircraft by flight log or by radio information including transponder signals. Especially, above Tokyo metropolitan area, flight tracks are tangled extremely each other, therefore assessments from various perspectives such as departure / arrival airport, used runway, aircraft model, and operator have been demanded for determining noise policies. However, for military aircrafts, it is not easy to identify their information with the same way as commercial aircrafts, because their flight logs are not disclosed and many of

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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 add

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Zuo, Yu Yu. "Analysis of Gas Turbine Engines Auxiliary Power Units." Applied Mechanics and Materials 533 (February 2014): 13–16. http://dx.doi.org/10.4028/www.scientific.net/amm.533.13.

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As aircraft became more complex a need was created for a power source to operate the aircraft systems on the ground without the necessity for operating the aircrafts main engines. This became the task of the Auxiliary Power Unit (APU). The use of an APU on an aircraft also meant that the aircraft was not dependant on ground support equipment at an airfield. It can provide the necessary power for operation of the aircrafts Electrical, Hydraulic and Pneumatic systems. It should come as no surprise that the power unit selected to do this task is a Gas Turbine Engine.

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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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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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Janeba-Bartoszewicz, Edyta, and Adam Rojewski. "Analysis of hazards occurring during the use of hydrazine." WUT Journal of Transportation Engineering 125 (June 1, 2019): 37–43. http://dx.doi.org/10.5604/01.3001.0013.6493.

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The article presents the safety issue bonded to the Polish Air Force F-16 multirole aircraft. The authors pointed out the issue of fuel used for emergency supply system of these aircrafts. The paper emphasized the fact that these aircrafts require special fuel with designation H-70, which is 70% aqueous solution of toxic hydrazine. For this reason, the rescue services of Polish Air Force bases where Polish F-16 are stationed had to be adjusted accordingly. Just as importantly authors noticed that in the event of an emergency landing of this aircraft at different airports can receive difficulti

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Olugbeji, Jemitola P., Okafor E. Gabriel, and Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft." Recent Patents on Engineering 14, no. 2 (2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.

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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exis

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FUĆ, Paweł, Monika KARDACH, and Marta MACIEJEWSKA. "Analysis of the availability of aircrafts with alternative propulsions." Combustion Engines 179, no. 4 (2019): 220–25. http://dx.doi.org/10.19206/ce-2019-437.

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Global air traffic doubles every 15 years. Therefore, aviation emission grows as well. It is advisable to look for an alternative aircrafts’ propulsion for both commercial and general aviation (usually flying closer to the ground). There are many prototypes proposed by homemade projects, through companies wanting to extend their offer. There are also several more advanced constructions ready to self-set or serially produced. In the article the main topic are electric aircrafts as an example of possibility to reduce the toxic compounds emission. According to the analysis some of companies speci

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Kumar, Sachin. "Computational Analysis for Random Winglet Designs on Light Aircraft." Journal of Advanced Research in Mechanical Engineering and Technology 05, no. 01 (2018): 01–16. http://dx.doi.org/10.24321/2454.8650.201801.

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Zhou, Hong, Zhan Xue Wang, and Xiao Bo Zhang. "Areo-Engine Cycle Parametric Analysis and Installed Performance Calculation Based on Aircraft Flight Mission." Applied Mechanics and Materials 482 (December 2013): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amm.482.277.

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The aircraft/engine integration design numerical simulation model was established. The engine design performance specifications were obtained by calculating aircraft lift-drag characteristics, mission analysis, constraint analysis. Combining engine cycle parametric analysis with installation loss computing, the engine performance parameters can be found, which meet the aircraft flight envelope performance requirements. Taking double bypass variable cycle engine as an example to check the model, the results show that the variable cycle engine can meet aircrafts thrust and fuel consumption deman

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Srinivas, G., and Srinivasa Rao Potti. "Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles." Applied Mechanics and Materials 592-594 (July 2014): 1020–24. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.1020.

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Fighter aircraft wings are the leading lift generating components for any aerospace vehicle. The recital of any flying vehicle largely depends on its wing design. Missiles and the fighter aircrafts which are having propulsion system mostly have fins to control and maneuver. In this present paper work an attempt has been made to design a fighter aircraft wing configuration which will be used in some air launched air to surface guided weapons fighter aircraft. The main focus of this paper agreement in determining the Sweep-back effects on fighter aircraft wing under transonic condition at differ

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Immer, Marc, and Philipp Georg Juretzko. "Advanced aircraft performance analysis." Aircraft Engineering and Aerospace Technology 90, no. 4 (2018): 627–38. http://dx.doi.org/10.1108/aeat-11-2016-0205.

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Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally eff

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Howarth, D. K. "VSTOL Aircraft market analysis." Aeronautical Journal 113, no. 1140 (2009): 107–18. http://dx.doi.org/10.1017/s0001924000002839.

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Abstract This paper describes the market for air vehicles that offer Very Short Take Off and Landing (VSTOL) capabilities, also known as VSTOL aircraft. A commercial VSTOL aircraft will only succeed if it provides profits to both manufacturers and airlines. Being able to operate out of shorter fields offers airlines greater flexibility and therefore provides a benefit to the airline. However, adding VSTOL performance also adds cost. Successful VSTOL aircraft designs must balance the added cost against the additional benefits VSTOL performance will provide. The first problem in any new VSTOL de

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Geri, Walter, and Gianni Bertoni. "Aircraft Guidance Law Analysis." IFAC Proceedings Volumes 37, no. 6 (2004): 499–504. http://dx.doi.org/10.1016/s1474-6670(17)32224-3.

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Hong, Wei Jiang, and Dong Li Ma. "Influence of Control Coupling Effect on Landing Performance of Flying Wing Aircraft." Applied Mechanics and Materials 829 (March 2016): 110–17. http://dx.doi.org/10.4028/www.scientific.net/amm.829.110.

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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing

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Kwiek, Agnieszka. "Conceptual design of an aircraft for Mars mission." Aircraft Engineering and Aerospace Technology 91, no. 6 (2019): 886–92. http://dx.doi.org/10.1108/aeat-08-2018-0231.

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Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic

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Zheng, Feng Zhu, Wei Min Cui, and Hong Juan Li. "Static Strength Analysis of Components of Flap Control System for a Certain Type of Aircraft." Applied Mechanics and Materials 401-403 (September 2013): 422–26. http://dx.doi.org/10.4028/www.scientific.net/amm.401-403.422.

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Pull rod and rocker arm are important parts of aircraft control system, its strength, stiffness and stability can largely affect the aircrafts control effect, sometimes the flight safety will be influenced [2]. A type of aircraft control system has been upgraded and modified, therefore the pull rod and rocker arm of the flap control system need to take the static strength test. Based on field test and finite element simulation analysis, this paper has the static strength of pull rod and rocker arm checked, and to verify the correctness of the finite element model and lay foundation for the opt

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Dongsheng, Chen, He Yan, and Zhou Mengqian. "Research on operation scenario based aircraft power system architecture analysis and modelling." E3S Web of Conferences 271 (2021): 01017. http://dx.doi.org/10.1051/e3sconf/202127101017.

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Aircraft power system is a complex system consisting of the power generation system, the power management and distribution system, and the power consumption system, which accounts for the aircraft's major fuel consumption and emissions. This paper proposes a scenario-based comprehensive power requirement analysis and system architecture methodology in order to alleviate the risk of systems over-design and discoordination caused by traditional bottom-up load collection and individual system design. Starting from the operation scenario, system functions are identified and corresponding physical

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Zhaohui, Ming, Zhang Ming, Tang Xinmin, and Han Song-Chen. "Structural Modelling and Deceleration Algorithm for a Follow Aircraft on Performance-Based Navigation Airway Based on Multi-Agent Technique." Cybernetics and Information Technologies 15, no. 6 (2015): 46–56. http://dx.doi.org/10.1515/cait-2015-0066.

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Abstract Considering the operation characteristics of the high-speed PBN airway, we propose an aircraft agent structural model and a basic algorithm flow of decision-making by Multi-agent technique. According to the constraint of safe separation and speed with the aircrafts, making use of the car-following theory, the deceleration constraint model is built for a flight management system. When the front aircraft decelerates, the model can offer a speed adjustment proposal for the following aircraft. The model is built based on the minimal safe separation and speed interval constraint; each vari

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Li, Xiang, Sheng Huang, Song Ding, and Lang Gu. "Analysis of Air-Flow Field of Large Ships in Waves." Applied Mechanics and Materials 494-495 (February 2014): 309–12. http://dx.doi.org/10.4028/www.scientific.net/amm.494-495.309.

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Movement of large ship in waves is one of the important factors which can induce ship surface air turbulence; it is bound to a large impact on the air-flow field on deck, which affect the safety of the aircraft landing. In order to study the change of the flow field in the process of movement of large ship and its influence on aircrafts take-off and landing, under the same experimental condition of the unsteady condition. We set up 3d model, observe and analyze the ships air-flow field changes in the movement. Finally, calculate the results and give the effect of the aircraft landing in the ke

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Venkatesh, P. H. J., and M. S. R. Viswanath. "Design and Analysis of Avionic Structures For Aircraft Applications." International Journal for Modern Trends in Science and Technology 6, no. 5 (2020): 78–83. http://dx.doi.org/10.46501/ijmtst060513.

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The Avionic enclosure is a electronic packed setup which are used in aircrafts and spacecrafts. Avionic enclosure is used for mechanical support to all the system elements and this is mechanically interfaced with the aircrafts. The avionic enclosures is a key role for the system performance. The avionic package has to be designed to withstand high dynamics. FINGS(FIBRE OPTIC GYRO BASED INERTIAL NAVIGATION SYSTEM) is a unit of aircraft for finding the navigation. In this paper the FINGS + GPS SYSTEM (FINGS) unit designed using SOLID WORKS and The Modal Analysis on these parts was carried out us

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Deshpande, Shubhangi, Layne T. Watson, Nathan J. Love, Robert A. Canfield, and Raymond M. Kolonay. "Aircraft Design Markup Language for Multidisciplinary Aircraft Design and Analysis." Journal of Aerospace Information Systems 12, no. 2 (2015): 267–83. http://dx.doi.org/10.2514/1.i010222.

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Woźny, Piotr, and Józef Błachnio. "Analysis Of Damage Arising From Exploitation Of The Aircraft." Journal of KONBiN 32, no. 1 (2014): 5–18. http://dx.doi.org/10.2478/jok-2014-0027.

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Abstract During exploitation, due to a variety of reasons, aircrafts are damaged or suffer from different failures. In the process of operation, using appropriate methods of diagnosis, failure, damage, and relative deregulation of individual elements or units can be detected. For this purpose, one can apply a number of indirect diagnostic methods with the use of recorded diagnostic signals or a direct diagnosis with the use of non-destructive methods. The proper identification of the technical condition allows to determine the causes of irregularities and take actions aimed at preventing their

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Wołoszyn, Mirosław. "Analysis of aircraft magnetic interference." International Journal of Applied Electromagnetics and Mechanics 39, no. 1-4 (2012): 129–36. http://dx.doi.org/10.3233/jae-2012-1452.

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Kong, Huan Ping, Chang Kui Liu, De Lin Liu, and Tao Jiang. "Aircraft Bearings Fracture Failure Analysis." Advanced Materials Research 887-888 (February 2014): 319–23. http://dx.doi.org/10.4028/www.scientific.net/amr.887-888.319.

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Between aircraft bearings lugs, plates fracture appeared. The failure mode and cause were analyzed by macro and micro observation, EDS analysis, metallographic examination and hardness testing. The results showed that two bearings’ failure were stress corrosion cracking. Bearings’ failure were related with abnormal force state, material cast loose exceeding the allowed limited values played a catalytic role to crack propagation. It is suggested that bearings material surface protection should be strengthened to improve corrosion resistance, bearings design should be optimized to avoid abnormal

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Tarvainen, Matti, Outi Valtonen, Eystein S. Husebye, and Björn Lund. "Seismic analysis of aircraft accidents." Natural Science 05, no. 07 (2013): 811–17. http://dx.doi.org/10.4236/ns.2013.57098.

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Cripwell, J. Paul. "Aircraft Traffic Analysis for Forecasting." Transportation Research Record: Journal of the Transportation Research Board 2177, no. 1 (2010): 27–32. http://dx.doi.org/10.3141/2177-04.

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Brown, H., and J. A. Elgin. "Aircraft Engine Control Mode Analysis." Journal of Engineering for Gas Turbines and Power 107, no. 4 (1985): 838–44. http://dx.doi.org/10.1115/1.3239820.

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This paper describes the control mode analysis procedure that is used to establish closed-loop control requirements for advanced aircraft propulsion systems. The procedure utilizes anticipated variations in engine component performance, engine deterioration, and control tolerances in a statistical analysis to establish corresponding variations in engine output performance and safety parameters. Potential closed-loop control configurations are evaluated by this process, compared, and the best configuration selected for implementation into control law and schedule designs. A byproduct of the ana

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Sokolović, Vlada S., Slaviša R. Pavlović, and Darko D. Janković. "Analysis of aircraft maintenance models." Vojnotehnicki glasnik 59, no. 4 (2011): 194–207. http://dx.doi.org/10.5937/vojtehg1104194s.

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Potkański, W. "Flutter analysis of light aircraft." Acta Mechanica 62, no. 1-4 (1986): 105–12. http://dx.doi.org/10.1007/bf01175857.

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Zhao, He Huan, and Hong Bin Yu. "Modeling and Analysis of Arresting Property of EMAS." Advanced Materials Research 989-994 (July 2014): 2829–33. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.2829.

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The EMAS of aircraft-pavement is a dedicated device that used to block aircraft overrunning the runway. To protect the safety of aircraft and passengers, the EMAS can safely arrest the overrun aircraft in an allowed distance and inertial load without injuring aircraft passengers and damaging aircraft. Combining with actual situation, this paper made statics and dynamics analysis under the action of the wheel of EMAS,and provides effective theoretical support for further research of EMAS of aircraft-pavement.

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Zhen, Ziyang, Ju Jiang, Xinhua Wang, and Kangwei Li. "Modeling, control design, and influence analysis of catapult-assisted take-off process for carrier-based aircrafts." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 13 (2017): 2527–40. http://dx.doi.org/10.1177/0954410017715278.

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This paper addresses the problems of modeling, control design, and influence analysis of the steam catapult-assisted take-off process of the carrier-based aircrafts. The mathematical models of the carrier-based aircraft, steam catapult, landing gears, and the environmental factors including deck motion and bow airflow have been established to express the aircraft dynamics in the take-off process. An engineering method based automatic flight control system has been designed, which is divided into the longitudinal channel and lateral channel. The influences of the preset control surface, ship de

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Al Wardi, Yousuf, Sasirajan Jeevarathinam, and Saleh Al Sabei. "A Cross-Cultural Anthropometric Analysis in Military Aviation." Aerospace Medicine and Human Performance 91, no. 4 (2020): 358–62. http://dx.doi.org/10.3357/amhp.5530.2020.

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BACKGROUND: Aircrew-aircraft compatibility is important in military aviation for flight safety. Anthropometric aircrew selection standards in RAFO were embedded from the selection standards of western defense forces as the aircrafts were imported from there. Henceforth efforts were made to fit local native aviators into aircrafts not initially designed for them. In view of this, this study was carried out to obtain the anthropometric data of Oman aircrew recruits and compare these with published western and eastern data with a hope to understand and highlight the aircrew-aircraft mismatch issu

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Wang, You Shan, Jian Wu, and Ben Long Su. "Analysis on the Hydroplaning of Aircraft Tire." Advanced Materials Research 87-88 (December 2009): 1–6. http://dx.doi.org/10.4028/www.scientific.net/amr.87-88.1.

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Aircraft tire is an important subassembly of aircraft, which is related to its safety tightly, especially for civil aircraft. Moreover, hydroplaning of aircraft tires is often a contributing factor in take-off and landing overrun and veeroff accidents. Therefore the study on them is imperative. For studying the hydroplaning of aircraft tire, a 2D finite element model of aircraft tire is developed by using TYABAS software, and then a 3D patterned tire model is presented. The hydroplaning of aircraft tire is analyzed by generally coupling an Eulerian finite volume method and an explicit Lagrangi

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Chiesa, Sergio, Sabrina Corpino, Marco Fioriti, Alessandro Rougier, and Nicole Viola. "Zonal safety analysis in aircraft conceptual design: application to SAvE aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227, no. 4 (2012): 714–33. http://dx.doi.org/10.1177/0954410012441430.

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Chen, Pu Woei, Shu Han Chang, and Chan Ming Chen. "Impact Loading Analysis of Light Sport Aircraft Landing Gear." Applied Mechanics and Materials 518 (February 2014): 252–57. http://dx.doi.org/10.4028/www.scientific.net/amm.518.252.

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This paper examined the critical loading condition of a light sport aircrafts main landing gear during the impact loading condition. The new category airplane was established by the FAA in 2004. The light sport aircraft has great market demand for personnel entertainment purpose and regional transportation. The main object of this research was to establish a static and dynamic loading simulation model for the aluminum alloy landing gear of a light sport aircraft. This work also examined the critical loading parameters of the main landing gear, including the maximum take-off weight and maximum

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Anton, N., and R. M. Botez. "Weight functions method for stability analysis applied as design tool for Hawker 800XP aircraft." Aeronautical Journal 119, no. 1218 (2015): 981–98. http://dx.doi.org/10.1017/s0001924000004280.

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Abstract A new method for system stability analysis, the weight functions method, is applied to estimate the longitudinal and lateral stability of a Hawker 800XP aircraft. This paper assesses the application of the weight functions method to a real aircraft and a method validation with an eigenvalues stability analysis of the linear small-perturbation equations. The method consists of finding the weight functions that are equal to the number of differential equations required for system modelling. The aircraft’s stability is determined from the sign of the total weight function – the sign shou

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Wu, Kai Feng, Yue Zhou, Jing Ma, and Juan Lin. "Skin Coating Design of Stealth Aircraft Based on Infrared Characteristic Analysis." Materials Science Forum 976 (January 2020): 50–54. http://dx.doi.org/10.4028/www.scientific.net/msf.976.50.

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With the requirement of the research on the stealthy aircraft’s infrared characteristic, the design and analysis have got more attention. Depend on synthesizing the main factors, include the surface IR radiation, the scatter radiation from the environment, the temperature distribution and the coat distribution of the surface, which effect the stealthy capability, a stealthy aircraft’s IR characteristic simulation model was proposed. Based on MODTRAN, the environment radiation model was built and was used in the simulation model. Finally, the proposed simulation mode was used in design and opti

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Kale, Nachiket Vinayak, Firat Ilkay, and Oliver Zysk. "Particular risk analysis: impact on hybrid aircraft design." International Journal of Structural Integrity 6, no. 3 (2015): 402–9. http://dx.doi.org/10.1108/ijsi-10-2014-0060.

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Purpose – This document presents a Particular Risks Assessment (PRA) performed on an Uncontained Engine Rotor Failure (UERF) event for the new aircraft design hybrid Extremely Short Take Off and Landing All Surface (ESTOLAS) aircraft. All three propellers of the ESTOLAS (one hub propeller and two feed propellers) are evaluated for their impact on the aircraft in case of an UERF. The purpose of this paper is to present an illustration of the safety analysis and its requirement in new aircraft development. Design/methodology/approach – The methodology used is in accordance with the aerospace ind

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Магдин, Александр, Aleksandr Magdin, Алексей Припадчев, Aleksey Pripadchev, Александр Горбунов, and Aleksandr Gorbunov. "ALGORITHM OF AIRCRAFT TARGET CHOICE." Bulletin of Bryansk state technical university 2019, no. 10 (2019): 48–54. http://dx.doi.org/10.30987/article_5db95e85e569b8.29571093.

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The work purpose consists in the algorithm development for aircraft target choice. The investigations were carried out with the use of methods of a system analysis, a theory of modeling, mathematical methods, methods of object-directed programming.  In farms when agricultural area processing it is advisable to use an aircraft. A choice is argued by aircraft advantages over the ground-based means of agricultural area processing which consist in mobility and a processing speed and also in the absence of mechanical impact upon the growth of the area under processing. In the paper there is o

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PAČAIOVÁ, Hana, Marianna TOMAŠKOVÁ, Michaela BALÁŽIKOVÁ, and Jozef KRAJŇÁK. "Analysis of air-traffic threats." Scientific Journal of Silesian University of Technology. Series Transport 110 (March 1, 2021): 143–55. http://dx.doi.org/10.20858/sjsutst.2021.110.12.

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Globally, air transport has seen a greater increase in recent years. This manuscript is divided into three parts for analysing the negative effects of aviation. The first part is focused on the identification of sources of aircraft noise. While the second part of this article describes the basic principles of the construction and operation of an aircraft jet engine concerning the gaseous emissions produced by such an engine (Third part missing?). The main benefit of this article is the evaluation of the reliability of the human factor because the human factor is an integral part of technical s

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TOTH, Jozsef, and Bertold BEKESI. "THE IMPORTANCE OF LIFE-CYCLE ANALYSIS IN ECONOMIC ANALYSIS OF ENVIRONMENTAL IMPACT OF ALTERNATIVE AIRCRAFT FUEL." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 21, no. 1 (2019): 194–98. http://dx.doi.org/10.19062/2247-3173.2019.21.26.

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Żugaj, Marcin, Przemysław Bibik, and Marcin Figat. "An Unmanned Aircraft Model for Control System Reconfiguration Analysis and Synthesis." Transactions on Aerospace Research 2017, no. 2 (2017): 97–116. http://dx.doi.org/10.2478/tar-2017-0018.

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Abstract Reliability of unmanned aircraft is a decisive factor for conducting air tasks in a controlled airspace. One of the means of improving unmanned aircraft reliability is reconfiguration of the control system, which will allow to maintain control over the aircraft despite an occurring failure. The control system is reconfigured by using still operational control surfaces to compensate for failure consequences and to control the damaged aircraft. Development of effective reconfiguration algorithms involves utilization of a non-linear model of unmanned aircraft dynamics, in which each cont

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Chen, Xiao Jie. "The Environmental Pollution Analysis of Aircraft." Advanced Materials Research 518-523 (May 2012): 2259–62. http://dx.doi.org/10.4028/www.scientific.net/amr.518-523.2259.

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The Environmental factors cover a wide range of aspects but noise and emissions are the main regulatory issues which affect the design of the aircraft. Both are largely associated with engine design aspects and aircraft flight profiles. With the expected growth in air traffic at the major airports the environmental pressure groups will become more vocal. This paper shows the influence of airworthiness and environmental influences of aircraft. Both noise and emission pollution were discussed. Several methods were given to reduce these environment pollution on the base of the analysis.

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Kustra, Todd W., Subhashini Ganapathy, Amanda C. Muller, and S. Narayanan. "Decision Support System for Logistics Systems Analysis Using Image Theory and Work Domain Analysis." Journal of Defense Modeling and Simulation: Applications, Methodology, Technology 2, no. 2 (2005): 71–85. http://dx.doi.org/10.1177/154851290500200203.

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In this study, image theory and work domain analysis were used to develop an interactive decision support system for sortie generation tasks in an Air Force aircraft maintenance unit. Aircraft maintenance personnel were charged with creating a short list of aircraft for deployment using either maintenance information alone or maintenance information with the interactive decision support system. Results were compared with a deployment list developed by expert aircraft maintenance superintendents. The deployment lists generated with the interactive decision support system more closely resembled

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Deiwert, George S., Alison E. Andrews, and Kazuhiro Nakahashi. "Theoretical analysis of aircraft afterbody flow." Journal of Spacecraft and Rockets 24, no. 6 (1987): 496–503. http://dx.doi.org/10.2514/3.25944.

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Mahaldar, Affan. "Bird Strike Analysis on Aircraft Wing." International Journal for Research in Applied Science and Engineering Technology 8, no. 10 (2020): 867–73. http://dx.doi.org/10.22214/ijraset.2020.32042.

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Zhang, Wen Guang, and Guo Min Lin. "Analysis of Aircraft Hydraulic System Failures." Advanced Materials Research 989-994 (July 2014): 2947–50. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.2947.

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The hydraulic system of Aircraft is an important power organization and plays an important role in the process of airplane operation. The failures of the airplane have the character of concealment, complexity and uncertainty. So if the hydraulic system ran out of order it not only cause huge casualties and economic losses, but also has a long and low efficiency maintenance cycle. This text analyzes the common causes of the failures and the failures that newly appeared of the aircraft hydraulic systems in detailed. Some of effective solutions have been proposed which quicken accelerate the spee

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Wu, Meng Li, Bin Chen, and Zhi Wei Xing. "Analysis of Centralized Aircraft Deicing Process." Applied Mechanics and Materials 101-102 (September 2011): 779–82. http://dx.doi.org/10.4028/www.scientific.net/amm.101-102.779.

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This paper established a mathematical model for the centralized aircraft ground deicing processes which includes preparation, deicing operations and release after the deicing. To ensure the safety of aircraft, the proposed model has taken into account the constraint that the total time of deicing processes shall be less than the retention time of the deicing fluid so as to avoid secondary icing hazards. The proposed model has been verified through numerical simulations, where a first-come-first-service scheduling scheme is assumed. Simulation results show that the proposed model matches the cu

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Sharafeev, I. Sh, and I. V. Ermolenko. "Analysis of light aircraft production management." Russian Aeronautics (Iz VUZ) 56, no. 4 (2013): 396–400. http://dx.doi.org/10.3103/s1068799813040120.

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