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Journal articles on the topic 'Aircraft applications'

Author: Grafiati

Published: 4 June 2021

Last updated: 8 February 2022

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1

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

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Accurate knowledge regarding the ongoing condition of an aircraft’s structural condition together with future life predictions enable optimal use of material, hence reducing mass, cost and environmental effects. Previous work by the authors has demonstrated the potential for using energy harvested from vibrating aircraft panels to power a self contained health monitoring system based on the use of wireless sensor nodes for an aircraft structure. However the system proposed was far from optimal. Research is being undertaken to investigate the various factors affecting the power output of such a system, including the design of the harvesters used (length, width, number of layers), their positioning and their orientation. The work presented in this paper enables the determination of the optimised positions for a series of harvesters on a representative aircraft panel, based on the use of shape functions for the various modes of vibration over the expected frequency range, to derive a function related to power output which is then optimised. A series of recommendations are made.

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2

A, Dr Mohan Krishna S., S. V. Gunaraman,, and Sandeep D. "Importance, Relevance and Applications of Smart Materials in Aircraft Control." International Journal of Trend in Scientific Research and Development Volume-2, Issue-4 (June 30, 2018): 1655–58. http://dx.doi.org/10.31142/ijtsrd14405.

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3

Enomoto, Kiyoshi. "Magnesium alloys for aircraft applications." Journal of Japan Institute of Light Metals 65, no. 9 (2015): 472–77. http://dx.doi.org/10.2464/jilm.65.472.

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4

Immarigeon, J.-P., R. T. Holt, A. K. Koul, L. Zhao, W. Wallace, and J. C. Beddoes. "Lightweight materials for aircraft applications." Materials Characterization 35, no. 1 (July 1995): 41–67. http://dx.doi.org/10.1016/1044-5803(95)00066-6.

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5

Renouard-Vallet, Gwenaelle M., Josef Kallo, Andreas K. Friedrich, Johannes Schirmer, Martin Saballus, and Gerrit Schmithals. "Fuel Cells For Aircraft Applications." ECS Transactions 30, no. 1 (December 17, 2019): 271–80. http://dx.doi.org/10.1149/1.3562482.

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6

BOLLER, Christian. "Smart Structures for Aircraft Applications." Journal of the Society of Mechanical Engineers 102, no. 963 (1999): 80–84. http://dx.doi.org/10.1299/jsmemag.102.963_80.

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7

Wang, Wego. "Aluminum alloys for aircraft applications." JOM 45, no. 9 (September 1993): 16–18. http://dx.doi.org/10.1007/bf03222426.

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8

Weeks, Thomas M. "Aircraft Technology-Some Overlooked Applications." Journal of Aircraft 44, no. 1 (January 2007): 1–4. http://dx.doi.org/10.2514/1.29415.

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9

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 (May 31, 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 using ABAQUS FEA software and a random vibration experimental analysis is tested under both static and dynamic analysis. The obtained results are compared other for the design optimization of FINGS package.

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10

Unlu, Deniz, Federico Cappuzzo, Olivier Broca, and Pierpaolo Borrelli. "Minimizing Aircraft ECS Bleed Off-Take - Virtual Integrated Aircraft Applications." SAE International Journal of Aerospace 9, no. 1 (September 20, 2016): 151–62. http://dx.doi.org/10.4271/2016-01-2054.

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11

Ruszaj, Adam, Józef Gawlik, and Sebastian Skoczypiec. "Electrochemical Machining – Special Equipment and Applications in Aircraft Industry." Management and Production Engineering Review 7, no. 2 (June 1, 2016): 34–41. http://dx.doi.org/10.1515/mper-2016-0015.

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AbstractElectrochemical machining is an unique method of shaping in which, for optimal parameters tool has no wear, surface layer properties after machining are similar to the core material and surface quality and accuracy increase together with material removal rate increase. Such advantages of electrochemical machining, besides of some ecological problems, create industry interest in the range of manufacturing elements made of materials with special properties (i.e. turbine blades of flow aircrafts engines). In the paper the nowadays possibilities and recent practical application of electrochemical machining in aircraft have been presented.

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12

Tarmizi Ahmad, Mohamed, Michael Lam, Razali Abidin, Shikin Razali, and Amzari Zhahir. "Flexible and extendable advance satellite tracking system." International Journal of Engineering & Technology 7, no. 4.13 (October 9, 2018): 10. http://dx.doi.org/10.14419/ijet.v7i4.13.21320.

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Aircraft tracking via satellite uses four dimensional aircraft position information to enhance flight safety by recording, scrutinizing and visualizing the information generated by an Airborne Tracking Unit (ATU) fitted onboard of aircraft flying from one point to another. It is an important device for aircraft operator to ensure its operational safety. Starfish Tracker SF3100-1 aircraft tracking unit can be used in aircraft satellite tracking applications. Research collaboration between Worldgate Technologies (WGT), Universiti Pertahanan Nasional Malaysia (UPNM) and Universiti Putra Malaysia (UPM) has developed the ATU originally from land base to airborne vehicles tracking, hence it provides multitudes of civil and military applications. The ATU is a unique device that enables multi-tasking application such as Air Combat Manoeuvring Instrumentation (ACMI), Network Centric Warfare and Flight Data Monitoring systems. In this paper, system characteristics and its applications are presented with the potential applications for Flight Data Monitoring system.

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13

Gao, Feng, Qizhi Xu, and Bo Li. "Aircraft Detection from VHR Images Based on Circle-Frequency Filter and Multilevel Features." Scientific World Journal 2013 (2013): 1–7. http://dx.doi.org/10.1155/2013/917928.

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Aircraft automatic detection from very high-resolution (VHR) images plays an important role in a wide variety of applications. This paper proposes a novel detector for aircraft detection from very high-resolution (VHR) remote sensing images. To accurately distinguish aircrafts from background, a circle-frequency filter (CF-filter) is used to extract the candidate locations of aircrafts from a large size image. A multi-level feature model is then employed to represent both local appearance and spatial layout of aircrafts by means of Robust Hue Descriptor and Histogram of Oriented Gradients. The experimental results demonstrate the superior performance of the proposed method.

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14

Hafez, Ahmed A. A. "AVERAGE CURRENT CONTROL FOR AIRCRAFT APPLICATIONS." JES. Journal of Engineering Sciences 39, no. 2 (March 1, 2011): 337–46. http://dx.doi.org/10.21608/jesaun.2011.120408.

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15

Tatum, Mark C., and Junshan Liu. "Unmanned Aircraft System Applications in Construction." Procedia Engineering 196 (2017): 167–75. http://dx.doi.org/10.1016/j.proeng.2017.07.187.

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16

Imamura, Taro. "CFD Applications for Aircraft Airframe Development." Marine Engineering 48, no. 5 (2013): 618–22. http://dx.doi.org/10.5988/jime.48.618.

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17

Krammer, Oliver, and Tareq I. Al Ma'aiteh. "Thermoelectric generators simulation in aircraft applications." International Journal of Sustainable Aviation 5, no. 4 (2019): 313. http://dx.doi.org/10.1504/ijsa.2019.10026911.

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Ma', Tareq I. Al, N. A. aiteh, and Oliver Krammer. "Thermoelectric generators simulation in aircraft applications." International Journal of Sustainable Aviation 5, no. 4 (2019): 313. http://dx.doi.org/10.1504/ijsa.2019.105243.

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19

BACKMAN, D. G., and J. C. WILLIAMS. "Advanced Materials for Aircraft Engine Applications." Science 255, no. 5048 (February 28, 1992): 1082–87. http://dx.doi.org/10.1126/science.255.5048.1082.

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20

HASEGAWA, Ryoei. "Cutting Tool for Aircraft and Applications." Journal of the Japan Society for Precision Engineering 75, no. 8 (2009): 953–57. http://dx.doi.org/10.2493/jjspe.75.953.

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21

Reddy, G., and V. Saraswat. "Advanced Navigation System for Aircraft Applications." Defence Science Journal 63, no. 2 (March 23, 2013): 131–37. http://dx.doi.org/10.14429/dsj.63.4254.

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22

Lenschow, Donald H., and Leif Kristensen. "Applications of Dual Aircraft Formation Flights." Journal of Atmospheric and Oceanic Technology 5, no. 6 (December 1988): 715–26. http://dx.doi.org/10.1175/1520-0426(1988)005<0715:aodaff>2.0.co;2.

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23

Wang, Zhipeng, Zhiqin Qian, Ziye Song, Hongzhou Liu, Wenjun Zhang, and Zhuming Bi. "Instrumentation and self-repairing control for resilient multi-rotor aircrafts." Industrial Robot: An International Journal 45, no. 5 (August 20, 2018): 647–56. http://dx.doi.org/10.1108/ir-03-2018-0053.

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Purpose Even though multi-rotor aircrafts are becoming more and more prevalent in the fields of aerial photography, agricultural spraying, disaster searching and rescuing, how to achieve higher reliability and robustness of an aircraft still poses a big challenge. It is not a rare case that a multi-rotor aircraft is severely damaged or crushed when an actuator or sensor is malfunctioned. This paper aims at the resilience of an aircraft when a rotor is malfunctioned. Design/methodology/approach The reliability of a multi-rotor aircraft can be measured in terms of stability, robustness, resilience and fault tolerance. All of these four aspects are taken into consideration to improve overall reliability of aircrafts. When a rotor malfunction occurs, the control algorithm is cable of adjusting the operation conditions of the rest of rotors to achieve system stability. Findings In this paper, the authors first present a research topic on the development of a resilient multi-robot aircraft. A multi-rotor aircraft usually possesses more actuated motions than the required degrees of freedom. Originality/value The authors proposed to equip the multi-rotor aircraft with malfunction detecting sensors, and they developed the self-repairing algorithm to re-stabilize the aircraft when a malfunction of a rotor occurs. The design concept and methods were implemented on an eight-rotor aircraft, and the performance of the proposed instrumentation and self-repairing algorithm have been verified and validated.

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24

Kranjec, Bojan, Sasa Sladic, Wojciech Giernacki, and Neven Bulic. "PV System Design and Flight Efficiency Considerations for Fixed-Wing Radio-Controlled Aircraft—A Case Study." Energies 11, no. 10 (October 3, 2018): 2648. http://dx.doi.org/10.3390/en11102648.

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The list of photovoltaic (PV) applications grows longer every day with high consideration for system efficiency. For instance, in spite of many recent PV aircraft designs, aircraft propulsion was mainly reserved for nonelectric motors. Lately, the Solar Impulse flight across the world shows the possibilities of larger PV powered electric aircraft. In order to obtain this goal efficiency of flight, PV conversion, power converters and electric drives have to be maximized. These demands led to a 63.4 m wingspan. The purpose of this paper is to present that PV power could be used for improving the performance of fixed-wing radio-controlled aircrafts with smaller wingspans (1 m). In order to improve the performance of battery powered electric unmanned aerial vehicles (UAV), a model without PV cells (commercial Li-ion battery powered UAV) was compared with UAV powered both from battery and PV modules. This work shows details about Boost DC/DC converter and PV system design for small size fixed-wing electric UAVs, investigating the possibility of the application of PV powered drones, as well. Theoretical findings involving efficiency improvements have been confirmed by measurements combining the improvements in electrical engineering, microcontroller application and aerodynamics.

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25

Deo, V. A., F. Silvestre, and M. Morales. "Flight performance monitoring with optimal filtering applications." Aeronautical Journal 124, no. 1272 (November 11, 2019): 170–88. http://dx.doi.org/10.1017/aer.2019.142.

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ABSTRACTThis work presents an alternative methodology for monitoring flight performance during airline operations using the available inboard instrumentation system. This method tries to reduce the disadvantages of the traditional specific range monitoring technique where instrumentation noise and cruise stabilisation conditions affect the quality of the performance monitoring results. The proposed method consists of using an unscented Kalman filter for aircraft performance identification using Newton’s flight dynamic equations in the body X, Y and Z axis. The use of the filtering technique reduces the effect of instrumentation and process noise, enhancing the reliability of the performance results. Besides the better quality of the monitoring process, using the proposed technique, additional results that are not possible to predict with the specific range method are identified during the filtering process. An example of these possible filtered results that show the advantages of this proposed methodology are the aircraft fuel flow offsets, as predicted in the specific range method, but also other important aircraft performance parameters as the aircraft lift and drag coefficients (CL and CD), sideslip angle (β) and wind speeds, giving the operator a deeper understanding of its aircraft operational status and the possibility to link the operational monitoring results to aircraft maintenance scheduling. This work brings a cruise stabilisation example where the selected performance monitoring parameters such as fuel flow factors, lift and drag bias, winds and sideslip angle are identified using only the inboard instrumentation such as the GPS/inertial sensors, a calibrated anemometric system and the angle-of-attack vanes relating each flight condition to a specific aircraft performance monitoring result. The results show that the proposed method captures the performance parameters by the use of the Kalman filter without the need of a strict stabilisation phase as it is recommended in the traditional specific range method, giving operators better flexibility when analysing and monitoring fleet performance.

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26

Ganjeh, Babak, and Mohd Roshdi Hassan. "Cost-Efficient Composite Processing Techniques for Aerospace Applications – A Review." Applied Mechanics and Materials 325-326 (June 2013): 1465–70. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.1465.

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Composite materials have been used in aircraft components since the early beginning of aircraft industry establishment.Undenaible advantages of composites in mechanical properties and light weight in comparison with conventional metal alloys make them desirable alternative for fabrication of different aircraft components. However, quality concerns and high costs of processing tackle the extensive usage of composites in aircraft structure, until the past decade, introducing new generation of composite processing techniques, needless of traditional autoclave processing and capable of fabricating aerospace-grade quality composite parts more time and cost efficiently. In this paper concise review over recent cost-efficient composite processing technologies with proven practicality in commercial aircraft applications, is presented.

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27

Brewer, Roger. "High Reliability Electronics for Demanding Aircraft Applications – An Overview." Additional Conferences (Device Packaging, HiTEC, HiTEN, and CICMT) 2016, HiTEC (January 1, 2016): 000011–17. http://dx.doi.org/10.4071/2016-hitec-11.

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Abstract The primary form of generated power on any typical aircraft (Tactical, Airlift, Commercial) requires conversion in multiple different forms (voltage levels, aircraft compliant frequency) and at various power levels to meet the total needs of the vehicle. DC:AC Power Conversion (Inverters), AC-DC Generator (conditioning) electronics, AC-AC frequency conditioning and DC:DC Power Conversion are all forms of conversion within the power system (primary, secondary tiers) typical of any aircraft. Additionally, within the power distribution network often solid state power switches in later generation aircraft and fighters are used to control and manage power (control power ramp-up for example) to loads and isolate electrical faults. The conditioning, conversion and control of this power with high reliability devices can often occur in more extreme environments (high temperatures, high vibration and confined spaces) and can present challenging issues for aerospace and specifically aircraft. Weight objectives can further add to the challenges. This paper will discuss, at largely a level based on acquired and compiled lessons learned, some of the aforementioned challenges including the susceptibility to both electrically and mechanically induced failure modes in power devices encountered in aircraft. The paper will also discuss the notion that while Wide Band Gap (WBG) technology may be the right answer in some/many applications, it may not be the answer in achieving high reliability given a specific combination of application and operating conditions. Reliability issues can be focused around: a) packaging optimization, b) manufacturing tolerances and c) selecting the right vendor to do the job. Further, the ability to receive adequate forms of cooling from the aircraft (if not otherwise constrained and if cooling margins permit) to power electronics will also be discussed as an obvious and significant driver in maintaining high reliability and integrity in more demanding (and higher power) applications. Trade assessments that can occur with specific generator electronics will be discussed at a non-specific, and generalized, level. The main body of the paper will be concluded with a discussion on the potential application of WBG technology in a variety of applications mentioned for aircraft while pointing out unique aspects that may be relevant in the future adoption of this technology. Finally, a conclusion will be provided reiterating various points throughout the paper and areas of potential follow-on activity.

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28

Lallana, Pedro C., Gotzon Aldabaldetreku, Alicia López, David S. Montero, Gaizka Durana, Javier Mateo, M. Ángeles Losada, Joseba Zubia, and Carmen Vázquez. "Sensing Applications in Aircrafts Using Polymer Optical Fibres." Sensors 21, no. 11 (May 21, 2021): 3605. http://dx.doi.org/10.3390/s21113605.

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We report on recent advances in the use of inexpensive polymer optical fibres (POFs) for sensing applications in avionics. The sensors analysed in this manuscript take advantage of the unique properties of polymers, such as high flexibility, elasticity, and sensitivity, and they range from strain, elongation, and vibration interrogators to level and temperature meters, leading to cost-effective techniques for structural health monitoring in aircraft structures. We also highlight recent power-supply methods using Power-over-POF in order to feed sensors remotely, and we discuss the constraints imposed by connectors on the performance of POF networks in aircrafts.

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29

ZECHIKHIN, Boris S., Sergey V. ZHURAVLEV, and Roman Yu MISYUTIN. "Permanent&Magnet Generators for Aircraft Applications." ELEKTRICHESTVO 6, no. 6 (2018): 49–59. http://dx.doi.org/10.24160/0013-5380-2018-6-49-59.

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30

Carvalho, Fernando K., Rodolfo G. Chechetto, Alisson A. B. Mota, and Ulisses R. Antuniassi. "Challenges of Aircraft and Drone Spray Applications." Outlooks on Pest Management 31, no. 2 (April 1, 2020): 83–88. http://dx.doi.org/10.1564/v31_apr_07.

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Crop protection on major crops is now required to follow the principles of integrated pest management so the timing and accuracy of any application of a pesticide or biopesticide has to be more precise to minimize adverse effects on non-target species. The development of UAVs (unmanned aerial vehicles) provides a means of providing a more targeted application of the correct dose, especially by using formulations that are more persistent, thus minimizing loss of spray in areas subject to rain. Avoiding use of too high a dosage allows greater survival of natural enemies and reduces the selection pressure for pests becoming resistant to specific modes of action. The downward flow of air from a UAV should also provide better distribution and impaction of droplets within a crop canopy, reduce soil impaction caused by taking heavy loads of spray applied with 200 l ha–1 of water, and allow treatments when fields are too wet to access with ground equipment. In Asia, many smallholder farmers are using a drone in preference to using a knapsack sprayer. According to Matthews, it has been shown that ULV spraying can be effective, but it needs a narrow droplet spectrum with the droplets remaining stable and not shrinking to become too small. Formulation research can reduce the volatility of the spray, hence the success of oil-based sprays. However, instead of petroleum-based oils, there is a chance to develop vegetable oil carriers with micro-sized particle suspensions to deliver low toxicity pesticides in droplets that can be deposited within the crop and not drift beyond the crop boundary. Oil deposits will be less prone to loss after rain so less should be lost in neighbouring ditches and water courses, especially as rainfall patterns are forecast to change. More studies are needed to evaluate the swath for deposition, buffer zones, formulation, nozzle selection, to guide future specific legislation for UAV applications.

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31

Yamaguchi, Yasuhiro. "Applications of Composite Materials to Aircraft Structures." Journal of the Japan Welding Society 64, no. 8 (1995): 602–6. http://dx.doi.org/10.2207/qjjws1943.64.602.

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32

de C. Henshaw, M. J., K. J. Badcock, G. A. Vio, C. B. Allen, J. Chamberlain, I. Kaynes, G. Dimitriadis, et al. "Non-linear aeroelastic prediction for aircraft applications." Progress in Aerospace Sciences 43, no. 4-6 (May 2007): 65–137. http://dx.doi.org/10.1016/j.paerosci.2007.05.002.

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33

Müller, Gerhard, Sebastian Beer, Sumit Paul, and Andreas Helwig. "Novel chemical sensor applications in commercial aircraft." Procedia Engineering 25 (2011): 16–22. http://dx.doi.org/10.1016/j.proeng.2011.12.005.

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34

Wood, T. J. "Optical Fibre Based Sensors for Aircraft Applications." Measurement and Control 22, no. 7 (September 1989): 206–9. http://dx.doi.org/10.1177/002029408902200704.

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35

Arumugam, Deepak, Premalatha Logamani, Santha Karuppiah, and Bharathi Thangaraj. "Performance Evaluation of PMSG for Aircraft Applications." Energy Procedia 117 (June 2017): 385–92. http://dx.doi.org/10.1016/j.egypro.2017.05.152.

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36

Zhoggui, R. "Computer applications in aircraft design and operation." Computer-Aided Design 21, no. 3 (April 1989): 189. http://dx.doi.org/10.1016/0010-4485(89)90104-8.

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37

Richardson, G. Y., S. C. Lei, and W. Tabakoff. "Erosion Testing of Coatings for V-22 Aircraft Applications." International Journal of Rotating Machinery 9, no. 1 (2003): 35–40. http://dx.doi.org/10.1155/s1023621x03000046.

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High-velocity (183 m/sec) sand erosion tests in a wind tunnel were conducted to evaluate developmental coatings from three separate companies under funding by the Navy's phase I small business innovative research program. The purpose of the coatings was to address a particular problem the V-22 tilt-rotor aircraft (Osprey) was having with regard to ingestion of sand particles by a titanium impeller that was associated with the aircraft's environmental control system. The three coatings that were deposited on titanium substrates and erosion-tested included (1) SixCy/DLC multilayers deposited by chemical vapor deposition (CVD); (2) WC/TaC/TiC processed by electrospark deposition; and (3) polymer ceramic mixtures applied by means of an aqueous synthesis. The erosion test results are presented; they provided the basis for assessing the suitability of some of these coatings for the intended application.

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38

Penney, R. W. "Collision avoidance within flight dynamics constraints for UAV applications." Aeronautical Journal 109, no. 1094 (April 2005): 193–99. http://dx.doi.org/10.1017/s0001924000000695.

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Abstract Avoiding collisions with other aircraft is an absolutely fundamental capability for semi-autonomous UAVs. However, an aircraft avoiding moving obstacles requires an evasive tactic that is simultaneously very quick to compute, compatible with the platform’s flight dynamics, and deals with the subtle spatio-temporal features of the threat. We will give an overview of a novel prototype method of rapidly generating smooth flight-paths constrained to avoid moving obstacles, using an efficient trajectory-optimisation technique. Obstacles are described in terms of simple geometrical shapes, such as ellipsoids, whose centres and shapes can vary with time. The technique generates a spatio-temporal trajectory which offers a high likelihood of avoiding the volume in space-time excluded by the predicted motion of each of the known obstacles. Such a flight-path could then be passed to the aircraft’s flight-control systems to negotiate the threat posed by the obstacles. Results from a demonstration implementation of the collision-avoidance technique will be discussed, including non-trivial scenarios handled well within 100ms on a 300MHz processor.

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39

Chávez, Javier Enrique Orna, Otto Fernando Balseca Sampedro, Jorge Isaías Caicedo Reyes, Diego Fernando Mayorga Pérez, Edwin Fernando Viteri Núñez, and Catalina Margarita Verdugo Bernal. "Análisis Y Diseño De Una Aeronave No Tripulada Para Uso Agrícola." European Scientific Journal, ESJ 13, no. 6 (February 28, 2017): 135. http://dx.doi.org/10.19044/esj.2017.v13n6p135.

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The present research proposes to diversify the use of unmanned aerial vehicles (UAV) with rotating wings for applications in the agricultural sector. For this we have analyzed and designed an unmanned aircraft. In first instance the applications of this type of aircraft in this sector were reviewed to determine possible design conditions that would aid in the sizing and design of the aircraft. Once the requirements had been determined, aerodynamic analysis was carried out to size up and launch the required power output for the craft. This in order to optimize the weight and autonomous fight time to finally design an aircraft prototype built in carbon fiber with the aid of fault theories as applied to composite materials. At the end of the research, an unmanned aircraft of 6 rotors, each with an installed power supply of 700W was designed. The aircraft has an autonomous flight time of 40 minutes without a payload, 20 minutes with a payload of 3Kg, and 8 minutes with a payload of 5Kg. The commercial application of these aircraft are the monitoring of land and fumigation in inaccessible areas.

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40

Qing, Xinlin, Wenzhuo Li, Yishou Wang, and Hu Sun. "Piezoelectric Transducer-Based Structural Health Monitoring for Aircraft Applications." Sensors 19, no. 3 (January 28, 2019): 545. http://dx.doi.org/10.3390/s19030545.

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Structural health monitoring (SHM) is being widely evaluated by the aerospace industry as a method to improve the safety and reliability of aircraft structures and also reduce operational cost. Built-in sensor networks on an aircraft structure can provide crucial information regarding the condition, damage state and/or service environment of the structure. Among the various types of transducers used for SHM, piezoelectric materials are widely used because they can be employed as either actuators or sensors due to their piezoelectric effect and vice versa. This paper provides a brief overview of piezoelectric transducer-based SHM system technology developed for aircraft applications in the past two decades. The requirements for practical implementation and use of structural health monitoring systems in aircraft application are then introduced. State-of-the-art techniques for solving some practical issues, such as sensor network integration, scalability to large structures, reliability and effect of environmental conditions, robust damage detection and quantification are discussed. Development trend of SHM technology is also discussed.

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41

Riba, Jordi-Roger, Álvaro Gómez-Pau, Manuel Moreno-Eguilaz, and Santiago Bogarra. "Arc Tracking Control in Insulation Systems for Aeronautic Applications: Challenges, Opportunities, and Research Needs." Sensors 20, no. 6 (March 16, 2020): 1654. http://dx.doi.org/10.3390/s20061654.

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Next generation aircrafts will use more electrical power to reduce weight, fuel consumption, system complexity and greenhouse gas emissions. However, new failure modes and challenges arise related to the required voltage increase and consequent rise of electrical stress on wiring insulation materials, thus increasing the risk of electrical arc appearance. This work performs a critical and comprehensive review concerning arc tracking effects in wiring insulation systems, underlying mechanisms, role of materials and possible mitigation strategies, with a special focus on aircraft applications. To this end an evaluation of the scientific and technological state of the art is carried out from the analysis of theses, research articles, technical reports, international standards and white papers. This review paper also reports the limitations of existing insulation materials, standard test methods and mitigation approaches, while identifying the research needs to comply with the future demands of the aircraft industry.

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42

Shanmugam, A., and T. Paul Robert. "Human factors engineering in aircraft maintenance: a review." Journal of Quality in Maintenance Engineering 21, no. 4 (October 12, 2015): 478–505. http://dx.doi.org/10.1108/jqme-05-2013-0030.

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Purpose – The purpose of this paper is to present a literature review on human factors in aircraft maintenance and to analyze and synthesize the findings in the literature on human factors engineering in aircraft maintenance. Design/methodology/approach – The review adopts a threefold approach: searching and collecting the scientific literature; sorting them on the basis of relevance and applications; and review of the scientific evidences. Broad areas of aircraft maintenance regulations are identified and each area was explored to study the level of scientific growth and publications. Notable theories, models and concepts are being summarized. Findings – Application of human factor principles in aviation spread beyond the technical arena of man-machine interface. The discipline has created a great impact on aircraft design, operations and maintenance. Its applications have percolated into design of aircraft maintenance facilities, task cards and equipment. Human factor concepts are being used for maintenance resource management. The principles are applied to shape the safety behavior and culture in aviation maintenance workplace. Nevertheless, the review unfolds immense potential for future research. Research limitations/implications – Research outcomes of non-aviation studies are also reviewed and consolidated to extend the applications to the aviation industry. Practical implications – This review would be a consolidated source of information confining to the physical aspect of human factors engineering in aircraft maintenance. It is intended to serve as a quick reference guide to the researchers and maintenance practitioners. Social implications – It brought out the benefits of adopting the principles of human factor engineering in aircraft maintenance. Application of human factor philosophy ensures enhanced safety in air transport, personal safety and well-being of maintenance personnel. Originality/value – This is a unique review based on aircraft maintenance regulations that are baseline performance standards made mandatory by regulatory authorities. Therefore, the review has been considered to be made on aircraft maintenance regulatory requirements that surpass corporate or competitive strategies in aviation maintenance organization.

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Wang, Hongyu, Xun Zhao, Hui Bai, Cunyue Lu, Baomin Zhang, and Cong Li. "Design of a Symmetrical Quad-rotor Biplane Tail-Sitter Aircraft without Control Surfaces and Experimental Verification." MATEC Web of Conferences 151 (2018): 04009. http://dx.doi.org/10.1051/matecconf/201815104009.

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This paper presents the design of a symmetrical quad-rotor biplane tail-sitter VTOL UAV (Vertical Take-off and Landing Unmanned Aerial Vehicle) which is composed of four rotors and two symmetrically mounted fixed wings. This aircraft achieves high accuracy in the attitude control and smooth flight mode transition with four rotors rather than the conventional VTOL UAVs using control surfaces. The proposal of angled rotor mounting is adopted to address the issue of insufficient yaw control authority. The layout of symmetrically mounted fixed wings makes the aircraft have capability of rapid bidirectional flight mode transition to improve maneuverability. To validate the performance of the aircraft, simulation and flight experiments are both implemented. These results show that the aircraft has a rapid yaw response under condition of the stable attitude control. In comparative experiment, it is shown that the aircraft is more flexible than other similar configuration of aircrafts. This symmetrical quad-rotor biplane tail-sitter VTOL UAV will have a wide range of potential applications in the military and civilian areas due to its superior performance..

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Ma, Zhen, and Xiyuan Chen. "Fiber Bragg Gratings Sensors for Aircraft Wing Shape Measurement: Recent Applications and Technical Analysis." Sensors 19, no. 1 (December 23, 2018): 55. http://dx.doi.org/10.3390/s19010055.

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The safety monitoring and tracking of aircraft is becoming more and more important. Under aerodynamic loading, the aircraft wing will produce large bending and torsional deformation, which seriously affects the safety of aircraft. The variation of load on the aircraft wing directly affects the ground observation performance of the aircraft baseline. To compensate for baseline deformations caused by wing deformations, it is necessary to accurately obtain the deformation of the wing shape. The traditional aircraft wing shape measurement methods cannot meet the requirements of small size, light weight, low cost, anti-electromagnetic interference, and adapting to complex environment at the same time, the fiber optic sensing technology for aircraft wing shape measurement has been gradually proved to be a real time and online dynamic measurement method with many excellent characteristics. The principle technical characteristics and bonding technology of fiber Bragg grating sensors (FBGs) are reviewed in this paper. The advantages and disadvantages of other measurement methods are compared and analyzed and the application status of FBG sensing technology for aircraft wing shape measurement is emphatically analyzed. Finally, comprehensive suggestions for improving the accuracy of aircraft wing shape measurement based on FBG sensing technology is put forward.

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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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Khusiafan, Firas J. "Use of KEVLAR ® 49 in Aircraft Components." Engineering Management Research 7, no. 2 (September 27, 2018): 14. http://dx.doi.org/10.5539/emr.v7n2p14.

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Aircraft industry is also finding its way to adapt on the increasing demand not only considering aircraft safety and customer requirements, but also on the increasing legislative requirements in terms of resource efficiency and gas emissions. This document explores Kevlar 49’s application on aircraft components and why this material is specifically selected for such applications above any other Kevlar type of materials. Its functions, properties, advantages and disadvantages are discussed together with some alternative materials in lieu of Kevlar 49. In order to provide credible information, literature search was conducted using significant keywords in Google Scholar and journal repository Deepdyve. Kevalr ® 49 is considered an exceptional material for reinforcement to produce aircraft components. It has high tensile strength, lightweight, inert on some conditions, stiff, and resilient. However, Kevlar’s has poor compressive strength, workability and is overly stiff for some applications. Another disadvantage is its cost, though it was shown to belong to a middle ranged material relative to carbon fiber and Boron. But overall, there are extensive applications in aircraft components that are now continuously using this material as reinforcement with other materials like carbon and boron to arrive on an ideal blend of product.

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Rypulak, Andrzej, and Sebastian Kuźmicz. "Use of augmented reality environment for practical aviation staff training." AUTOBUSY – Technika, Eksploatacja, Systemy Transportowe 19, no. 6 (June 30, 2018): 698–703. http://dx.doi.org/10.24136/atest.2018.159.

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The article describes the course of works aimed at creating a mobile application using Mobile Augmented Reality technology supporting the training process of personnel servicing aircraft in the field of pre-flight aircraft inspections. The requirements for the application, selection of programming tools and mobile imaging devices are presented. At the end of the article the results of tests of applications on various mobile devices and their conclusions are presented.

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Dyantyi, Noluntu, Adrian Parsons, Cordellia Sita, and Sivakumar Pasupathi. "PEMFC for aeronautic applications: A review on the durability aspects." Open Engineering 7, no. 1 (November 10, 2017): 287–302. http://dx.doi.org/10.1515/eng-2017-0035.

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AbstractProton exchange membrane fuel cells (PEMFC) not only offer more efficient electrical energy conversion, relative to on-ground/backup turbines but generate by-products useful in aircraft such as heat for ice prevention, deoxygenated air for fire retardation and drinkable water for use on-board. Consequently, several projects (e.g. DLR-H2 Antares and RAPID2000) have successfully tested PEMFC-powered auxiliary unit (APU) for manned/unmanned aircraft. Despite the progress from flying PEMFC-powered small aircraft with 20 kW power output as high as 1 000 m at 100 km/h to 33 kW at 2 558 m, 176 km/h [1, 2, 3], durability and reliability remain key challenges. This review reports on the inadequate understanding of behaviour of PEMFC under aeronautic conditions and the lack of predictive methods conducive for aircraft that provide real-time information on the State of Health of PEMFCs.Highlights: The main research findings are–To minimize performance loss due to high altitude and inclination by adjusting cathode stoichiometric ratio.–To improve quality of oxygen-depleted air by controlling operating temperature and stoichiometric ratio.–Need to devise real time prediction methods conducive for determining PEMFC SoH in aircraft.

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ENDO, MAKOTO. "Composites for Aircraft and Aerospace Applications." Sen'i Gakkaishi 70, no. 9 (2014): P—508—P—511. http://dx.doi.org/10.2115/fiber.70.p-508.

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Batina, John T. "Unsteady transonic algorithm improvements for realistic aircraft applications." Journal of Aircraft 26, no. 2 (February 1989): 131–39. http://dx.doi.org/10.2514/3.45734.

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