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Journal articles on the topic 'Aircraft application'

Author: Grafiati

Published: 4 June 2021

Last updated: 9 March 2023

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1

Yao, Jin Bo, Yue Ming Yang, Qin Yu Yang, Xiu Juan Liu, and Dun Jin. "Application of LED Light Source in the Flow Imaging." Applied Mechanics and Materials 380-384 (August 2013): 219–22. http://dx.doi.org/10.4028/www.scientific.net/amm.380-384.219.

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Aircraft in flight, such as supercooled water droplets encountered icing conditions suitable for the external environment, the relevant parts of the body will freeze, making the aircraft's aerodynamic performance deterioration, severe endanger flight safety, in addition, the aircraft parked in the open winter months , there will be icing, you need to clean up before takeoff. We should grasp the mechanism of aircraft icing, environmental factors and easy to freeze parts of the body. This paper presents a simulation using the wind tunnel icing device icing wind tunnel simulations can reproduce the real situation of aircraft icing, for guiding practice and got good results.

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Min, Kyung Ju, and Ho Sung Lee. "Composite Materials Characterization for Aircraft Application." Materials Science Forum 857 (May 2016): 169–73. http://dx.doi.org/10.4028/www.scientific.net/msf.857.169.

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Various composite materials have been developed for many of aircrafts feature and it is important to establish the composite materials characterization procedure based on the airworthiness requirement. Since properties of composites are a function of the properties of the constituent phases, their relative amounts, and processing methods, the overall processing must be carefully evaluated. This paper presents a composite materials evaluation procedure for composite aircraft and provide the effective statistical allowable to be approved by airworthiness certification agency. All material, specimens, fixtures and test results contained within this study were traceable and approved by the agency. In this study 8 different mechanical properties are obtained for 4 environmental conditions from 5 batches for robust sampling. By using modified coefficient of variation, the B-basis value of 0°tensile strength of carbon/epoxy unidirectional composite for elevated temperature/wet condition increases from 2,291MPa to 2,331MPa. The result would be applied to qualify domestic composite materials for aircraft within the level of a global standard.

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Alestra, Stephane, Cristophe Bordry, Cristophe Brand, Evgeny Burnaev, Pavel Erofeev, Artem Papanov, and Cassiano Silveira-Freixo. "Application of Rare Event Anticipation Techniques to Aircraft Health Management." Advanced Materials Research 1016 (August 2014): 413–17. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.413.

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Generally faults in complex technical systems (such as aircrafts) can be considered as rare events. In this paper we apply classification techniques to problem of rare events anticipation and demon-strate the approach to predictive maintenance of aircrafts through the real-world test cases from aircraft operations based on the data granted by AIRBUS.

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Broer, Agnes A. R., Rinze Benedictus, and Dimitrios Zarouchas. "The Need for Multi-Sensor Data Fusion in Structural Health Monitoring of Composite Aircraft Structures." Aerospace 9, no. 4 (March 30, 2022): 183. http://dx.doi.org/10.3390/aerospace9040183.

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With the increased use of composites in aircraft, many new successful contributions to the advancement of the structural health monitoring (SHM) field for composite aerospace structures have been achieved. Yet its application is still not often seen in operational conditions in the aircraft industry, mostly due to a gap between research focus and application, which constraints the shift towards improved aircraft maintenance strategies such as condition-based maintenance (CBM). In this work, we identify and highlight two key facets involved in the maturing of the SHM field for composite aircraft structures: (1) the aircraft maintenance engineer who requires a holistic damage assessment for the aircraft’s structural health management, and (2) the upscaling of the SHM application to realistic composite aircraft structures under in-service conditions. Multi-sensor data fusion concepts can aid in addressing these aspects and we formulate its benefits, opportunities, and challenges. Additionally, for demonstration purposes, we show a conceptual design study for a fusion-based SHM system for multi-level damage monitoring of a representative composite aircraft wing structure. In this manner, we present how multi-sensor data fusion concepts can be of benefit to the community in advancing the field of SHM for composite aircraft structures towards an operational CBM application in the aircraft industry.

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Wu, Yue. "Application of aluminum alloy in aircraft." Journal of Physics: Conference Series 2228, no. 1 (March 1, 2022): 012024. http://dx.doi.org/10.1088/1742-6596/2228/1/012024.

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Abstract From the perspective of aircraft manufacturing industry, aluminum alloy is a material with high practicability. It has the advantages of simple process, convenient processing, good forming performance, high durability and reliability, convenient maintenance, taking into account a series of advantages such as corrosion resistance, high strength, high stiffness and low cost. Applying it to the aircraft manufacturing industry can not only effectively control the cost of aircraft manufacturing, but also give full play to the material properties, improve the service performance of various aircraft components, improve the aircraft manufacturing level, and meet the development needs of the aircraft manufacturing industry. Based on the application case of aluminum alloy in aircraft, this paper studies the application of aluminum alloy in aircraft, and then puts forward the existing problems and solutions of aluminum alloy in aircraft, in order to provide valuable reference for the development of material field and aircraft manufacturing field in China.

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Bimo, Emanuel Ario, Eka Prabawa, Esra Kriahanta Sembiring, Oktaheroe Ramsi, Sjafrie Sjamsoeddin, Purnomo Yusgiantoro, and I. Wayan Midhio. "Application of AHP and PESTEL-SWOT Analysis on The Study of Military Amphibious Aircraft Acquisition Decision Making in Indonesia." Technium Social Sciences Journal 27 (January 8, 2022): 837–53. http://dx.doi.org/10.47577/tssj.v27i1.5414.

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Indonesia’s characteristics as an archipelagic state along with the increase of traditional and non-traditional threats in Indonesia require the ownership of military amphibious aircraft to oversee its maritime territories and perform logistics distribution to remote areas with minimum accessibility, especially its outermost islands. This study applied a combination of analytic hierarchy process (AHP), Political, Economic, Social, Techonology, Environment, and Legal (PESTEL) and Strength, Weakness, Opportunity, and Threat (SWOT) analysis to conduct a structured, systematic, measurable, and comprehensive decision-making process for selecting military amphibious aircraft and prescribe strategic recommendations on the acquisition plan. By using 3 criteria, 14 sub-criteria, and 3 alternative aircraft models, the results of AHP analysis showed that the Beriev Be-200 aircraft are the most preferred aircraft by the Indonesian users. The results of PESTEL-SWOT analysis show that good diplomatic relations between Indonesia and the manufacturer’s country of origin, users’ support to the plan, and user’s ability to adapt in operating and maintaining the aircraft support this decision. Meanwhile, limited fiscal capacity and domestic aircraft maintenance facilities/depots, as well as the risk of spare parts scarcity, have to be addressed for Indonesia to acquire its own military amphibious aircrafts.

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Loong, Ling Jin, Chockalingam Aravind Vaithilingam, Gowthamraj Rajendran, and Venkatkumar Muneeswaran. "Modelling and analysis of vienna rectifier for more electric aircraft applications using wide band-gap materials." Journal of Physics: Conference Series 2120, no. 1 (December 1, 2021): 012027. http://dx.doi.org/10.1088/1742-6596/2120/1/012027.

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Abstract This paper presents a comprehensive study on the switching effects of wide bandgap devices and the importance of power electronics in an aircraft application. Silicon (Si), silicon carbide (SiC), and gallium nitride (GaN) are wide bandgap devices that act as a power electronic switch in the AC-DC converter for More Electric Aircraft (MEA) applications. Therefore, it is important to observe their converting efficiency to identify the most suitable wide bandgap device among three devices for AC-DC converters in aircraft applications to provide high efficiency and high-power density. In this study, the characteristics of Si, SIC, and GaN devices are simulated using PSIM software. Also, this paper presents the performance of the Vienna rectifier for aircraft application. The Vienna rectifier using Si, SiC, and GaN devices are simulated using PSIM software for aircraft application. GaN with Vienna rectifier provides better performance than Si and SiC devices for aircraft applications among the three devices. It gives high efficiency, high power density, low input current THD to meet IEEE-519 standard, and high-power factor at mains.

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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

MITSUHASHI, Kiyomichi, Ryozo SEO, and Masahiko YOKOTA. "Optical Technology Application in Aircraft." Journal of the Japan Society for Aeronautical and Space Sciences 36, no. 408 (1988): 18–25. http://dx.doi.org/10.2322/jjsass1969.36.18.

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Gramopadhye, Anand K., David Kraus, Pradeep Rao, and Daniel Jebaraj. "Application of Advanced Technology to Team Training." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 40, no. 21 (October 1996): 1072–76. http://dx.doi.org/10.1177/154193129604002106.

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Research on civil aircraft inspection and maintenance has shown the importance of teamwork in completing aircraft inspection and maintenance tasks. Training has been identified as one of the primary intervention strategies in improving team performance. If training is to be successful, it is clear that we need to provide aircraft maintenance technicians (AMTs) with training tools to help enhance their team skills and improve team performance within the aircraft inspection/maintenance environment. In response to this need, this paper describes the development of a computer-based multimedia team training tool, the Aircraft Maintenance Team Training (AMTT) software.

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11

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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Kosacki, Kamil, and Andrzej Tomczyk. "APPLICATION OF ANALYTICAL REDUNDANCY OF MEASUREMENTS TO INCREASE THE RELIABILITY OF AIRCRAFT ATTITUDE CONTROL." Aviation 26, no. 3 (October 12, 2022): 138–44. http://dx.doi.org/10.3846/aviation.2022.17555.

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This article presents basic methodology and some algorithms for estimating attitude and heading angles of an unmanned or optionally piloted aircraft in the event of a partial failure of the on-board measurement systems. The aim of the research is to develop effective estimation algorithms of non-measurable aircraft state variables. Correlation between quantities describing kinematics of the aircraft’s movement in space were used. Properties of the estimation algorithms are illustrated by exemplary calculations using real data recorded during test flights of the optionally controlled MP-02A Czajka airplane. Quality of the estimated signals allows to continue flight in case of a non-catastrophic failure of the measurement systems. Developed algorithms are used in control systems designed at the Department of Avionics and Control of the Rzeszów University of Technology, dedicated to unmanned and optionally controlled light aircraft.

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Kamal, Ashraf M., and Alex Ramirez-Serrano. "Systematic Methodology for Aircraft Concept Development with Application to Transitional Aircraft." Journal of Aircraft 57, no. 1 (January 2020): 179–97. http://dx.doi.org/10.2514/1.c035437.

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14

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 (March 22, 2012): 714–33. http://dx.doi.org/10.1177/0954410012441430.

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A., Armaan, and Srinivas G. "In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines." International Journal of Engineering & Technology 7, no. 2 (May 23, 2018): 805. http://dx.doi.org/10.14419/ijet.v7i2.10910.

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Today the aircraft engine designing and development work is increasing drastically. Especially aircraft engines play a vital role in order to decide the aircrafts speed and its performance. Broadly turbojet, turboprop, turbo shaft and turbofan engines comes under the category of air breathing engines. Every engine has its own purpose and application. But modern aircrafts require much more advancements. Designing a new aircraft engine has been a really challenging task to the researchers. But giving a complete holistic view of aircraft engines and research gap would definitely help a lot to the new designers. Once identified the drawbacks of engine performance can be corrected in the future. For any new design of aircraft engine researchers are suggested to take Theoretical, Experimental and Numerical approaches. Therefore present paper makes an effort to review complete recent Theoretical, Experimental and Numerical approaches which are followed till date. Under all the three approaches all the air breathing engines have been clearly explained and solicited. The effort is to identify the gaps between different approaches which are hampering the process of engine development. The paper also gives the research gaps that need to be incorporated for effective performance enhancement of the aircraft engines for aeromechanical features.

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Afanas’ev, A. Yu, A. R. Karimov, and E. E. Studneva. "A Wheel Motor for Aircraft Application." Russian Aeronautics 62, no. 4 (October 2019): 529–34. http://dx.doi.org/10.3103/s1068799819040019.

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17

Radić, Vlado. "Composite materials application in aircraft industry." Vojnotehnicki glasnik 47, no. 6 (1999): 75–87. http://dx.doi.org/10.5937/vojtehg9904075r.

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18

POURNARAS, U. A. "MARINE APPLICATION OF AIRCRAFT PROPULSION SYSTEMS." Journal of the American Society for Naval Engineers 67, no. 4 (March 18, 2009): 933–44. http://dx.doi.org/10.1111/j.1559-3584.1955.tb03168.x.

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19

Friedrich, K. A., Josef Kallo, Johannes Schirmer, and Gerrit Schmitthals. "Fuel Cell Systems for Aircraft Application." ECS Transactions 25, no. 1 (December 17, 2019): 193–202. http://dx.doi.org/10.1149/1.3210571.

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20

Mohler, R. R., and R. R. Zakrzewski. "Suboptimal intelligent control: agile aircraft application." IEEE Transactions on Control Systems Technology 4, no. 4 (July 1996): 363–68. http://dx.doi.org/10.1109/87.508884.

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21

Khong, P. W., and B. L. Lim. "Spreadsheet application in aircraft structural analysis." Advances in Engineering Software 17, no. 1 (January 1993): 13–19. http://dx.doi.org/10.1016/0965-9978(93)90037-t.

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Anton, N., R. M. Botez, and D. Popescu. "Application of the weight function method on a high incidence research aircraft model." Aeronautical Journal 117, no. 1195 (September 2013): 897–912. http://dx.doi.org/10.1017/s0001924000008575.

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Abstract This paper assesses the application of a new method for system stability analysis, the weight functions method, to the longitudinal and lateral motions of a High Incidence Research Aircraft Model. The method consists of finding the number of weight functions that is 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; which should be negative for a stable model. The Aero-Data Model In Research Environment (ADMIRE) simulation, developed by the Swedish Defence Research Agency, was used for the aerodynamic aircraft modelling, with the following configurations: Mach number = 0·25, altitude = 500m, angle-of-attack [–10 to 30]°, elevon deflection angle [–30 to 30]°, canard deflection [0° and 25°] and rudder deflection angles [–30° and 30°]. These flight configurations were selected because they are among the flight conditions for Cat. II Pilot Induced Oscillation (PIO) criteria validation, performed on the FOI aircraft model presented in the PIO Handbook by the Group for Aeronautical Research and Technology in Europe, Flight Mechanics/Action Group 12. This aircraft model has a known instability for longitudinal and lateral motions and so a control law was introduced to stabilise its flight.

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Hebbar, Archana, and Abhay A. Pashilkar. "Application of Quantitative Measures for Analysing Aircraft Handling Qualities." Defence Science Journal 66, no. 1 (January 27, 2016): 3. http://dx.doi.org/10.14429/dsj.66.9196.

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<p>The ease and precision with which pilot is able to handle the designated task determines the aircraft’s handling qualities. Accordingly, the most common methodology for determining aircraft’s handling qualities is through pilot opinions or through questionnaires. These subjective means of analysis is not reliable as the sole source of judgments. Quantitative metrics to analyse the task difficulty based on pilot’s performance, supplemented with subjective decision, can provide better insight into pilot workload levels and in turn the aircraft’s handling qualities. The application of few objective performance measurement techniques to flight data of a high performance fighter aircraft is discussed. Pilot/aircraft’s performance under different configurations is analysed. Analysis results show that pilots usually tend to give more priority to pitch axis in case of dual axis tracking task. And pilots are therefore more aggressive in accomplishing pitch axis tracking task than in roll. Workload assessments were also performed by comparing the results of single axis tracking experiments conducted using a high fidelity flight simulator with the flight data. It is seen that pilot’s aggressiveness levels in controlling the roll control inceptor is significantly less, with improved tracking accuracy when exercised as the primary task.</p><p><strong>Defence Science Journal, Vol. 66, No. 1, January 2016, pp. 03-10, DOI: http://dx.doi.org/10.14429/dsj.66.9196</strong></p>

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Hockenhull, M. "Airworthiness aspects of new technologies: Interaction between aircraft structural dynamics and control systems." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 5 (May 1, 1998): 309–17. http://dx.doi.org/10.1243/0954410981532298.

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The application of electrical flight control systems to civil transport aircraft has directed attention to the need for improved airworthiness regulation. In this paper, the scope and interpretation of a new FAR/JAR Part 25 regulation in preparation is discussed, applicable to aircraft that have closed-loop control systems for flight control, load alleviation or stability augmentation, and have the potential to interact with the aircraft's structural dynamics.

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Qi, Jia Rui, Hua Kai Wei, Yan Li Li, and Li Han. "Application of the Laser Welding Technique in Aircraft Repair." Advanced Materials Research 887-888 (February 2014): 1269–72. http://dx.doi.org/10.4028/www.scientific.net/amr.887-888.1269.

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With the extensive use of new materials for aircraft structures, traditional riveting technology has been difficult to meet the demands of aircraft repairs. Laser welding of high concentration of energy is ideal technique for aircraft repair,because of its high welding speed, small heat-affected zone, perfect welding joint and small deformation of the welded structure. This article analyzes the application of laser welding technology in aeronautical aluminum alloys, titanium alloys and superalloys aircraft damage repair.

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Jiang, Xiaoting. "Fault Diagnosis of Civil Aircraft Electrical Power System Based on Triangular Fuzzy Number and Grey Relational Analysis." Journal of Physics: Conference Series 2258, no. 1 (April 1, 2022): 012070. http://dx.doi.org/10.1088/1742-6596/2258/1/012070.

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Abstract The stable operation of the aircraft electrical power system is closely related to aircraft’s function implementation and safety. Therefore, research on fault diagnosis of aircraft electrical system is important and necessary. This paper proposes a fault diagnosis method of civil aircraft power system based on triangular fuzzy number and grey relational analysis. For the purpose of obtaining complete data, it takes into account single fault symptom and historical data, and keeps the fuzzy feature from initial estimation of diagnosis scheme to the end. The example analysis shows that this method has feasibility and efficiency in practical application.

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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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Yang, Ming Hua, Guo Gang Wang, Ling Zhang, Xiao Ping Han, and Tao Liang. "Application Topsis Analysis on Aviation Anti-Submarine Aircraft Performance Evaluation." Advanced Materials Research 918 (April 2014): 84–88. http://dx.doi.org/10.4028/www.scientific.net/amr.918.84.

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Use Topsis law on aviation anti-submarine aircraft maneuvering performance evaluation for assessment, evaluation index set to establish anti-submarine aircraft maneuverability, the establishment of a data matrix samples to be evaluated, the results consistent with the actual situation. This method effectively reflects the comprehensive and objective maneuverability of the aircraft, aviation anti-submarine aircraft performance evaluation provides a new way.

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Martinez, Dan William, Michaela T. Espino, Honelly Mae Cascolan, Jan Lloyd Crisostomo, and John Ryan C. Dizon. "A Comprehensive Review on the Application of 3D Printing in the Aerospace Industry." Key Engineering Materials 913 (March 18, 2022): 27–34. http://dx.doi.org/10.4028/p-94a9zb.

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Additive manufacturing is a process wherein a three-dimensional object is created layer-by-layer. It offers adaptability to the geometrical complexity and customizability of the design, which is difficult to manufacture using conventional manufacturing. The aerospace industry is one of the sectors that first adopted additive manufacturing, particularly three-dimensional printing (3D printing) in the production of aircraft parts such as rocket engine components, oil fuel tanks, environmental control system ducting, combustor liner, custom cosmetic aircraft interior components, and unmanned aerial vehicle (UAV) components. The aircraft's most common materials used in the 3D printing prototype parts are acrylonitrile butadiene styrene (ABS) thermoplastic, carbon-fiber and thermoplastic composite, and nylon 12 using selective laser sintering, fused deposition modeling, or composite filament co-extrusion technology. One of the aerospace industry's challenges is ensuring the efficiency and quality of aircraft structural parts that typically require complicated manufacturing due to their complexity and variability of function. Additive manufacturing is seen to respond to this challenge by developing and prototyping 3D printed parts and exploring practical 3D printing technologies.

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Fera, Marcello, Raffaele Abbate, Mario Caterino, Pasquale Manco, Roberto Macchiaroli, and Marta Rinaldi. "Economic and Environmental Sustainability for Aircrafts Service Life." Sustainability 12, no. 23 (December 3, 2020): 10120. http://dx.doi.org/10.3390/su122310120.

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Aircrafts are responsible for a significant environmental impact mainly due to the air pollution caused by their motors. The use of composite materials for their production is a way to significantly reduce the weight of the structures and to maximise the ratio between the payload weight and the gasoline consumption. Moreover, the design phase has to consider the cost of different operations performed during the aircraft service life. During the entire life cycle, one of the main costs is the maintenance one. In the current literature, there is a lack of knowledge of methods for maintenance cost estimation in the aircraft industry; moreover, very few environmental assessment methods have been developed. Thus, the aim of this paper is to define a new method to support the aircraft design process; both the environmental and the economic dimensions have been included with the purpose of assessing the aircraft sustainability during its service life. A green index has been identified mixing the maintenance cost and an environmental parameter with the aim of identifying the greenest solution. A final practical application shows the feasibility and the simple application of the proposed approach.

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Fielding, C., and M. Lodge. "Stability and control of STOVL aircraft: The design of longitudinal flight control laws." Aeronautical Journal 104, no. 1038 (August 2000): 383–89. http://dx.doi.org/10.1017/s0001924000064022.

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Abstract Over the past three decades, the UK aerospace industry has carried out significant research into the development of short take-off and vertical landing (STOVL) technology, to enhance the performance and operation of the Harrier aircraft, and for possible application to future aircraft such as those being developed under the Joint Strike Fighter (JSF) programme. Some of this research has focused on aircraft handling and flight control for the transition between wing-borne and jet-borne flight. Following on from internal research at British Aircraft Corporation/British Aerospace (now part of BAE Systems) in the mid to late 1970s, further development work has been carried out in the 1980s and 90s in support of the UK’s Vectored thrust Advanced Aircraft flight Control (VAAC) Harrier and Integrated Flight and Propulsion Control System (IFPCS) programmes. This paper contains a short review of STOVL aircraft longitudinal flight control law design, and how basic feedback control schemes can be used to influence the aircraft’s response and hence its handling qualities.

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Yue, Siwen, Le Xiao, Jiaxin Li, and Nan Wang. "Research on application of knowledge graph for aircraft maintenance." Advances in Mechanical Engineering 14, no. 7 (July 2022): 168781322211074. http://dx.doi.org/10.1177/16878132221107429.

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Aircraft maintenance technology is related to flight safety. It is not only a significant guarantee for the safety of passengers’ lives and property but also an important means for airlines to reduce costs and improve profitability. This paper focuses on aircraft maintenance decision-making, analyzes the current situation and defects of maintenance decision-making, applies knowledge graph technology to this field, and constructs aircraft maintenance knowledge graph; through the character analysis of sample data and experimental comparison, the key factors affecting the accuracy of aircraft maintenance decisions are found; few-shot knowledge reasoning technology is introduced to improve the maintenance strategy reasoning algorithm. In the 737NG aircraft maintenance decision-making system of an airline, the feasibility and effectiveness of the method are verified, which provides strong support for flight safety.

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Bobin, A. V., V. A. Azarov, S. A. Bulgakov, and D. A. Savin. "Technique for recognition of aircrafts and radar traps in the control circuit of airspace control system based on neural network technology." Izvestiya MGTU MAMI 7, no. 1-4 (July 10, 2013): 124–30. http://dx.doi.org/10.17816/2074-0530-67843.

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The paper proposes a method for building of automatic recognizers of aircrafts on a set of radar measurements based on the cascade of multilayer feedforward neural networks. The practical application of this technique in recognizing of three types of aircraft is presented as well.

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Kachel, Stanisław. "Control Curves Method of Airframe Geometry Modeling." Solid State Phenomena 199 (March 2013): 279–84. http://dx.doi.org/10.4028/www.scientific.net/ssp.199.279.

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The paper presents the methodological approach to development of curves by selection of driving parameters with the application of the method to designing and reproduction of aircraft surfaces on the examples of both newly designed aircrafts and the ones that are already in service. The major assumptions are outlined that are necessary to develop the mathematical model of driving curves and surfaces, these assumptions served as the basis to draw up the relevant algorithms and to convert them to routines of the GRIP (Graphics Interactive Programming) language that is a part of the CAD/CAM/CAE Unigraphics system. These algorithms include the newly developed tool dedicated to design aircraft components and provided with inputs to the multi-criteria synthesis of the aerodynamic profiles of aircrafts. The study comprises also the assumptions to the newly developed algorithms dedicated to modelling of components incorporated into aircraft structures, these algorithms have been successfully implemented by the author.

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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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Zhang, Wen Guang, Guo Min Lin, Miao Shang, and Fei Zhou. "The Application of Modern Sealing Technology in Aircraft." Advanced Materials Research 912-914 (April 2014): 810–13. http://dx.doi.org/10.4028/www.scientific.net/amr.912-914.810.

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With the development of modern aircraft industry, the structure of the plane becoming more and more complex, and the sealing of parts is becoming stricter. Traditional sealing technology began gradually revealed its deficiencies. In this paper, the sealing method of the hydraulic system, oil tank, window and cover of the aircraft is introduced in details. The effective ways to seal have been put forward, and it also offering technical reference to the aircraft parts manufacturer.

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Wu, Chunhui, and Stephane Redonnet. "Prediction of Aircraft Noise Impact with Application to Hong Kong International Airport." Aerospace 8, no. 9 (September 15, 2021): 264. http://dx.doi.org/10.3390/aerospace8090264.

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As part of a collective research effort towards greener aviation, the present study focuses on the noise impact of aircraft operations around major airports. To this end, an aircraft noise prediction platform is developed, which relies on state-of-the-art functionalities as well as more specific, innovative features. Originally built upon the Aircraft Noise and Performance (ANP) database and its Noise–Power–Distance (NPD) table, the method is further refined to alleviate most of their inherent limitations (e.g., standardized and simplified aircraft noise scenarios). The resulting aircraft noise prediction platform is validated against benchmark cases of increasing complexity, being then applied to real-life situations involving actual aircraft operations around Hong Kong International Airport (HKIA). Specific comparative analyses are conducted, which allow highlighting the variability of the noise impact by aircraft, depending on their type (A330, B777) and/or operational conditions (power settings, meteorological conditions, routes, banks, etc.). The study delivers insightful outcomes, whether phenomenological (aircraft noise impact) or methodological (aircraft noise prediction). As a by-product, it illustrates how noise prediction methods/platforms such as the present one may help in guiding the further expansion of airport operations and/or infrastructures (as is currently the case with HKIA).

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Ding, Liquan, Dujuan Xue, Zhiyang Dai, Wei Liu, and Yiqing Sui. "Application of GOA-GDOP in aircraft collaborative detection." ITM Web of Conferences 45 (2022): 01032. http://dx.doi.org/10.1051/itmconf/20224501032.

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The cooperative detection of aircraft has been widely concerned by scholars at home and abroad in recent years. This paper mainly studies the positioning accuracy of the sensor-carrying aircraft in collaborative detection. By using Grasshopper Optimisation Algorithm (GOA), Taking Geometrical Dilution of Precision (GDOP) as the objective function, the relative position relationship between aircraft is determined, the optimal detection configuration is planned, and the feasibility of the algorithm is analyzed under limited flight area conditions, the positioning accuracy of collaborative detection is further improved.

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Улитенко, Ю. А. "ВІДНОСНИЙ КРИТЕРІЙ ЕФЕКТИВНОСТІ ВИСОКОШВИД-КІСНОГО ЛІТАЛЬНОГО АПАРАТА." Open Information and Computer Integrated Technologies, no. 85 (July 29, 2019): 151–66. http://dx.doi.org/10.32620/oikit.2019.85.09.

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Development of perspective high-speed aircrafts inseparably linked with level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircrafts are increase speed and flight height. With each new generation of turbojet bypass engine with afterburner their specific thrust and a specific impulse are increase, also application of high technologies raises leads to substantial growth of the engine cost too. At the same time existing engines design has the big reserves for modernization. For a quantitative assessment of the degree of influence of the new technical solution on the quality of the task performance by the aviation complex, criteria (indicators) of efficiency are used. However, it is not possible to find a direct functional dependence of the overall criterion of the effectiveness of the aviation complex on the technical and operational characteristics, conditions of use of a high-speed aircraft. The purpose of this work is to develop a methodology for determining the economic criterion for assessing the degree of influence of a new technical solution on the quality of the task performance by the aviation complex (the value of the integrated performance criterion). The text of the paper provides an analysis of recent research and publications. The developed relative criterion of the efficiency of a high-speed aircraft makes it possible to accomplish the goal set, as well as to estimate the costs at the cost of which the final result is achieved. It is shown that boosting engines with water injection has some advantage over other options for increasing the thrust of high-speed aircraft engines. The application of the obtained results can be used to substantiate new technical solutions and establish their impact on the quality of the task performance by the aviation complex, as well as reduce the time to create competitive high-speed aircraft.

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Gershon, B., and I. Eldror. "Research and Application of Superplastic Forming Titanium Alloys for Commercial Aircraft Parts." Materials Science Forum 475-479 (January 2005): 3047–50. http://dx.doi.org/10.4028/www.scientific.net/msf.475-479.3047.

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Titanium alloys sheets have many attractions for the aerospace industry owing to their high strength, low density, heat resistance and other useful properties. Many of the sheet metal structures in airframes have complex shapes and compound curvatures with intricate details. Superplastic forming (SPF), a most recent advancement in titanium sheet forming technology, exploits the excellent characteristic of >1000% elongation potential for the fabrication of complex configurations not achievable by conventional methods. SPF technology can also reduce manufacturing cost by shortening the preparation time, eliminating the need for extensive welding or other joining methods and by reducing the number of manufacturing steps. Consequently, high profit margins may be achieved in serial aircraft production. This paper outlines the research at Israel Aircraft Industries (IAI) of SPF technology and its application in producing complex-shape Ti sheet parts for the new IAI commercial aircrafts, models “G-150” and “G-200”. Examples of both actual and experimental parts are given, together with details of the manufacturing parameters employed. An economical analysis is also included.

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Harker, Blaine M., J. M. Downing, Michael M. James, and Kent L. Gee. "Application of a crackle-based adjustment to military aircraft noise levels." Journal of the Acoustical Society of America 152, no. 4 (October 2022): A222. http://dx.doi.org/10.1121/10.0016079.

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Crackle is a sound quality that can be identified in the jet noise of tactical aircraft and may contribute to perceived community noise levels in the vicinity of military airports. Crackle has been linked to the skewness of the waveform pressure derivative, or derivative skewness. Recently, listener trials quantified the perceptual relationships between derivative skewness, loudness, and annoyance. We present a method to calculate a crackle-based adjustment to aircraft noise levels derived from annoyance. This crackle adjustment is applied to a large sample set of community noise measurements in the vicinity of departing military aircraft. Finally, we develop an empirical model to apply crackle-based adjustments to community noise models of tactical aircraft departures. The empirical model allows airport planners to examine how aircraft flight paths, altitudes, and engine conditions affect the crackle adjustment, which is significant in the airport's immediate vicinity and along the aircraft departure path. [Work funded by an AFRL SBIR.]

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Jafernik, Henryk, Janusz Ćwiklak, Kamil Krasuski, and Jarosław Kozuba. "Application of IGS Products for Air Navigation." Annual of Navigation 24, no. 1 (December 1, 2017): 285–300. http://dx.doi.org/10.1515/aon-2017-0021.

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Abstract Single Point Positioning (SPP) method is widely used in air, marine, and land navigation to determine the user’s position in real time and post factum. A typical accuracy for this method of determining the user’s position in the static mode is approximately 10 meters. In air operations, the SPP method accuracy can be several times lower and that may cause problems with precise positioning of an aircraft. The authors of this article presented preliminary results of research concerning aircraft positioning in the kinematic mode based on GPS observations. For this purpose, an in-flight experiment, in which a Cessna 172 aircraft was used, was performed at the airport in Mielec, Poland. The aircraft was equipped with a dual-frequency Topcon TPS HiperPro receiver, which was recording satellite observations with 1-second interval. The aircraft position was determined using the least-squares method (LSM) in the RTKLIB (RTKPOST module) software. Two research tests were performed within the scope of the experiment, i.e. in test I the aircraft position was determined on the basis of raw GPS observations and the broadcast ephemeris data whereas in test II precision products of the IGS were used, such as: precise ephemeris SP3, DCB hardware delay, clock bias data of GPS satellites and receivers in the CLK format, data of the ionosphere maps based on IONEX format, and phase center calibration of GPS satellites and receivers in the ANTEX format. The use of the IGS precision products improved the accuracy of the X coordinate to 1 m, Y to 0.7 m and Z to 1.3 m. On the basis of tests I and II, an additional RMS-3D parameter was determined, whose mean value was 4 m.

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Kirschen, Philippe G., Martin A. York, Berk Ozturk, and Warren W. Hoburg. "Application of Signomial Programming to Aircraft Design." Journal of Aircraft 55, no. 3 (May 2018): 965–87. http://dx.doi.org/10.2514/1.c034378.

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Zahorski, Tomasz. "APPLICATION OF SOLID PAINT COATING ON AIRCRAFT." Journal of KONES. Powertrain and Transport 20, no. 4 (January 1, 2015): 493–99. http://dx.doi.org/10.5604/12314005.1137865.

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Chincholikar, Somesh A. "Non-Aircraft Application of Mini Jet Engine." International Journal for Research in Applied Science and Engineering Technology 7, no. 5 (May 31, 2019): 2087–88. http://dx.doi.org/10.22214/ijraset.2019.5348.

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Wigdorowitz, B. "Application of linearization analysis to aircraft dynamics." Journal of Guidance, Control, and Dynamics 15, no. 3 (May 1992): 746–50. http://dx.doi.org/10.2514/3.20900.

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Starke, E. A., and J. T. Staley. "Application of modern aluminum alloys to aircraft." Progress in Aerospace Sciences 32, no. 2-3 (1996): 131–72. http://dx.doi.org/10.1016/0376-0421(95)00004-6.

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Amin, S. M., E. Y. Rodin, and Y. Wu. "Neurocontrol of an aircraft: Application to windshear." Mathematical and Computer Modelling 22, no. 1 (July 1995): 63–78. http://dx.doi.org/10.1016/0895-7177(95)00101-7.

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王, 逾涯. "Application of Photogrammetry in Aircraft Components Repair." Mechanical Engineering and Technology 09, no. 06 (2020): 562–69. http://dx.doi.org/10.12677/met.2020.96060.

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Marcos, Andrés, and Gary J. Balas. "A robust integrated controller/diagnosis aircraft application." International Journal of Robust and Nonlinear Control 15, no. 12 (2005): 531–51. http://dx.doi.org/10.1002/rnc.1010.

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