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Journal articles on the topic 'Aircraft engineering'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Liang, Di, and Sheng Jing Tang. "The Design and Development of the Aerodynamic Engineering Prediction Software for Aircrafts." Applied Mechanics and Materials 543-547 (March 2014): 3136–40. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.3136.

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Aerodynamic analysis and calculation are very important parts in the aircraft design, and aerodynamic engineering prediction is widely used in the aircraft preliminary design stage. However, traditional aerodynamic engineering prediction causes heavy computation and is time-consuming. The developed software such as DATCOM has the disadvantages of complicated operation and black box structure. To overcome the disadvantages above, we develop the software for aerodynamic engineering prediction based on the aerodynamic characteristics and prediction for aircrafts. There are three parts in this software which are database, calculation module and user interface. The software is verified by a numerical example of one aircraft, and compares with the data of Computational Fluid Dynamics (CFD) and the wind tunnel test. The results show that the calculated results of the aerodynamic engineering prediction and CFD are basically consistent, and the software is able to meet the accuracy demand in the preliminary design phase of the aircraft.

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2

Olugbeji, Jemitola P., Okafor E. Gabriel, and Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft." Recent Patents on Engineering 14, no. 2 (October 29, 2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.

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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exist on the methodology for optimizing the wing thickness to chord ratio of the Box wing aircraft configurations. Methods: To address this gap, in this work, a two stage optimization methodology based on gradient search algorithm and regression analysis was implemented for the optimization of Box wing aircrafts wing thickness to chord ratio. The first stage involved optimizing the All Up Mass (AUM), Direct Operating Cost (DOC) and Zero Lift Drag Coefficients (CDO), with respect to the aft and fore sweep angle for some selected τ values. At the second stage, a suitability function (γ) was optimized with respect to the aft and fore sweep angle for some selected τ values. A comparative study was further carried out using the proposed methodology on similar size cantilever wing aircraft. Results: From the result, an optimal τ value was reached. Also the τ value for the cantilever aircraft found based on the proposed methodology was similar to the true τ value of the adopted aircraft, thereby validating the methodology. Conclusion: Based on the optimal τ value reached from this work, the Box wing aircraft are suitable for thin airfoils.

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3

Rogalski, Tomasz, and Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM." Aviation 9, no. 2 (June 30, 2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.

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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft should be equipped with fly‐by‐wire control systems, and there are no clear, straight, rules rate and describe the handling qualities of small airplanes with fly‐by‐wire control systems. This paper presents a methodology created by the authors that classifies and compares the handling qualities of general aviation aircraft equipped with fly‐by‐wire control systems. It takes into consideration two parameters: pilot's effort during realization of ordered tasks and precision of his control.

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4

Sun, Ji Ku, Zong Jie Cao, De Jian Sun, and Yi Chen. "Characteristic of Corrosive Damages about Aircraft Structures in Service." Applied Mechanics and Materials 543-547 (March 2014): 316–19. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.316.

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In engineering practices, aircraft structures have been damaged due to the structural corrosion, the corrosive problem of aircrafts needs to call high attentions for researchers because aircraft structures are composed of metals and compound metals. In this paper, corrosion problems and structural reliability of aircraft structures are discussed. Corrosion morphology and mechanism of aircraft structures are analyzed based on metal corrosion theory. The characteristics of the various types of corrosions of aircraft structures have been enumerated. The effect of environments in corrosion process of aircraft structures is studied. The law of corrosion developed at aircraft structural parts or materials is summarized. This research contributes to improving professionals capacity of corrosion prevention and control. It also provides technical support for aircraft maintainers.

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Bendall, Keith C. "Metallic materials for aircraft engineering." Aircraft Engineering and Aerospace Technology 67, no. 5 (May 1995): 5–7. http://dx.doi.org/10.1108/eb037595.

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6

Jackson, Scott. "SYSTEMS ENGINEERING FOR COMMERCIAL AIRCRAFT." INCOSE International Symposium 7, no. 1 (August 1997): 36–43. http://dx.doi.org/10.1002/j.2334-5837.1997.tb02151.x.

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7

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

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ABSTRACTA novel image-based method is presented in this paper to estimate the poses of commercial aircrafts in a runway end safety area. Based on the fact that similar poses of an aircraft will have similar geometry structures, this method first extracts features to describe the structure of an aircraft's fuselage and aerofoil by RANdom Sample Consensus algorithm (RANSAC), and then uses the central moments to obtain the aircrafts’ pose information. Based on the proposed pose information, a two-step feature matching strategy is further designed to identify an aircraft's particular pose. In order to validate the accuracy of the pose estimation and the effectiveness of the proposed algorithm, we construct a pose database of two common aircrafts in Asia. The experiments show that the designed low-dimension features can accurately capture the aircraft's pose information and the proposed algorithm can achieve satisfied matching accuracy.

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8

Sobolev, L. B. "Economic aspects of military aircraft engineering." Economic Analysis: Theory and Practice 17, no. 4 (April 27, 2018): 600–613. http://dx.doi.org/10.24891/ea.17.4.600.

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9

Danil’chenko, V. P., and M. V. Skiba. "Minimization of aircraft engineering enterprise losses." Russian Aeronautics (Iz VUZ) 50, no. 2 (June 2007): 199–203. http://dx.doi.org/10.3103/s1068799807020146.

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10

Padfield, G. D. "Flight handling qualities." Aeronautical Journal 110, no. 1104 (February 2006): 73–84. http://dx.doi.org/10.1017/s0001924000001020.

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Abstract This paper describes the methodology and key results from the first three years of delivery of ‘Flight Handling Qualities’ (FHQ), a problem-based-learning core module for fourth year Master of Engineering (MEng) undergraduates in Aerospace Engineering and optional module for the Systems Engineering MSc Programme, at the University of Liverpool. The module aim is to equip students with the skills and knowledge required to tackle aircraft handling qualities (HQs) and related ‘whole aircraft’ problems. Students are presented with the theory of handling qualities engineering in a series of interactive lectures. The students work in teams of four or five and undertake a number of team-building exercises throughout the first semester. Teams are presented with the idea that the aircraft with its handling qualities is the focus for knowledge acquisition and skills development. Each team is given the task of assessing and quantifying the HQs of a particular aircraft in a particular role, and then developing fixes to any handling deficiencies they identify; the current aircraft include the Wright Flyer, Grob 115, Black Hawk, Bo-105 and XV-15. Teams write an interim report at the end of the first term and a final report at the end of the second term, showing how they have assessed the aircraft, developed solutions to the problems and made recommendations concerning the aircraft’s suitability in the defined role. The reports also address the technical feasibility and economic viability of the proposed upgrades. The teams present their work to mock ‘customers’ (group of staff, another student team, visiting Industrialists) with the objective of demonstrating that the aircraft is now fit for the role. Each individual student maintains a ‘personal learning journal’, in which they document the development of their understanding of handling qualities and, more general, transferable skills. The module is designed to enable students to engage in all elements of the conceive-design-implement-operate (CDIO) cycle.

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11

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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12

Zhen, Ziyang, Ju Jiang, Xinhua Wang, and Kangwei Li. "Modeling, control design, and influence analysis of catapult-assisted take-off process for carrier-based aircrafts." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 13 (June 20, 2017): 2527–40. http://dx.doi.org/10.1177/0954410017715278.

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This paper addresses the problems of modeling, control design, and influence analysis of the steam catapult-assisted take-off process of the carrier-based aircrafts. The mathematical models of the carrier-based aircraft, steam catapult, landing gears, and the environmental factors including deck motion and bow airflow have been established to express the aircraft dynamics in the take-off process. An engineering method based automatic flight control system has been designed, which is divided into the longitudinal channel and lateral channel. The influences of the preset control surface, ship deck motion, ship bow airflow, and automatic flight control system system are tested by a series of simulations. The simulation results show that the elevator angle preset is necessary in the stage of accelerated running on the ship deck and the deck motion is the most important factor for safe take-off, while the ship bow airflow is beneficial for climbing up of the aircraft. The automatic flight control system gives the guarantee of safety and performance in the take-off process of the carrier-based aircraft.

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13

Pinheiro Melo, Sofia, Alexander Barke, Felipe Cerdas, Christian Thies, Mark Mennenga, Thomas S. Spengler, and Christoph Herrmann. "Sustainability Assessment and Engineering of Emerging Aircraft Technologies—Challenges, Methods and Tools." Sustainability 12, no. 14 (July 14, 2020): 5663. http://dx.doi.org/10.3390/su12145663.

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Driven by concerns regarding the sustainability of aviation and the continued growth of air traffic, increasing interest is given to emerging aircraft technologies. Although new technologies, such as battery-electric propulsion systems, have the potential to minimise in-flight emissions and noise, environmental burdens are possibly shifted to other stages of the aircraft’s life cycle, and new socio-economic challenges may arise. Therefore, a life-cycle-oriented sustainability assessment is required to identify these hotspots and problem shifts and to derive recommendations for action for aircraft development at an early stage. This paper proposes a framework for the modelling and assessment of future aircraft technologies and provides an overview of the challenges and available methods and tools in this field. A structured search and screening process is used to determine which aspects of the proposed framework are already addressed in the scientific literature and in which areas research is still needed. For this purpose, a total of 66 related articles are identified and systematically analysed. Firstly, an overview of statistics of papers dealing with life-cycle-oriented analysis of conventional and emerging aircraft propulsion systems is given, classifying them according to the technologies considered, the sustainability dimensions and indicators investigated, and the assessment methods applied. Secondly, a detailed analysis of the articles is conducted to derive answers to the defined research questions. It illustrates that the assessment of environmental aspects of alternative fuels is a dominating research theme, while novel approaches that integrate socio-economic aspects and broaden the scope to battery-powered, fuel-cell-based, or hybrid-electric aircraft are emerging. It also provides insights by what extent future aviation technologies can contribute to more sustainable and energy-efficient aviation. The findings underline the need to harmonise existing methods into an integrated modelling and assessment approach that considers the specifics of upcoming technological developments in aviation.

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14

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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15

Sakaue, Hirotaka. "Special Issue: Deicing and Anti-Icing of Aircrafts." Aerospace 8, no. 3 (March 10, 2021): 72. http://dx.doi.org/10.3390/aerospace8030072.

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16

Магдин, Александр, Aleksandr Magdin, Алексей Припадчев, Aleksey Pripadchev, Александр Горбунов, and Aleksandr Gorbunov. "ALGORITHM OF AIRCRAFT TARGET CHOICE." Bulletin of Bryansk state technical university 2019, no. 10 (November 7, 2019): 48–54. http://dx.doi.org/10.30987/article_5db95e85e569b8.29571093.

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The work purpose consists in the algorithm development for aircraft target choice. The investigations were carried out with the use of methods of a system analysis, a theory of modeling, mathematical methods, methods of object-directed programming. In farms when agricultural area processing it is advisable to use an aircraft. A choice is argued by aircraft advantages over the ground-based means of agricultural area processing which consist in mobility and a processing speed and also in the absence of mechanical impact upon the growth of the area under processing. In the paper there is offered a procedure for a choice of an aircraft type for processing different agricultural area on the criterion of minimum costs. An investigation novelty consists in the use of the algorithm developed with reference to the choice of agricultural aircraft for chemical agent distribution depending on agricultural area dimensions and a landscape. Conclusion: the developed algorithm for a target choice of an aircraft allows carrying out a complex analysis both of aircrafts (characters, engineering and flight characteristics) on the basis of costs minimum for an agricultural area processing, and a geometry (dimensions and configuration) of the areas to be subjected to processing. In the paper as an example there is carried out a choice of an aircraft for processing a set of areas with specified dimensions.

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17

NAKAZATO, Kimiya. "To Secure Aircraft Safety Engineering Judgement for Preventive Action to Promote Aircraft Safety." Journal of the Society of Mechanical Engineers 111, no. 1070 (2008): 47–50. http://dx.doi.org/10.1299/jsmemag.111.1070_47.

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18

Rothwell, A. "Aircraft structures for engineering students (3rd edition)." Aircraft Design 4, no. 2-3 (June 2001): 147–49. http://dx.doi.org/10.1016/s1369-8869(01)00004-0.

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19

Krammer, J., O. Sensburg, J. Vilsmeier, and G. Berchtold. "Concurrent engineering in design of aircraft structures." Journal of Aircraft 32, no. 2 (March 1995): 423–30. http://dx.doi.org/10.2514/3.46733.

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20

Bendall, Keith C. "Selection of copper alloys for aircraft engineering." Aircraft Engineering and Aerospace Technology 69, no. 4 (August 1997): 328–31. http://dx.doi.org/10.1108/00022669710178001.

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21

Kablov, E. N. "Materials and chemical technologies for aircraft engineering." Herald of the Russian Academy of Sciences 82, no. 3 (May 2012): 158–67. http://dx.doi.org/10.1134/s1019331612030069.

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22

Udroiu, Razvan. "Research regarding reverse engineering for aircraft components." MATEC Web of Conferences 94 (2017): 01012. http://dx.doi.org/10.1051/matecconf/20179401012.

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23

Jackson, Scott. "Systems Engineering In the Commercial Aircraft Domain." INSIGHT 1, no. 2 (March 1998): 6–7. http://dx.doi.org/10.1002/inst.1998126.

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24

Krus, Petter. "1.5.2 Systems Engineering in Aircraft System Design." INCOSE International Symposium 11, no. 1 (July 2001): 723–28. http://dx.doi.org/10.1002/j.2334-5837.2001.tb02363.x.

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25

Grishkevich, P. M., A. S. Govorkov, and M. S. Yakhnenko. "Engineering analysis of composite aircraft beam element." Journal of Physics: Conference Series 1661 (November 2020): 012207. http://dx.doi.org/10.1088/1742-6596/1661/1/012207.

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26

Ramalingam, Balakrishnan, Vega-Heredia Manuel, Mohan Rajesh Elara, Ayyalusami Vengadesh, Anirudh Krishna Lakshmanan, Muhammad Ilyas, and Tan Jun Yuan James. "Visual Inspection of the Aircraft Surface Using a Teleoperated Reconfigurable Climbing Robot and Enhanced Deep Learning Technique." International Journal of Aerospace Engineering 2019 (September 12, 2019): 1–14. http://dx.doi.org/10.1155/2019/5137139.

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Aircraft surface inspection includes detecting surface defects caused by corrosion and cracks and stains from the oil spill, grease, dirt sediments, etc. In the conventional aircraft surface inspection process, human visual inspection is performed which is time-consuming and inefficient whereas robots with onboard vision systems can inspect the aircraft skin safely, quickly, and accurately. This work proposes an aircraft surface defect and stain detection model using a reconfigurable climbing robot and an enhanced deep learning algorithm. A reconfigurable, teleoperated robot, named as “Kiropter,” is designed to capture the aircraft surface images with an onboard RGB camera. An enhanced SSD MobileNet framework is proposed for stain and defect detection from these images. A Self-filtering-based periodic pattern detection filter has been included in the SSD MobileNet deep learning framework to achieve the enhanced detection of the stains and defects on the aircraft skin images. The model has been tested with real aircraft surface images acquired from a Boeing 737 and a compact aircraft’s surface using the teleoperated robot. The experimental results prove that the enhanced SSD MobileNet framework achieves improved detection accuracy of aircraft surface defects and stains as compared to the conventional models.

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Götten, F., D. F. Finger, M. Havermann, C. Braun, M. Marino, and C. Bil. "Full configuration drag estimation of short-to-medium range fixed-wing UAVs and its impact on initial sizing optimization." CEAS Aeronautical Journal 12, no. 3 (June 10, 2021): 589–603. http://dx.doi.org/10.1007/s13272-021-00522-w.

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AbstractThe paper presents the derivation of a new equivalent skin friction coefficient for estimating the parasitic drag of short-to-medium range fixed-wing unmanned aircraft. The new coefficient is derived from an aerodynamic analysis of ten different unmanned aircraft used for surveillance, reconnaissance, and search and rescue missions. The aircraft is simulated using a validated unsteady Reynolds-averaged Navier Stokes approach. The UAV’s parasitic drag is significantly influenced by the presence of miscellaneous components like fixed landing gears or electro-optical sensor turrets. These components are responsible for almost half of an unmanned aircraft’s total parasitic drag. The new equivalent skin friction coefficient accounts for these effects and is significantly higher compared to other aircraft categories. It is used to initially size an unmanned aircraft for a typical reconnaissance mission. The improved parasitic drag estimation yields a much heavier unmanned aircraft when compared to the sizing results using available drag data of manned aircraft.

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Zhang, Yongjie, Kang Cao, Ke Liang, and Yongqi Zeng. "Study on the evaluation model of serialized civil aircraft commonality index based on fuzzy set theory." Journal of Intelligent & Fuzzy Systems 40, no. 6 (June 21, 2021): 11539–58. http://dx.doi.org/10.3233/jifs-202749.

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Commonality, a typical commercial feature of serialized civil aircraft study and development, refers to a series of methods of reusing and sharing assets, which were developed based on broad similarity. The common design of serialized civil aircraft is capable of maximally saving R&D, production, operation, and disposal. To maximize the total benefits of manufacturers and operators, the common design of serialized civil aircrafts primarily exploits the commercial experience of serialized products in other fields (e.g., automobiles and mobile phones), whereas a scientific index system and quantitative evaluation model has not been formed. Accordingly, this study proposes a new civil aircraft commonality index evaluation model in accordance with fuzzy set theory and methods. The model follows two branches, i.e., attribute commonality and structural commonality, to develop a multi-level civil aircraft commonality index system. The proposed model can split the commonality into six commonality sub-intervals and build the corresponding standard fuzzy set with the characteristic attribute parameters of the civil aircraft as the elements. Next, based on considerable civil aircraft sample data, a fuzzy test is designed to yield the membership function of the fuzzy set. Thus, a model of evaluating civil aircraft commonality is constructed, taking the characteristic parameters of the civil aircraft to be evaluated as input, and selecting the degree of commonality of each level as output. Lastly, this study employs the evaluation model to evaluate the commonality of Boeing 757-200 with other civil aircrafts. Furthermore, the evaluated results well explain the actual situation, which verifies the effectiveness and practicability of the proposed model.

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29

Hsu, J. C. "Using system engineering on an aircraft improvement project." Aeronautical Journal 110, no. 1114 (December 2006): 813–20. http://dx.doi.org/10.1017/s0001924000001688.

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A complete system engineering process is applied to a pilot project that will determine the initial deployment of the system engineering process for future projects. It was a challenge to complete the entire systems engineering process to include project team utilisation of system engineering tools in such a short time span. Therefore, systems engineering products had to be useful and productive to the project. The system requirements definition, quality function deployment (QFD) evaluation, trade study, risk identification and risk mitigation processes were completed in a timely manner and assisted in the system eequirements, system design and preliminary design reviews successfully.

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Lin, Fusheng, and Guang Meng. "Study on the Dynamics of a Rotor in a Maneuvering Aircraft." Journal of Vibration and Acoustics 125, no. 3 (June 18, 2003): 324–27. http://dx.doi.org/10.1115/1.1576422.

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This paper shows how the dynamics of a rotor in a maneuvering aircraft changes according to the operation of the aircraft. The mathematical model of an unbalanced rotor system located in the maneuvering aircraft is derived. The dynamic characteristics of the rotor running at a constant angular speed or a constant acceleration are studied under the assumptions that the aircraft maneuvers only in a vertical plane and that the pitching angle and the flight path inclination of the aircraft are equal. The effects of gravity and unbalance parameter are considered. The results show that the unbalanced response of a rotor in an aircraft is obviously influenced by the aircraft’s flying status.

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31

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

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

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

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Aircraft power system is a complex system consisting of the power generation system, the power management and distribution system, and the power consumption system, which accounts for the aircraft's major fuel consumption and emissions. This paper proposes a scenario-based comprehensive power requirement analysis and system architecture methodology in order to alleviate the risk of systems over-design and discoordination caused by traditional bottom-up load collection and individual system design. Starting from the operation scenario, system functions are identified and corresponding physical architecture and power loads are analysed. Given the complexity of operation scenarios and aircraft power system, model-based system engineering methodology is applied to the top-down aircraft power system architecture design. SysML tool is used to carry out to analyse the aircraft power system architecture during taxi scenario, which provides great advantages on model tracing and reuse.

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33

Nickol, C. L. "Future Naval Aircraft and Aircraft Carrier Design: A Study of Aircraft/Ship Interface." Naval Engineers Journal 109, no. 3 (May 1997): 299–309. http://dx.doi.org/10.1111/j.1559-3584.1997.tb03216.x.

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34

Liu, Na, and Hong Bin Yu. "The Design of Dynamic Model of Engineering Material Arresting System." Applied Mechanics and Materials 607 (July 2014): 435–39. http://dx.doi.org/10.4028/www.scientific.net/amm.607.435.

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Engineered Material Arresting System (EMAS) is a new type of soft ground arresting system that can safely arrest the overrun aircraft in an allowed distance without injuring aircraft passengers and damaging aircraft landing gear. The paper provides an overview of the EMAS background firstly. A numerical simulation is carried out by VB.NET software through reasonable hypothesis and simplification the system of dynamic model. The model is reasonable and feasible compared with prototype experiment results.

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Yu, Hao Qing, You Gen Gong, and Ai Ping Liu. "Wind Erosion Prevention and Repair of Composite Material Components of Civil Aircraft." Advanced Materials Research 225-226 (April 2011): 673–77. http://dx.doi.org/10.4028/www.scientific.net/amr.225-226.673.

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This paper addresses how to discover wind erosion of aircraft components in time and to take appropriate measures to repair and prevent damage, thereby reducing the cost of aircraft maintenance and prolonging aircraft service life. The authors of this paper have extensively compiled and studied civilian aircraft maintenance data in the recent years from Guangzhou Aircraft Maintenance Engineering Co. Ltd. In this paper they discuss the aircraft components most susceptible to wind erosion, as well as repair methods and prevention mechanisms. These findings can serve as a reference and a guide to civilian aircraft flight maintenance, repair, and routine inspections.

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36

Bates, J. P., A. J. Morris, and P. N. Payne. "Knowledge-based geometric modelling of aircraft structures." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 4 (April 1, 1997): 273–84. http://dx.doi.org/10.1243/0954410971532677.

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Aerospace engineering offers a challenging test environment for advanced design systems and methods. Focusing particularly on knowledge-based engineering (KBE) systems, this paper demonstrates their application in automating the solid modelling of aircraft structures. The principles are illustrated through a case study example in which a description is given of the knowledge-based geometric modelling of light alloy fuselage frame sectors. The business benefits of using KBE systems in an aerospace engineering programme are quantified. Recommendations for the extended application of the technology to achieve strategic market advantage are also given.

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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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Hassanpour, A., and Seid H. Pourtakdoust. "Three-dimensional model predictive controller design for approach to landing with microburst encounter." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 11 (May 10, 2017): 2034–47. http://dx.doi.org/10.1177/0954410017707545.

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Microburst is considered an extreme powerful hazard for aircrafts, especially during takeoff, approach and landing phases of flight. Current airborne piloting practices involve taking alternative routes, if early detection of microburst wind shear (MBW) for its effective avoidance is possible. In this respect, design and analysis of precision automatic flight path control systems for microburst penetration are of outmost importance whose success can significantly reduce crash risks and thus enhance the flight safety. The current study is focused on the design and analysis of a three-dimensional model predictive controller for a wide body transport type aircraft encountering MBW in approach to landing phase of flight. This task is performed utilizing the full nonlinear six degrees of freedom aircraft equations of motion and the most complete 3D model of the MBW and its gradients. The results are promising for online applications as the proposed model predictive controller-based controller has effectively guided and kept the aircraft on the approach glide path with negligible deviations against aircraft initial lateral displacements, sharp edge gust disturbance as well as the MBW.

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Boughari, Yamina, Ruxandra Mihaela Botez, Georges Ghazi, and Florian Theel. "Flight control clearance of the Cessna Citation X using evolutionary algorithms." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 3 (August 6, 2016): 510–32. http://dx.doi.org/10.1177/0954410016640821.

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In this paper, an Aircraft Research Flight Simulator equipped with Flight Dynamics Level D (highest level) was used to collect flight test data and develop new controller methodologies. The changes in the aircraft’s mass and center of gravity position are affected by the fuel burn, leading to uncertainties in the aircraft dynamics. A robust controller was designed and optimized using the H∞ method and two different metaheuristic algorithms; in order to ensure acceptable flying qualities within the specified flight envelope despite the presence of uncertainties. The H∞ weighting functions were optimized by using both the genetic algorithm, and the differential evolution algorithm. The differential evolution algorithm revealed high efficiency and gave excellent results in a short time with respect to the genetic algorithm. Good dynamic characteristics for the longitudinal and lateral stability control augmentation systems with a good level of flying qualities were achieved. The optimal controller was used on the Cessna Citation X aircraft linear model for several flight conditions that covered the whole aircraft’s flight envelope. The novelty of the new objective function used in this research is that it combined both time-domain performance criteria and frequency-domain robustness criterion, which led to good level aircraft flying qualities specifications. The use of this new objective function helps to reduce considerably the calculation time of both algorithms, and avoided the use of other computationally more complicated methods. The same fitness function was used in both evolutionary algorithms (differential evolution and genetic algorithm), then their results for the validation of the linear model in the flight points were compared. Finally, robustness analysis was performed to the nonlinear model by varying mass and gravity center position. New tools were developed to validate the results obtained for both linear and nonlinear aircraft models. It was concluded that very good performance of the business Cessna Citation X aircraft was achieved in this research.

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Moshkov, Petr, Valery Samokhin, and Alexey Yakovlev. "ABOUT THE COMMUNITY NOISE PROBLEM OF THE LIGHT PROPELLER AIRCRAFT." Akustika 34 (November 1, 2019): 66–71. http://dx.doi.org/10.36336/akustika20193466.

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A light aircraft community noise problem was considered. Basic aircraft noise sources were described. A model was presented to evaluate engine-propeller aircraft power plant noise that may be used while estimating both light aircraft community noise and flight paths providing aircraft inaudibility in the housing system area adjacent to an airfield. An effective engineering analysis agreement of experimental and design power plant noise data has been given. Major light aircraft communication noise reduction methods have been considered. The principal future investigation directions were stated to provide scientific-and-engineering experience in developing present-day low-noise light aircraft has been developed.

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Amelin, K. B., O. I. Sauta, Yu G. Shatrakov, and S. V. Baburov. "Mathematical model of radio engineering ship system errors in the autolanding problems studies." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 4 (December 30, 2017): 98–104. http://dx.doi.org/10.38013/2542-0542-2017-4-98-104.

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The paper describes the results of statistical processing of flight path errors recorded on board aircraft during aircraft carrier landing approaches using the S-band radar system and the microwave radio-beacon landing system. The analysis and statistical processing data averaging is carried out. A mathematical model of a random (noise) component of the measurement error of radio engineering landing systems used on aircraft carriers is built.The study introduces a mathematical model based on actual data of full-scale tests, which allows us to carry out a wide range of studies to determine the accuracy of various types aircraft landing approaches, including the presence of ship rocking and spatial evolution of the aircraft. The results of mathematical simulation are presented.

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Krasuski, Kamil, Damian Wierzbicki, and Henryk Jafernik. "Utilization PPP method in aircraft positioning in post-processing mode." Aircraft Engineering and Aerospace Technology 90, no. 1 (January 2, 2018): 202–9. http://dx.doi.org/10.1108/aeat-05-2016-0078.

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Purpose The purpose of this paper is to study the implementation of GNSS technique in aviation for recovery of aircraft’s position using Precise Point Positioning (PPP) method. Design/methodology/approach The aircraft’s coordinates in ellipsoidal frame were obtained based on GPS code and phase observations for PPP method. The numerical computations were executed in post-processing mode in the CSRS-PPP and magicPPP online services. The mathematical scheme of PPP method was development using indifference equations of Ionosphere-Free linear combination. In the experiment, airborne test using Cessna 172 aircraft on June 01, 2010 in the military airport in Deblin was realized. The aircraft’s position was determined using data from GNSS receiver (Topcon HiperPro with interval of 1 s). Findings In this paper, the accuracy of aircraft’s position is better than 0.07 m for CSRS-PPP service and better than 0.27 m for magicPPP service. In case of the Mean Radial Spherical Error parameter, the average value for CSRS-PPP service equals to 0.01 m, whereas for magicPPP, it is about 0.38 m. The values of vertical coordinate of Cessna 172 aircraft were also checked with results of Real Time Kinematic–On The Fly technique. Research limitations/implications In this paper, the analysis of aircraft positioning is focused on the application of the PPP method in post-processing mode. In near real time, the PPP method still has limitations, especially in the area of ambiguity resolution and also instrumental biases (e.g. Narrow Lane Hardware Delays). Practical implications The PPP method can be applied in aviation in post-processing mode for verification of true aircraft coordinates and elimination of blunder errors from adjustment processing of GNSS observations. The Zenith Wet Delay term as a product of troposphere delay and receiver clock bias as a product of precise time transfer can be obtained in the PPP method. Originality/value The paper presents that the PPP method is an alternative solution for the recovery of aircraft’s position in aviation, and this method can be also applied in the positioning of aircraft based on GLONASS or GPS/GLONASS data.

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Maneschijn, A., T. Jones, and T. W. von Backström. "An operability framework for unmanned aircraft systems." Aeronautical Journal 115, no. 1168 (June 2011): 361–76. http://dx.doi.org/10.1017/s0001924000005881.

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Abstract In the current absence of comprehensive and generic UAS airworthiness regulations, the development of UAS and their introduction into non-segregated airspace pose significant challenges to the UAS industry and regulators. This paper reports on a research study that considered the problem, from an engineering perspective, beyond the limits of the airworthiness of the aircraft and remote control station. The study introduces the concept of UAS operability, which includes the safe and reliable functioning of the UAS as a system, the airworthiness of its airborne sub-systems, and the safe and reliable functioning of its non-airborne sub-systems and functional payloads. The regulatory domain for UAS operability is described and the study establishes a generic and comprehensive UAS operability framework. The framework was validated by populating its elements with engineering criteria that can be used by the UAS engineering domain for the development of engineering specifications and as guidance towards achieving the safe and reliable functioning of UAS.

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Mohamed, Majeed, and Vikalp Dongare. "Aircraft neural modeling and parameter estimation using neural partial differentiation." Aircraft Engineering and Aerospace Technology 90, no. 5 (July 2, 2018): 764–78. http://dx.doi.org/10.1108/aeat-02-2016-0021.

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Purpose The purpose of this paper is to build a neural model of an aircraft from flight data and online estimation of the aerodynamic derivatives from established neural model. Design/methodology/approach A neural model capable of predicting generalized force and moment coefficients of an aircraft using measured motion and control variable is used to extract aerodynamic derivatives. The use of neural partial differentiation (NPD) method to the multi-input-multi-output (MIMO) aircraft system for the online estimation of aerodynamic parameters from flight data is extended. Findings The estimation of aerodynamic derivatives of rigid and flexible aircrafts is treated separately. In the case of rigid aircraft, longitudinal and lateral-directional derivatives are estimated from flight data. Whereas simulated data are used for a flexible aircraft in the absence of its flight data. The unknown frequencies of structural modes of flexible aircraft are also identified as part of estimation problem in addition to the stability and control derivatives. The estimated results are compared with the parameter estimates obtained from output error method. The validity of estimates has been checked by the model validation method, wherein the estimated model response is matched with the flight data that are not used for estimating the derivatives. Research limitations/implications Compared to the Delta and Zero methods of neural networks for parameter estimation, the NPD method has an additional advantage of providing the direct theoretical insight into the statistical information (standard deviation and relative standard deviation) of estimates from noisy data. The NPD method does not require the initial value of estimates, but it requires a priori information about the model structure of aircraft dynamics to extract the flight stability and control parameters. In the case of aircraft with a high degree of flexibility, aircraft dynamics may contain many parameters that are required to be estimated. Thus, NPD seems to be a more appropriate method for the flexible aircraft parameter estimation, as it has potential to estimate most of the parameters without having the issue of convergence. Originality/value This paper highlights the application of NPD for MIMO aircraft system; previously it was used only for multi-input and single-output system for extraction of parameters. The neural modeling and application of NPD approach to the MIMO aircraft system facilitate to the design of neural network-based adaptive flight control system. Some interesting results of parameter estimation of flexible aircraft are also presented from established neural model using simulated data as a novelty. This gives more value addition to analyzing the flight data of flexible aircraft as it is a challenging problem in parameter estimation of flexible aircraft.

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Li, Peng, Yan Heng Zhang, Han Xu Sun, and Hao Pan. "Design and Aerodynamic Characteristics Study of a Spherical Aircraft." Advanced Materials Research 662 (February 2013): 612–15. http://dx.doi.org/10.4028/www.scientific.net/amr.662.612.

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In order to achieve the goals of small aircraft’s taking off and landing in any posture and the protection of propeller, a new single-propeller spherical aircraft structure was proposed, which had the capacity of flying in the air and walking on the ground simultaneously. An aerodynamic model of the aircraft was built. The aerodynamic characteristics of the spherical aircraft, including the lift and the anti-torque and the generated torque of the flow deflectors under the propeller’s down airflow, are studied in depth by means of CFD numerical simulation method. A reasonable design and installation program is proposed according to the research results.

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Anandhanarayanan, Karuppanasamy, Ankit Raj, Rajah Krishnamurthy, and Debasis Chakraborty. "Engineering Method of Prediction of Plume Path of Air Launched Missile." Defence Science Journal 70, no. 2 (March 9, 2020): 201–6. http://dx.doi.org/10.14429/dsj.70.13853.

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Separation dynamics study of an air-launched missile is a paramount task for ensuring the safety of launch aircraft. The study should certify that there is absolute absence of any physical interference of missile with the aircraft at any circumstance. It is also important to ensure that the interference of rocket motor plume of hot-launched missile does not have any significant effect on the structure, on board electronic components and sensitive parts of the aircraft. The plume ingestion into the aircraft intake is a critical problem which endangers the safety of the aircraft. Therefore, the prediction of plume path of hot-launched missile is a significant part of separation dynamics study. An engineering approach based on a particle tracking method was followed in predicting the plume path in the present work. Further, the method is modified using reverse particle tracking method to make it more efficient. The method is applied in predicting plume path for an air-to air-missile and is found that this approach gives reasonably accurate plume path with minimum computational requirements.

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Pan, Weijun, Zhengyuan Wu, and Xiaolei Zhang. "Identification of Aircraft Wake Vortex Based on SVM." Mathematical Problems in Engineering 2020 (May 12, 2020): 1–8. http://dx.doi.org/10.1155/2020/9314164.

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The aircraft wake vortex has important influence on the operation of the airspace utilization ratio. Particularly, the identification of aircraft wake vortex using the pulsed Doppler lidar characteristics provides a new knowledge of wake turbulence separation standards. This paper develops an efficient pattern recognition-based method for identifying the aircraft wake vortex measured with the pulsed Doppler lidar. The proposed method is outlined in two stages. (i) First, a classification model based on support vector machine (SVM) is introduced to extract the radial velocity features in the wind fields by combining the environmental parameters. (ii) Then, grid search and cross-validation based on soft margin SVM with kernel tricks are employed to identify the aircraft wake vortex, using the test dataset. The dataset includes wake vortices of various aircrafts collected at the Chengdu Shuangliu International Airport from Aug 16, 2018, to Oct 10, 2018. The experimental results on dataset show that the proposed method can identify the aircraft wake vortex with only a small loss, which ensures the satisfactory robustness in detection performance.

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Hitch, H. P. Y. "CADCAM in the Aircraft Industry." Proceedings of the Institution of Mechanical Engineers, Part B: Management and engineering manufacture 200, no. 2 (May 1986): 107–14. http://dx.doi.org/10.1243/pime_proc_1986_200_058_02.

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Reviews the development of CADCAM (computer aided design and manufacture) and CAE (computer aided engineering) in the UK aircraft industry, and describes the systems at present used by British Aerospace in their factories. Discusses communications between systems and how the setting up of networks can overcome problems in collaborative projects. Outlines recent developments in robotics and FMS (flexible manufacturing systems) and reefers to the impact of new materials in aircraft design and manufacturing. Comments on the effect of the new technology on the work-force.

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Price, M., S. Raghunathan, and R. Curran. "An integrated systems engineering approach to aircraft design." Progress in Aerospace Sciences 42, no. 4 (June 2006): 331–76. http://dx.doi.org/10.1016/j.paerosci.2006.11.002.

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Kasava, N. K. "Aircraft Maintenance Engineering Higher Apprenticeship: Review and Challenges." KnE Social Sciences 3, no. 11 (August 8, 2018): 84. http://dx.doi.org/10.18502/kss.v3i11.2752.

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