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Journal articles on the topic 'Aircraft modelling'

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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1

Al-Ahmed, S., and J. P. Fielding. "Vulnerability prediction method for use in aircraft conceptual design." Aeronautical Journal 103, no. 1024 (June 1999): 309–15. http://dx.doi.org/10.1017/s0001924000064903.

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Abstract A methodology has been developed to integrate the vulnerability discipline into the conceptual/preliminary design process of combat aircraft. An interactive and programmable solid modelling Computer Aided Design (CAD) system is used to generate a CAD solid model of the aircraft’s critical components. The aircraft’s components’ sizes and shapes are pre-defined by a conceptual/preliminary design synthesis computer model. A systematic Child-Parent assembly process is used to model the aircraft vulnerability, by defining the criticality degree of each component in the aircraft assembly. Solid Modelling CAD techniques have been modified to develop techniques to perform the two main standard vulnerability assessments, namely the shotline and vulnerable area methods.

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2

Döpelheuer, Andreas. "Aircraft emission parameter modelling." Air & Space Europe 2, no. 3 (May 2000): 34–37. http://dx.doi.org/10.1016/s1290-0958(00)80060-x.

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3

Zhaohui, Ming, Zhang Ming, Tang Xinmin, and Han Song-Chen. "Structural Modelling and Deceleration Algorithm for a Follow Aircraft on Performance-Based Navigation Airway Based on Multi-Agent Technique." Cybernetics and Information Technologies 15, no. 6 (December 1, 2015): 46–56. http://dx.doi.org/10.1515/cait-2015-0066.

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Abstract Considering the operation characteristics of the high-speed PBN airway, we propose an aircraft agent structural model and a basic algorithm flow of decision-making by Multi-agent technique. According to the constraint of safe separation and speed with the aircrafts, making use of the car-following theory, the deceleration constraint model is built for a flight management system. When the front aircraft decelerates, the model can offer a speed adjustment proposal for the following aircraft. The model is built based on the minimal safe separation and speed interval constraint; each variable, influencing the deceleration of the following aircraft can be analyzed. Simulation analysis is carried out for different combinations of aircraft types, initial speed, safe separation and deceleration. The follow aircraft deceleration was calculated under different conditions and the results coincided with reality. It is proved that the model can provide safe separation between the two aircrafts.

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4

Galea, E., and N. Markatos. "Modelling Of Aircraft Cabin Fires." Fire Safety Science 2 (1989): 801–10. http://dx.doi.org/10.3801/iafss.fss.2-801.

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5

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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6

Albagory, Yasser. "Modelling, Investigation, and Feasibility of Stratospheric Broadband mm-Wave 5G and beyond Networks for Aviation." Electronics 9, no. 11 (November 7, 2020): 1872. http://dx.doi.org/10.3390/electronics9111872.

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Recent advances in communication systems provide an enabling technology for aircraft connection and safety. A promising communication system that uses stratospheric platforms provides an efficient and improved communication performance and can be an efficient solution for establishing communication networks for aviation. Therefore, in this paper, a novel communication network based on stratospheric basestation (SB) is proposed to provide fifth-generation (5G) and beyond services for civil aviation aircrafts to improve global flight connectivity, control, and safety. The proposed aircraft–SB network is demonstrated, and its coverage geometry is modelled and investigated. As the 5G and beyond networks use millimeter wave frequency bands (mm-wave), the performance of different atmospheric losses including gaseous absorption, rain, and fog/cloud is analyzed to investigate the system’s practical feasibility at different 5G proposed frequencies ranging from 3.5 to 66 GHz through a flight model including three distinct stages which are takeoff/landing, climbing/descending, and cruise stages. Also, handover scenarios in the proposed aircraft–SB network are investigated and analyzed at the proposed 5G frequencies. In addition, the aircraft–SB 5G network is compared to the most recent low-Earth orbit (LEO) Internet satellites where the proposed system is expected to provide low latency, less atmospheric attenuation, longer aircraft–SB link duration, and very low handover rate.

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7

Levinski, O. "Aeroelastic modelling of aircraft empennage buffet." ANZIAM Journal 45 (September 6, 2004): 981. http://dx.doi.org/10.21914/anziamj.v45i0.936.

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8

Scanlan, Jim, Terry Hill, Rob Marsh, Christophe Bru, Martin Dunkley, and Paul Cleevely. "Cost modelling for aircraft design optimization." Journal of Engineering Design 13, no. 3 (September 2002): 261–69. http://dx.doi.org/10.1080/09544820110108962.

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9

Mengall, G. "Fuzzy modelling for aircraft dynamics identification." Aeronautical Journal 105, no. 1051 (September 2001): 551–55. http://dx.doi.org/10.1017/s0001924000018029.

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A new methodology is described to identify aircraft dynamics and extract the corresponding aerodynamic coefficients. The proposed approach makes use of fuzzy modelling for the identification process where input/output data are first classified by means of the concept of fuzzy clustering and then the linguistic rules are extracted from the fuzzy clusters. The fuzzy rule-based models are in the form of affine Takagi-Sugeno models, that are able to approximate a large class of nonlinear systems. A comparative study is performed with existing techniques based on the employment of neural networks, showing interesting advantages of the proposed methodology both for the physical insight of the identified model and the simplicity to obtain accurate results with fewer parameters to be properly tuned.

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10

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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11

Manvelidze, A. B. "Air lines network modelling algorithm." Strategic decisions and risk management, no. 6 (February 13, 2018): 22–29. http://dx.doi.org/10.17747/2078-8886-2017-6-22-29.

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This analysis is dedicated to find out methods for setting of route networks where new aircraft can be effectively put into service. The conception of this analysis is based on the idea of so called connectivity principle for airports connected by passenger traffic with each other.For the passenger traffic analysis the author took passenger traffic data by federal districts starting from the Far East. Then consequently the data for Siberian, Ural, Wolga, Northwestern, Central, Southern and North Caucasian federal districts were analyzed. Passenger traffic to the Crimea was treated separately. Detailed specifications of passenger traffics were provided in order to determine the connections between airports both within federal districts and beyond them and with neighboring areas in western direction. Query of routes was done based on limitations for non-stop flight range and on minimum and maximum (for significant traffics) flight frequencies.The analysis approach lets us concentrate attention on those airlines which at best fit for putting into service of chosen aircraft. Also this method permits to determine the routes with currently insufficient or low traffics but where there’s a definite growth potential. When analysis data are combined with traffic data and tariffs, then it becomes possible to determine the most profitable routes for introduction of new aircraft. Traffic volume, actual figures and forecast, consolidated characteristics of chosen airlines, list of airlines for further studies of efficiency and competitiveness of introduced aircraft are determined.

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12

Whitehouse, G. R., and R. E. Brown. "Modelling a helicopter rotor’s response to wake encounters." Aeronautical Journal 108, no. 1079 (January 2004): 15–26. http://dx.doi.org/10.1017/s0001924000004954.

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In recent years, various strategies for the concurrent operation of fixed-and rotary-wing aircraft have been proposed as a means of increasing airport capacity. Some of these strategies will increase the likelihood of encounters with the wakes of aircraft operating nearby. Several studies now exist where numerical simulations have been used to assess the impact of encounters with the wakes of large transport aircraft on the safety of helicopter operations under such conditions. This paper contrasts the predictions of several commonly-used numerical simulation techniques when each is used to model the dynamics of a helicopter rotor during the same idealised wake encounter. In most previous studies the mutually-induced distortion of the wakes of the rotor and the interacting aircraft has been neglected, yielding the so-called ‘frozen vortex’ assumption. This assumption is shown to be valid only when the helicopter encounters the aircraft wake at high forward speed. At the low forward speeds most relevant to near-airfield operations, however, injudicious use of the frozen vortex assumption may lead to significant errors in predicting the severity of a helicopter’s response to a wake encounter.

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13

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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14

Lawver, Darell, Lisa Nikodym, Darren Tennant, and Howard Levine. "Non-linear numerical modelling of aircraft impact." International Journal of Crashworthiness 6, no. 4 (June 6, 2001): 451–70. http://dx.doi.org/10.1533/cras.2001.0190.

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15

Tam, E., J. J. Lowke, and A. B. Murphy. "Modelling Lightning Initiation and Attachment to Aircraft." Journal of Physics: Conference Series 550 (November 26, 2014): 012002. http://dx.doi.org/10.1088/1742-6596/550/1/012002.

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16

Frosina, Emma, Carmine Caputo, Gianluca Marinaro, Adolfo Senatore, Ciro Pascarella, and Giuseppe Di Lorenzo. "Modelling of a Hybrid-Electric Light Aircraft." Energy Procedia 126 (September 2017): 1155–62. http://dx.doi.org/10.1016/j.egypro.2017.08.315.

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17

Cox, Stephen, and Lluis Vinagre. "Modelling of confusions in aircraft call-signs." Speech Communication 42, no. 3-4 (April 2004): 289–312. http://dx.doi.org/10.1016/j.specom.2003.09.006.

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18

RABIE, G., A. KHATTAB, and A. ELZAHABY. "MODELLING OF AN AIRCRAFT LONGITUDINAL CONTROL SYSTEM." International Conference on Aerospace Sciences and Aviation Technology 2, CONFERENCE (April 1, 1987): 1–14. http://dx.doi.org/10.21608/asat.1987.26176.

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19

Jadin, E. A., and D. V. Bromberg. "Modelling of ozone reduction by stratospheric aircraft." Journal of Atmospheric and Terrestrial Physics 56, no. 9 (July 1994): 1091–94. http://dx.doi.org/10.1016/0021-9169(94)90047-7.

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20

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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21

Booker, Julian, Caius Patel, and Phillip Mellor. "Modelling Green VTOL Concept Designs for Reliability and Efficiency." Designs 5, no. 4 (October 28, 2021): 68. http://dx.doi.org/10.3390/designs5040068.

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All-electric and hybrid-electric aircraft are a future transport goal and a possible ‘green’ solution to increasing climate-related pressures for aviation. Ensuring the safety of passengers is of high importance, informed through appropriate reliability predictions to satisfy emerging flight certification requirements. This paper introduces another important consideration related to redundancy offered by multiplex electric motors, a maturing technology which could help electric aircraft manufacturers meet the high reliability targets being set. A concept design methodology is overviewed involving a symbolic representation of aircraft and block modelling of two important figures of merit, reliability, and efficiency, supported by data. This leads to a comparative study of green aircraft configurations indicating which have the most potential now, and in the future. Two main case studies are then presented: an electric tail rotor retrofitted to an existing turbine powered helicopter (hybrid) and an eVTOL aircraft (all-electric), demonstrating the impact of multiplex level and number of propulsion channels on meeting target reliabilities. The paper closes with a summary of the important contribution to be made by multiplex electric machines, well as the advancements necessary for green VTOL aircraft sub-systems, e.g., power control unit and batteries, to improve reliability predictions and safety further.

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22

PORTAPAS, Vilius, Alastair COOKE, and Mudassir LONE. "MODELLING FRAMEWORK FOR FLIGHT DYNAMICS OF FLEXIBLE AIRCRAFT." Aviation 20, no. 4 (December 20, 2016): 173–82. http://dx.doi.org/10.3846/16487788.2016.1264719.

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The flight dynamics and handling qualities of any flexible aircraft can be analysed within the Cranfield Aircraft Accelerated Loads Model (CA2LM) framework. The modelling techniques and methods used to develop the framework are presented. The aerodynamic surfaces were modelled using the Modified Strip Theory (MST) and a state-space representation to model unsteady aerodynamics. With a modal approach, the structural flexibility and each mode’s influence on the structure deflections are analysed. To supplement the general overview of the framework equations of motion, models of atmosphere, gravity, fuselage and engines are introduced. The AX-1 general transport aircraft model is analysed as an example of the CA2LM framework capabilities. The results showed that, according to the Gibson Dropback criterion, the aircraft with no control system lacks the stability and its longitudinal handling qualities are unsatisfactory. Finally, the steps for future developments of the CA2LM framework are listed within conclusions.

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23

Jovanovic, Julia, and Colin Novak. "Standardization of modelling methodology for aircraft noise exposure contours." Journal of the Acoustical Society of America 152, no. 4 (October 2022): A128. http://dx.doi.org/10.1121/10.0015772.

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Aircraft noise exposure contours are important tools for land-use planning around aerodromes. They inform local governments and stakeholders as to the acoustic impacts of aircraft operations on areas surrounding the airport. This information is considered when defining municipal zoning and building regulations. While noise contours are often regarded as concrete guidance identifying the suitability of an area for noise sensitive development, their prescribed modelling methodology is imprecise and non-standardised. A vague description such as the yearly day night level or 95th percentile day is typically mandated by overseeing authorities which leaves ambiguity in terms of the various specific input parameters. This can result in differing noise contour outputs, which in turn can cause conflict, especially between stakeholders with competing interests. This research highlights the need for better standardization and guidance for aircraft noise exposure contour modelling. It further demonstrates how varying interpretations of modelling methodologies can alter the input parameters of an aircraft noise model and significantly impact the outputs.

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24

Song, Y., B. Horton, and J. Bayandor. "Verified fuselage section water impact modelling." Aeronautical Journal 123, no. 1268 (October 2019): 1740–54. http://dx.doi.org/10.1017/aer.2019.110.

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ABSTRACTAlong many flight corridors, bodies of water serve as preferred emergency landing options. Thus, relevant scenarios must be investigated to improve aircraft crashworthiness in the event of an impact landing on water. Enhancing the damage tolerance of aircraft structures through repetitive experiments can, however, prove highly uneconomical. Such large-scale trials can be influenced by many factors of uncertainty adversely affecting the quality of the results. Therefore, the work presented in this study focuses in particular on evaluating a computational methodology perfected for aircraft water ditching using Coupled Lagrangian-Eulerian (CLE) that allows detailed prediction of structural response of a verified deformable fuselage section during such events. Validation of the fluid-structure interactive (FSI) strategy developed is conducted, thoroughly comparing the method against the analytical and experimental results of multiple wedge drop tests. Finally, the validated FSI strategy is applied to a high-fidelity fuselage section model impacting water to simulate and assess a realistic ditching scenario.

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25

Harris, A. P., and N. M. Ratcliffe. "Dimensional modelling of the fuel outgassing phenomenon: Improving flammability assessment of aircraft fuel tanks." Aeronautical Journal 115, no. 1172 (October 2011): 605–14. http://dx.doi.org/10.1017/s0001924000006291.

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Abstract Fuel outgassing (oxygen evolution) within aircraft fuel tanks presents a serious flammability hazard. Time constants representing oxygen transfer rate, from the fuel into a tank’s ullage, are used to model the effect of outgassing on tank flammability. These time constants are specific to a single aircraft type and flight envelope and may not accurately represent fuel outgassing behaviour for other aircraft types with differing fuel tank configurations and flight envelopes. To improve current modelling practice for more accurate flammability analysis dimensional modelling has been used to determine the rate of oxygen evolution from Jet A-1 fuel in an aircraft fuel tank. Measurements of oxygen evolution rate, made on a dimensionally similar model, have been projected to an A320 aircraft. The evolution of oxygen from the fuel was found to increase monotonically with time. Fitting the test data with an inverse-exponential function enabled oxygen release rate and its associated time constant (τ) to be determined. Dimensional modelling of aviation fuel outgassing using model fuel tanks will enable oxygen evolution rate from aviation fuel to be determined for a wide range of aircraft fuel tank configurations and environments without the need for flight testing. In turn the accuracy of flammability assessment of aircraft fuel tanks will be improved and significant cost savings made.

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26

Khairuddin, Ismail Mohd, Anwar P. P. A. Majeed, Ann Lim, Jessnor Arif M. Jizat, and Abdul Aziz Jaafar. "Modelling and PID Control of a Quadrotor Aerial Robot." Advanced Materials Research 903 (February 2014): 327–31. http://dx.doi.org/10.4028/www.scientific.net/amr.903.327.

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This paper elucidates the modeling of a + quadrotor configuration aerial vehicle and the design of its attitude and altitude controllers. The aircraft model consists of four fixed pitch angle propeller, each driven by an electric DC motor. The hovering flight of the quadrotor is governed by the Newton-Euler formulation. The attitude and altitude controls of the aircraft were regulated using heuristically tuned (Proportional-Integral-Derivative) PID controller. It was numerically simulated via Simulink that a PID controller was sufficient to bring the aircraft to the required altitude whereas the attitude of the vehicle is adequately controlled by a PD controller.

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27

Sheng, L. Q., J. H. Pei, and X. Y. Liu. "Self-affine Fractal Modelling of Aircraft Echoes from Low-resolution Radars." Defence Science Journal 66, no. 2 (March 23, 2016): 151. http://dx.doi.org/10.14429/dsj.66.8423.

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<p>For complex targets, the non rigid vibration of an aircraft as well as its attitude changes and the rotation of its rotating parts will induce complex nonlinear modulation on its echo from low-resolution radars. If one performs the fractal analysis of measures on an aircraft echo, it may offer a fine description of the dynamic characteristics which induce the echo structure. On basis of introducing self-affine fractal theory, the paper models real recorded aircraft echo data from a low-resolution radar using the self-affine fractal representation, and investigates the application of echo self-affine fractal characteristics in aircraft target classification. Results analysis shows that aircraft echoes from low-resolution radars can be modelled by using the self-affine fractal method, and the self-affine fractal features can be effectively applied to target classification and recognition.</p><p> </p>

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28

Sadovnychiy, S. "Physical modelling of a flight control system." Aeronautical Journal 107, no. 1071 (May 2003): 249–55. http://dx.doi.org/10.1017/s0001924000097293.

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Abstract This paper deals with the methods of physical modelling of Flight Control Systems (FCS) by means of Dynamically Similar free-flying Models (DSM) for the investigation of stability and controllability of aircraft at subsonic flight speeds. The subsonic flight regime allows us to avoid Mach number similarity considerations. The large scale of the DSM meets autosimilarity of Reynolds numbers, whilst Froude similarity is assured during the development and manufacturing of the DSM. This paper proves the presence of necessary and sufficient conditions of similarity for the FCS of an aircraft, and that of its DSM. The existence of necessary conditions have been proved both mathematically (by means of the π – Theorem from the theory of dimensions), and with equations involving physical quantities. The generalised scale coefficients for transitioning from the FCS’s aircraft gain factors, to those of the FCS of the DSM have been obtained, and it is shown that the coefficients depend only on the linear scale of the DSM.

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29

Wang, Jie Ning, and Gao Yang Jiang. "The Aircraft Surface Movement Behaviors Modelling and Analysis Using Petri Net." Advanced Materials Research 466-467 (February 2012): 946–50. http://dx.doi.org/10.4028/www.scientific.net/amr.466-467.946.

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The description of aircraft surface movement behaviors at airdrome is the key issue of control and scheduling simulation which aims to solve the surface traffic activities problems. Using the Petri Net theory and CPN Tools to build hierarchical and timed Petri Net of aircraft taxing, prescribed the entire progress of aircraft from apron service to takeoff in order to achieve flexible random route allocation and normal orderly operation.

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30

Archilla, Víctor, Dévora Hormigo, María Sánchez-García, and David Raper. "AVIATOR - Assessing aViation emission Impact on local Air quality at airports: TOwards Regulation." MATEC Web of Conferences 304 (2019): 02023. http://dx.doi.org/10.1051/matecconf/201930402023.

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Emissions from aircraft have adverse effects on the air quality in and around airports, contributing to public health concerns within neighbouring communities. AVIATOR will adopt a multi-level measurement, modelling and assessment approach to develop an improved description and quantification of the relevant aircraft engine emissions, and their impact on air quality under different climatic conditions. Particulate and gaseous emissions in a test cell and on-wing from an in-service aircraft will be measured to determine pollutant plume evolution from the engine and APU exhaust. This will provide an enhanced understanding of primary emitted pollutants, specifically the nvPM and vPM (down to 10nm), and the scalability between the regulatory test cell and real environments. AVIATOR will develop and deploy a proof-of-concept low cost sensor network for monitoring UFP, PM and gaseous species across multiple airports and surrounding communities. Campaigns will be complemented by high-fidelity modelling of aircraft exhaust dynamics, microphysical and chemical processes within the plume. CFD, box, and airport air quality models will be applied, providing validated parameterisations of the relevant processes, applicable to standard dispersion modelling on the local scale. Working with the regulatory community, AVIATOR will develop improved guidance on measuring and modelling the impact of aircraft emissions, and will provide airports and regulators with tools and guidance to improve the assessment of air quality in and around airports.

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31

Pitchaimuthu, Selladurai, Jitesh J. Thakkar, and P. R. C. Gopal. "Modelling of risk factors for defence aircraft industry using interpretive structural modelling, interpretive ranking process and system dynamics." Measuring Business Excellence 23, no. 3 (October 22, 2019): 217–39. http://dx.doi.org/10.1108/mbe-05-2018-0028.

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Purpose Risk management in defence aircraft industry has considerable interest among academics and practitioners. The purpose of this paper is to develop interactions among risk factors dimensions (RFDs) and inspect the importance relationship among the performance measures in Indian aircraft industry and, finally, understand the effect of involvements provided by the managerial team on risk reduction process. Design/methodology/approach An extensive literature review was carried out to identify 26 risk parameters and 13 performance measure indices relevant for an aircraft industry. Survey method was used to obtain the importance of these parameters and measures. Further, these factors are grouped into five risk dimensions based on the brain storming session by the project managers. Initially, Risk factors for defense aircraft industry (RFDs) analyzed by Interpretative structural model (ISM) to know the contextual relationship among the RFDs and then applied Interpretive ranking process (IRP) to inspect the pre-eminence relationship among them. Finally, SD is applied to understand the effect of involvements provided by the managerial team on risk reduction process. Findings Government policy and legal RFDs has emerged as the key driving RFDs. In IRP modelling, technology RFD has emerged as more influential RFD which is the more relevant factor with respect to performance measure indices and this result is supported by detailed sensitivity analysis of system dynamic model. Originality/value The outcomes of this research can help project management team to identify the high severity risk factors which need immediate risk reduction/mitigation action.

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32

Zhang, Xia, Youchao Sun, and Yanjun Zhang. "Ontology modelling of intelligent HCI in aircraft cockpit." Aircraft Engineering and Aerospace Technology 93, no. 5 (June 10, 2021): 794–808. http://dx.doi.org/10.1108/aeat-11-2020-0255.

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Purpose Semantic modelling is an essential prerequisite for designing the intelligent human–computer interaction in future aircraft cockpit. The purpose of this paper is to outline an ontology-based solution to this issue. Design/methodology/approach The scenario elements are defined considering the cognitive behaviours, system functions, interaction behaviours and interaction situation. The knowledge model consists of a five-tuple array including concepts, relations, functions, axioms and instances. Using the theory of belief-desire-intention, the meta-model of cognitive behaviours is established. The meta-model of system functions is formed under the architecture of sub-functions. Supported by information flows, the meta-model of interaction behaviours is presented. Based on the socio-technical characteristics, the meta-model of interaction situation is proposed. The knowledge representation and reasoning process is visualized with the semantic web rule language (SWRL) on the Protégé platform. Finally, verification and evaluation are carried out to assess the rationality and quality of the ontology model. Application scenarios of the proposed modelling method are also illustrated. Findings Verification results show that the knowledge reasoning based on SWRL rules can further enrich the knowledge base in terms of instance attributes and thereby improve the adaptability and learning ability of the ontology model in different simulations. Evaluation results show that the ontology model has a good quality with high cohesion and low coupling. Practical implications The approach presented in this paper can be applied to model complex human–machine–environment systems, from a semantics-driven perspective, especially for designing future cockpits. Originality/value Different from the traditional approaches, the method proposed in this paper tries to deal with the socio-technical modelling issues concerning multidimensional information semantics. Meanwhile, the constructed model has the ability of autonomous reasoning to adapt to complex situations.

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33

Lu, Wen-Chi, Walid El-Moudani, Téo Cerqueira Revoredo, and Felix Mora-Camino. "Neural networks modelling for aircraft flight guidance dynamics." Journal of Aerospace Technology and Management 4, no. 2 (2012): 169–74. http://dx.doi.org/10.5028/jatm.2012.04020712.

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34

Christopoulos, C., J. F. Dawson, L. Dawson, I. D. Flintoft, O. Hassan, A. C. Marvin, K. Morgan, P. Sewell, C. J. Smartt, and Z. Q. Xie. "Characterization and modelling of electromagnetic interactions in aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 224, no. 4 (December 17, 2009): 449–58. http://dx.doi.org/10.1243/09544100jaero567.

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Bisagni, C., and M. S. Pigazzini. "Modelling strategies for numerical simulation of aircraft ditching." International Journal of Crashworthiness 23, no. 4 (May 23, 2017): 377–94. http://dx.doi.org/10.1080/13588265.2017.1328957.

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Finney, J. M. "MODELLING FOR FATIGUE CRACK GROWTH PREDICTION IN AIRCRAFT." Fatigue & Fracture of Engineering Materials and Structures 8, no. 3 (March 1985): 205–22. http://dx.doi.org/10.1111/j.1460-2695.1985.tb00423.x.

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Yazar, Isil. "Modelling of aircraft harness tests via Petri network." International Journal of Sustainable Aviation 2, no. 3 (2016): 235. http://dx.doi.org/10.1504/ijsa.2016.080241.

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Yazar, Isil. "Modelling of aircraft harness tests via Petri network." International Journal of Sustainable Aviation 2, no. 3 (2016): 235. http://dx.doi.org/10.1504/ijsa.2016.10001099.

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Ayres, Manuel, Hamid Shirazi, Regis Carvalho, Jim Hall, Richard Speir, Edith Arambula, Robert David, et al. "Modelling the location and consequences of aircraft accidents." Safety Science 51, no. 1 (January 2013): 178–86. http://dx.doi.org/10.1016/j.ssci.2012.05.012.

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Juang *, Jih-Gau, and Jern-Zuin Chio. "Fuzzy modelling control for aircraft automatic landing system." International Journal of Systems Science 36, no. 2 (February 10, 2005): 77–87. http://dx.doi.org/10.1080/0020772042000325961.

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41

Zaporozhets, Oleksander I., and Vadim I. Tokarev. "Aircraft noise modelling for environmental assessment around airports." Applied Acoustics 55, no. 2 (October 1998): 99–127. http://dx.doi.org/10.1016/s0003-682x(97)00101-1.

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Blázquez, A. L. González. "Mathematical modelling for analysis of nonlinear aircraft dynamics." Computers & Structures 37, no. 2 (January 1990): 193–97. http://dx.doi.org/10.1016/0045-7949(90)90401-m.

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Pérez–Rodríguez, J. V., J. M. Pérez–Sánchez, and E. Gómez–Déniz. "Modelling the asymmetric probabilistic delay of aircraft arrival." Journal of Air Transport Management 62 (July 2017): 90–98. http://dx.doi.org/10.1016/j.jairtraman.2017.03.001.

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Tomlinson, S. P., and D. G. Tilley. "Computer Modelling of Aircraft Hydraulic Systems Using Bathfp." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 2 (July 1993): 139–43. http://dx.doi.org/10.1243/pime_proc_1993_207_258_02.

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The computer simulation package BATHfp has been developed at the Fluid Power Centre, University of Bath to perform transient time domain simulations of fluid power systems. Utilities are provided which allow new models to be introduced into the component database. This enables the package to be tailored to particular dedicated areas of interest such as aircraft flight controls, braking and landing gear and fuel flow systems. This paper describes the application of BATHfp to aircraft hydraulic systems. An example is taken of an electrohydraulic position control system which uses an actuator to move an aileron according to a desired schedule. Parametric variations are made to illustrate how system performance can be improved.

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45

Olja, Čokorilo. "Quantified risk assessment modelling of aircraft landing operations." Scientific Research and Essays 6, no. 20 (September 19, 2011): 4406–13. http://dx.doi.org/10.5897/sre11.838.

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Leitao, A. L. F., and D. W. Newton. "Proportional hazards modelling of aircraft cargo door complaints." Quality and Reliability Engineering International 5, no. 3 (July 1989): 229–38. http://dx.doi.org/10.1002/qre.4680050308.

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Cimmino, N., SS Ponnusamy, A. Garcia Garriga, and L. Mainini. "A modelling and simulation framework for the integrated design of aircraft systems." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 10 (April 3, 2019): 1648–60. http://dx.doi.org/10.1177/0954410019835726.

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New technologies and complex systems are being developed in commercial aviation to meet strict requirements regarding fuel consumption, emissions and noise constraints. This motivates the development of multidisciplinary environments to efficiently manage the increasing complexity of the design process. Under the Clean Sky 2 initiative, the ModellIng and Simulation tools for Systems IntegratiON on Aircraft (MISSION) project aims to develop an integrated framework to holistically support the aircraft design, development and validation processes. Within the MISSION framework, this paper proposes a methodology to handle the integration between the aircraft level and the system level in the early phase of aircraft design. The methodology is demonstrated for the case of the Landing Gear System in the rejected take-off scenario.

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Ahmad, S. M., M. H. Shaheed, A. J. Chipperfield, and M. O. Tokhi. "Non-linear modelling of a one-degree-of-freedom twin-rotor multi-input multi-output system using radial basis function networks." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 216, no. 4 (April 1, 2002): 197–208. http://dx.doi.org/10.1243/09544100260369731.

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Modelling of innovative aircraft such as unmanned air vehicles (UAVs), X-wing, tilt body and delta-wing aircraft is not easy. It is argued in this paper that non-linear system identification is suitable for modelling air vehicles of complex configuration. This approach is demonstrated through a laboratory test rig. Extensive time and frequency-domain model-validation tests are employed in order to instil confidence in the estimated model. The estimated model has a good predictive capability and can be utilized for non-linear flight simulation studies. Some aspects of the modelling approach presented may be relevant to flight mechanics modelling of new generations of air vehicle.

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Anastasiia, Novokhatska. "DESIGN OF AN AIRFOIL BY MATHEMATICAL MODELLING USING DATABASE." Journal of Airline Operations and Aviation Management 1, no. 1 (July 25, 2022): 19–26. http://dx.doi.org/10.56801/jaoam.v1i1.3.

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The aerodynamic performance of low Reynolds airfoils with a Reynolds number less than 105 is critical for a variety of applications, including unmanned aerial vehicles, micro air vehicles, and low-speed/high-altitude aircraft. In general, most airfoils with Reynolds numbers less than 106 cannot be considered to have constant lift and drag characteristics. XFLR5 is a tool for analysing low-Reynolds-number airfoils, wings, and aircraft. It comes with XFOIL's direct and inverse analysis tools. The lifting line theory, the vortex lattice approach, and the 3-D panel method are all used to build and analyse wings. The lift coefficient (Cl) and pressure distribution (Cp) are fundamental metrics that determine the behaviour of airfoils. The cornerstone of aerodynamic analysis during aircraft development is pressure distribution data.

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Glaser-Opitz, Henrich, Ján Labun, Kristína Budajová, and Leonard Glaser-Opitz. "DESCENT TRAJECTORY MODELLING FOR THE LANDING SYSTEM PROTOTYPE." Transport 35, no. 2 (April 3, 2020): 133–42. http://dx.doi.org/10.3846/transport.2020.12231.

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This paper gives another view on a method used for aircraft approach and landing phase of flight that enables replacement of standard glideslope. Proposed Landing System is based on Terrain Reference Navigation (TRN) using own created terrain elevation database, based on Radar Altimeter (RA) measurements compared to the overflown terrain. Simulations were performed on a chosen airport (KSC – Košice Airport) and aircraft (Boeing 737-800), where descend procedures was designed based on real airline data in compliance with Initial 4D Trajectory (i4D). Descend trajectory was modelled with EUROCONTROL Base of Aircraft DAta (BADA) performance model as a Continuous Descent Approach (CDA) from proposed merging point to the KSC RunWaY (RWY) threshold. This method was proposed to enhance pilot situational awareness in situations when standard Instrument Landing System (ILS) information could be lost or misleading and without the need of any ground station for successful navigation and guidance to the RWY threshold. Landing System prototype flight test were performed on full mission flight simulator.

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