Relevant bibliographies by topics / Aircraft reliability

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Aircraft reliability'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 January 2023

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Journal articles on the topic "Aircraft reliability"

1

Hauka, Maris, and Jurijs Paramonovs. "Airline and Aircraft Reliability." Transport and Aerospace Engineering 1 (May 8, 2014): 9. http://dx.doi.org/10.7250/tae.2014.002.

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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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Wawrzyński, Wojciech, Mariusz Zieja, Justyna Tomaszewska, and Mariusz Michalski. "Reliability Assessment of Aircraft Commutators." Energies 14, no. 21 (November 6, 2021): 7404. http://dx.doi.org/10.3390/en14217404.

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The article describes the method of predicting the reliability and durability of an aircraft commutator, which is a primary source of electric energy in helicopters. Tests were conducted for 10 starter-generators. From this research it follows that the technical condition of brushes and bearings has a significant impact on the reliability of starter-generators. The reliability of starter-generators was determined based on the method consisting of two stages that was adopted: the first stage involved determining the density function of changes in diagnostic parameter depending on the operating time, but the second stage included the assessment of the reliability of bearings of the starter-generator taking into account the real flight profile. The first stage of the adopted method consisted of defining the dynamic model of changing the length of the starter-generator’s brush, which became the probabilistic model. Subsequently, based on differential equations, Fokker–Planck partial differential equation was derived, which describes the process of increasing the brush wear in a probabilistic way. This method enables the prediction of the residual durability of the helicopter’s starter-generator due to the change in a diagnostic parameter which is the wear of brushes during starter-generator operation. The second stage of this method allows determining the durability of starter-generator’s bearings building upon the average helicopter’s flight profile. Owing to the difficulty in measuring the wear of bearings, the relation between the durability of bearings and the temperature of surroundings can be applied by replacing the flight altitude with temperature. The reliability of the helicopter’s starter-generator was determined based on the serial-type reliability structure.
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SAINTIS, LAURENT, EMMANUEL HUGUES, CHRISTIAN BES, and MARCEL MONGEAU. "COMPUTING IN-SERVICE AIRCRAFT RELIABILITY." International Journal of Reliability, Quality and Safety Engineering 16, no. 02 (April 2009): 91–116. http://dx.doi.org/10.1142/s0218539309003319.

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This paper deals with the modeling and computation of in-service aircraft reliability at the preliminary design stage. This problem is crucial for aircraft designers because it enables them to evaluate in-service interruption rates, in view of designing the system and of optimizing aircraft support. In the context of a sequence of flight cycles, standard reliability methods are not computationally conceivable with respect to industrial timing constraints. In this paper, first we construct the mathematical framework of in-service aircraft reliability. Second, we use this model in order to demonstrate recursive formulae linking the probabilities of the main failure events. Third, from these analytic developments, we derive relevent reliability bounds. We use these bounds to design an efficient algorithm to estimate operational interruption rate indicators. Finally, we show the usefulness of our approach on real-world cases provided by Airbus.
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Shi, Qiongyan, and Jianghua Zhang. "Mechanical Structure Design of the Aircraft ASD Control Isolation Control." Journal of Applied Mathematics 2022 (November 16, 2022): 1–16. http://dx.doi.org/10.1155/2022/8306216.

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Aircraft control system is of key importance for flight attitude control of aircrafts. Its normal function directly determines whether the aircraft flies safely, flight delay, and dispatch reliability. Therefore, this paper designs the mechanical structure of the aircraft ASD control isolation control. Firstly, the mechanical control principle of the driving rod system is analyzed, and the isolation mechanism of pitch and roll control is designed; secondly, the control lines are classified, the transmission characteristic requirements of the aircraft control isolation system are given, the transmission ratio distribution and calculation of the aircraft control isolation system are given, and finally, the mechanism design of the aircraft ASD control isolation system is realized.
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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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Chu, Shuanglei, Fei Liu, and Zhiqiang Wei. "The Study on Dispatch Reliability Prediction Model of Civil Aircraft." Open Mechanical Engineering Journal 8, no. 1 (December 31, 2014): 828–32. http://dx.doi.org/10.2174/1874155x01408010828.

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Dispatch reliability is the key parameters to reflect the overall reliability of civil aircraft, and it is also the important technical parameters needs to be considered in the original design of civil aircraft. According to the actual delay rate data of airlines, combined with the relationship between delay rate and dispatch reliability, from the perspective of civil aircraft design, author firstly puts forward that seven design parameters of the aircraft design phase, the design parameters consist of five main parameters and two auxiliary parameters, and then this paper establishes a mathematical relationship between dispatch reliability and aircraft original design parameters, the dispatch reliability of civil aircraft was predicted, prediction model is reasonable and has higher precision accuracy, it laid the theoretical basis and data support for dispatch reliability prediction of our country civil aircraft, meanwhile the prediction model of dispatch reliability can provide reference data for the structure design of civil aircraft.
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Bai, Wen Hua, Hong Fu Zuo, and De Feng Lv. "A Method to Reliability Analysis of the Aircraft’s Structural Component." Advanced Materials Research 452-453 (January 2012): 223–27. http://dx.doi.org/10.4028/www.scientific.net/amr.452-453.223.

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The MRBR is important to ensure the aircraft’s safety and reliability. The analysis to the structural components’ reliability is to establish the basis for its MRBR. The aviation component’s reliability obey the bathtub curve distribution, Weibull distribution, exponential distribution and a linear increasing distribution. A method of reliability analysis of structural components is proposed. According to the aircraft operating data the structural components reliability distribution is fitted. The component failure weaknesses and remedial measures can be determined according to its reliability distribution. So the perfect MRBR can be obtained. As an example the structural component slide rail is studied, which showed the slide rail reliability is the Weibull distribution and consistent with the actual running situation. So the example showed that the proposed method is reasonable. And a viable method to the development of aircraft MRBR is got.
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Dalkilic, Serdar. "Improving aircraft safety and reliability by aircraft maintenance technician training." Engineering Failure Analysis 82 (December 2017): 687–94. http://dx.doi.org/10.1016/j.engfailanal.2017.06.008.

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Tang, Hong, Guo Guang Chen, and Hui Zhu He. "Optimization Design and Numerical Simulation for Aerodynamics Shape of an Aircraft." Applied Mechanics and Materials 215-216 (November 2012): 275–78. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.275.

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Considering safety and reliability of interface between aircraft and artillery, aircraft need of increasing space of shell bands, but its range decreased by flight experimental results. It is enough to numerically simulate and calculate to aerodynamics of two projects (namely aircraft increased spacing bands vs. archetype aircraft) model in this paper. The simulation results show that big space of shell bands affect aircraft body’s coefficient of drag, and keep to flight experimental results. In keeping to big spacing bands at the same time, it is put forward optimization scheme that aircraft can reach to design range by adjusted tails shrink angle. When the tails shrink angle reached to six degrees, the big spacing bands aircraft’s coefficient of drag decreased obviously and pressure coefficient little increased to avail of improving aircraft’s range by a large of numerical simulations.
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Dissertations / Theses on the topic "Aircraft reliability"

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Yang, Ju-Sung. "System reliability optimization of aircraft wings." Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54818.

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System reliability based design of aircraft wings is studied. A wing of a light commuter aircraft designed according to the FAA regulations is compared with one designed by system reliability optimization. Both the level III, and the advanced first order, second moment (AFOSM) method are employed to evaluate the probability of failure of each failure element of the system representing the wing. In the level III method the statistical correlation between failure modes is neglected. The AFOSM method allows to evaluate the sensitivity derivatives of the system safety index analytically. Furthermore, it accounts for the statistical correlation between failure modes. The results demonstrate the potential of stochastic optimization, and the importance of accounting for the statistical correlation between failure modes. Finally, it is shown that the problem associated with discontinuity of sensitivity derivatives, encountered when using second order Ditlevsen upper bounds to estimate the system failure probability, is circumvented if a penalty function method is used for optimization.
Ph. D.
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Rambalakos, Andreas. "Monte Carlo simulation methodology for the reliability of aircraft structures reliability of aircraft structures under damage tolerance requirements." Saarbrücken VDM Verlag Dr. Müller, 2006. http://d-nb.info/988567741/04.

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Cook, Lawrence. "Visual inspection reliability for composite aircraft structures." Thesis, Cranfield University, 2009. http://dspace.lib.cranfield.ac.uk/handle/1826/6834.

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This thesis presents a study of the effects of surface colour, surface finish and dent shape on the visual inspection reliability of 3D surface indentations common in shape to those produced by impact damage to carbon fibre reinforced epoxy laminates. Falling weight (2.5kg) apparatus was used to produce impact damage to non-painted, non-mesh Hexcel AS4/ 8552 carbon fibre reinforced plastic (CFRP) laminates and painted AS4/ 8552 laminates containing bronze mesh and glass fabric lightning strike protection layers. Ø20 mm and Ø87 mm hemispherical tip impacts to painted 17ply and 33ply laminates at varying energy levels typically produced circular shaped, smoothly contoured, rounded sectional profiles with an absence of surface breaking cracks. Sectional profiles through coordinate measuring (CMM) data of the impact dents were described using a set of geometric variables. Identifying relationships between impact energy and the geometric variables allowed the typical sectional profile through impact damage dents from Ø20 mm and Ø87 mm hemispherical tips on 17ply and 33ply painted CFRP laminates to be calculated for energies between 5J to 80J. Calculated sectional profiles typical of impact damage dents to CFRP laminates were reconstructed as simple revolved shapes using 3D computer aided design (CAD) models. The 3D CAD models were computer numerical control (CNC) machined into 3mm Plexiglas panels to produce facsimiles of hemispherical impact damage dents on CFRP laminates. Facsimile specimen sets of sixteen 600 mm x 600 mm panels were produced in gloss and matt grey, white and blue finishes. Each set contained the same 32 different sized machined dents representing Ø20 mm and Ø87 mm hemispherical tip impact damage to 17ply & 33ply painted CFRP laminate. Each facsimile specimen set was combined with similarly finished unflawed (dent free) panels. 64 panels in each colour/ finish were presented for 5 seconds in a randomised order to a minimum of 15 novice participants in a visual inspection task lasting approximately 25 minutes. II A set of corresponding visual inspection experiments were performed in which physical specimens were replaced by digitally projected actual size photorealistic images of the machining CAD data. Comparisons between the results of the physical and virtual specimen trials revealed differences in detectability for similarly sized dents. The detection results obtained from visual inspection of physical specimens demonstrated that the detectability of dents similar to those caused by higher (>40J) energy impacts from a Ø87 mm hemispherical tip was less than that of the dents caused by lower energy (<20J) impacts from Ø20 mm tips. However, larger subsurface delamination area was demonstrated by the higher energy Ø87 mm impacts than lower energy Ø20 mm impacts on 150 mm x 100 mm coupons of the same thickness laminate. The results of these experiments imply that detectability of dents caused by larger diameter objects at higher energies cannot be assumed to be greater than that of lower energy impacts from smaller diameter objects. The detection results demonstrate that detectability by visual inspection cannot be assumed the same for an impact dent on different surface colours and finishes. In general terms, the highest numbers of dents returning >90% detection were observed on grey specimens and the highest number of dents returning 0% detection were observed on matt blue specimens. The difference in detection rates for similarly sized dents on a gloss and matt finish was least on grey coloured specimens and greatest on blue coloured specimens.
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Bineid, Mansour. "Aircraft systems design methodology and dispatch reliability prediction." Thesis, Cranfield University, 2005. http://dspace.lib.cranfield.ac.uk/handle/1826/5415.

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Aircraft despatch reliability was the main subject of this research in the wider content of aircraft reliability. The factors effecting dispatch reliability, aircraft delay, causes of aircraft delays, and aircraft delay costs and magnitudes were examined. Delay cost elements and aircraft delay scenarios were also studied. It concluded that aircraft dispatch reliability is affected by technical and non-technical factors, and that the former are under the designer's control. It showed that the costs of aircraft delays are very significant and must be reduced. Cont/d.
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Vaziry-Zanjany, Mohammad Ali. "Aircraft conceptual design modelling incorporating reliability and maintainability predictions." Thesis, Cranfield University, 1996. http://dspace.lib.cranfield.ac.uk/handle/1826/3437.

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A computer assisted conceptual aircraft design program has been developed (CACAD). It has an optimisation capability, with extensive break-down in maintenance costs. CACAD's aim is to optimise the size, and configurations of turbofan-powered transport aircraft. A methodology was developed to enhance the reliability of current aircraft systems, and was applied to avionics systems. R&M models of thermal management were developed and linked with avionics failure rate and its maintenance cost prediction methods. The impact of the environmental control system, and engine-provided bleed flow was also modelled and incorporated into CACAD. The program showed the ARINC 600 & 408A flow rates to the avionics bay, and to the deck instruments may both profitably be increased by 50%. This keeps the direct operating cost (DOC) increase at bay for long-range passenger aircraft, and offers a reduction of up to 1% in DOC for the short to medium range passenger aircraft. A methodology was developed to model all aspects of future high risk technologies, with special consideration given to reliability, maintainability, and development cost (R, M&D) predictions as applied to variable camber wings (VCW). Many aspects of VCW were modelled. These included different types of drag saving due to chord- wise, as well as span-wise camber variation. Models were also derived for mass, maintenance cost, and extra development cost increments for wing trailing edge devices, flight control, and hydraulic systems. On incorporation into CACAD, a reduction in DOC of up to 3.5% was predicted. The VCW technology were evaluated for DOC improvements, against a number of existing, future, and derivative aircraft, under different sensitivity conditions. R, M&D predictions were shown to be decisive in addressing the feasibility of a new technology. The R&M predictions of the whole study shows that, long range, low to medium capacity derivative transport aircraft are most appropriate for the VCW technology, and the short to medium range, low to medium capacity aircraft are most suitable for reliability enhancement projects of aircraft advanced systems.
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Vaziry-Zanjany, Mohammad Ali (F). "Aircraft conceptual design modelling incorporating reliability and maintainability predictions." Thesis, Cranfield University, 1996. http://hdl.handle.net/1826/3437.

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A computer assisted conceptual aircraft design program has been developed (CACAD). It has an optimisation capability, with extensive break-down in maintenance costs. CACAD's aim is to optimise the size, and configurations of turbofan-powered transport aircraft. A methodology was developed to enhance the reliability of current aircraft systems, and was applied to avionics systems. R&M models of thermal management were developed and linked with avionics failure rate and its maintenance cost prediction methods. The impact of the environmental control system, and engine-provided bleed flow was also modelled and incorporated into CACAD. The program showed the ARINC 600 & 408A flow rates to the avionics bay, and to the deck instruments may both profitably be increased by 50%. This keeps the direct operating cost (DOC) increase at bay for long-range passenger aircraft, and offers a reduction of up to 1% in DOC for the short to medium range passenger aircraft. A methodology was developed to model all aspects of future high risk technologies, with special consideration given to reliability, maintainability, and development cost (R, M&D) predictions as applied to variable camber wings (VCW). Many aspects of VCW were modelled. These included different types of drag saving due to chord- wise, as well as span-wise camber variation. Models were also derived for mass, maintenance cost, and extra development cost increments for wing trailing edge devices, flight control, and hydraulic systems. On incorporation into CACAD, a reduction in DOC of up to 3.5% was predicted. The VCW technology were evaluated for DOC improvements, against a number of existing, future, and derivative aircraft, under different sensitivity conditions. R, M&D predictions were shown to be decisive in addressing the feasibility of a new technology. The R&M predictions of the whole study shows that, long range, low to medium capacity derivative transport aircraft are most appropriate for the VCW technology, and the short to medium range, low to medium capacity aircraft are most suitable for reliability enhancement projects of aircraft advanced systems.
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Chu, Liu. "Reliability and optimization, application to safety of aircraft structures." Thesis, Rouen, INSA, 2016. http://www.theses.fr/2016ISAM0008/document.

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Les chercheurs dans le domaine de la conception aérodynamique et de la fabrication des avions ont fait beaucoup d'effort pour améliorer les performances des ailes par des techniques d'optimisation. Le développement de la mécanique des fluides numérique a permis de réduire les dépenses en soufflerie tout en fournissant des résultats convaincants pour simuler des situations compliquées des aéronefs. Dans cette thèse, il a été choisi une partie spéciale et importante de l'avion, à savoir, la structure de l'aile. L'optimisation basée sur la fiabilité est une méthode plus appropriée pour les structures sous incertitudes. Il se bat pour obtenir le meilleur compromis entre le coût et la sécurité tout en tenant compte des incertitudes du système en intégrant des mesures de fiabilité au sein de l'optimisation. Malgré les avantages de l'optimisation de la fiabilité en fonction, son application à un problème d'ingénierie pratique est encore assez difficile. Dans notre travail, l'analyse de l'incertitude dans la simulation numérique est introduite et exprimée par la théorie des probabilités. La simulation de Monte Carlo comme une méthode efficace pour propager les incertitudes dans le modèle d'éléments finis de la structure est ici appliquée pour simuler les situations compliquées qui peuvent se produire. Pour améliorer l'efficacité de la simulation Monte Carlo dans le processus d'échantillonnage, la méthode de l'Hypercube Latin est effectuée. Cependant, l'énorme base de données de l'échantillonnage rend difficile le fait de fournir une évaluation explicite de la fiabilité. L'expansion polynôme du chaos est présentée et discutée. Le modèle de Kriging comme un modèle de substitution joue un rôle important dans l'analyse de la fiabilité. Les méthodes traditionnelles d'optimisation ont des inconvénients à cause du temps de calcul trop long ou de tomber dans un minimum local causant une convergence prématurée. Le recuit simulé est une méthode heuristique basée sur une recherche locale, les Algorithmes Génétiques puisent leur inspiration dans les principes et les mécanismes de la sélection naturelle, qui nous rendent capables d'échapper aux pièges des optimums locaux. Dans l'optimisation de la conception de base de la fiabilité, ces deux méthodes ont été mises en place comme procédure d'optimisation. La boucle de l'analyse de fiabilité est testée sur le modèle de substitution
Tremendous struggles of researchers in the field of aerodynamic design and aircraft production were made to improve wing airfoil by optimization techniques. The development of computational fluid dynamic (CFD) in computer simulation cuts the expense of aerodynamic experiment while provides convincing results to simulate complicated situation of aircraft. In our work, we chose a special and important part of aircraft, namely, the structure of wing.Reliability based optimization is one of the most appropriate methods for structural design under uncertainties. It struggles to seek for the best compromise between cost and safety while considering system uncertainties by incorporating reliability measures within the optimization. Despite the advantages of reliability based optimization, its application to practical engineering problem is still quite challenging. In our work, uncertainty analysis in numerical simulation is introduced and expressed by probability theory. Monte Carlo simulation as an effective method to propagate the uncertainties in the finite element model of structure is applied to simulate the complicate situations that may occur. To improve efficiency of Monte Carlo simulation in sampling process, Latin Hypercube sampling is performed. However, the huge database of sampling is difficult to provide explicit evaluation of reliability. Polynomial chaos expansion is presented and discussed. Kriging model as a surrogate model play an important role in the reliability analysis.Traditional methods of optimization have disadvantages in unacceptable time-complexity or natural drawbacks of premature convergence because of finding the nearest local optima of low quality. Simulated Annealing is a local search-based heuristic, Genetic Algorithm draws inspiration from the principles and mechanisms of natural selection, that makes us capable of escaping from being trapped into a local optimum. In reliability based design optimization, these two methods were performed as the procedure of optimization. The loop of reliability analysis is running in surrogate model
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Alkhatib, K. Y. "Analytical redundancy scheme for improving reliability of automatic flight control systems for aircraft." Thesis, Loughborough University, 1985. https://dspace.lboro.ac.uk/2134/31989.

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Any redundancy scheme in aircraft control systems is usually considered separately from the control algorithms involved. All feedback control systems are usually designed under the assumption that their sensors will not fail. When the integrity requirements demand it, then a redundancy scheme must be designed to provide any required measurements with only extremely short interruptions to normal service being caused by failures of individual sensors.
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King, Merrill F. "A reliability centered maintenance analysis of aircraft control bearings used in the Navy's S-3 aircraft." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA342292.

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Thesis (M.S. in Management) Naval Postgraduate School, December 1997.
"December 1997." Thesis advisor(s): Keebom Kang, Donald R. Eaton. Includes bibliographical references (p. 73-74). Also available online.
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Dermentzoudis, Marinos. "Establishment of models and data tracking for small UAV reliability." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Jun%5FDermentzoudis.pdf.

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Thesis (M.S. in Operations Research and M.S. in Systems Engineering)--Naval Postgraduate School, June 2004.
Thesis advisor(s): David Olwell. Includes bibliographical references (p. 217-224). Also available online.
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Books on the topic "Aircraft reliability"

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Howell, J. M. Reliability and maintainability. Neuilly sur Seine, France: AGARD, 1995.

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Cook, M. V. A summary report on an experimental investigation into methods for quantifying hang glider airworthiness parameters. Cranfield, U.K: College of Aeronautics, Cranfield Institute of Technology, 1987.

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Kacprzynski, Jerzy J. Reliability studies of finite element methods in North America. Neuilly sur Seine, France: AGARD, 1987.

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Baldwin, Richard P. Aircraft engine reliability analysis using lower confidence limit estimate procedures. Monterey, Calif: Naval Postgraduate School, 1992.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. AGARD/SMP review damage tolerance for engine structures. 4. Reliability and quality assurance. Neuilly sur Seine, France: AGARD, 1991.

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King, Merrill F. A reliability centered maintenance analysis of aircraft control bearings used in the Navy's S-3 aircraft. Monterey, Calif: Naval Postgraduate School, 1997.

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Lameris, J. The use of load enhancement factors in the certification of composite aircraft structures. Amsterdam: National Aerospace Laboratory, 1990.

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Megson, T. H. G. Aircraft structures forengineering students. 2nd ed. New York: Halsted Press, 1990.

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Lock, M. W. B. Reliability of in-service inspection of transport aircraft structures: ARB Fellowship1981 - final report. London: Civil Aviation Authority, 1985.

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Savage, M. Life and dynamic capacity modeling for aircraft transmissions. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Book chapters on the topic "Aircraft reliability"

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Lapesa Barrera, David. "Aircraft Induction." In Springer Series in Reliability Engineering, 195–96. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-90263-6_14.

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Tiassou, Kossi, Karama Kanoun, Mohamed Ka, Christel Seguin, and Chris Papadopoulos. "Modeling Aircraft Operational Reliability." In Lecture Notes in Computer Science, 157–70. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-24270-0_12.

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Manning, S. D., J. N. Yang, and J. L. Rudd. "Durability of aircraft structures." In Probabilistic fracture mechanics and reliability, 213–67. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-017-2764-8_5.

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Ladkin, Peter B. "Causal Reasoning about Aircraft Accidents." In Computer Safety, Reliability and Security, 344–60. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/3-540-40891-6_30.

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Lapesa Barrera, David. "AMP Secondary Sources: Aging Aircraft." In Springer Series in Reliability Engineering, 87–93. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-90263-6_7.

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Hooke, F. H. "Aircraft structural reliability and risk analysis." In Probabilistic fracture mechanics and reliability, 131–70. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-017-2764-8_3.

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Chan, K. W., G. J. Trmal, A. P. H. May, and G. Southcombe. "Reliability of Aircraft High Lift Devices." In COMADEM 89 International, 104–10. Boston, MA: Springer US, 1989. http://dx.doi.org/10.1007/978-1-4684-8905-7_16.

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Markling, Gilbert, and Göran Holmberg. "The Viggen Aircraft Radar, Reliability Achievement." In Reliability Data Collection and Use in Risk and Availability Assessment, 301–13. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-642-82773-0_31.

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Man, Wai Yeung, and Eric T. T. Wong. "Developing Alert Level for Aircraft Components." In Springer Series in Reliability Engineering, 85–106. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-43412-0_6.

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Schagaev, Igor, and Brian Robinson Kirk. "Aircraft Flight Reliability and the Safety Landscape of Aircraft Use." In Active System Control, 73–98. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-46813-6_3.

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Conference papers on the topic "Aircraft reliability"

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Iden, Steven M., and Angela Morris. "High Reliability Aircraft Generator System." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1988. http://dx.doi.org/10.4271/881414.

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Ming, Li, Wang Peng, Shan Xingjian, and Wang Lulu. "Reliability allocation for aircraft engines." In 2017 Prognostics and System Health Management Conference (PHM-Harbin). IEEE, 2017. http://dx.doi.org/10.1109/phm.2017.8079162.

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GEBMAN, JEAN. "Avionics maintainability - More important than reliability." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2096.

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Hauter, A. J. "Equipment Reliability Real and Perceived." In General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871038.

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ETZL, JULIUS, RICHARD BRANDAU, CHARLES FISCHER, and JAMES OAKES. "Automated Reliability Expert System - ARES." In Aircraft Design, Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2944.

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Shi, Pan, and Sankaran Mahadevan. "Aircraft structures reliability under corrosion fatigue." In 19th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-1377.

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Spencer, Floyd W. "Visual inspection reliability of transport aircraft." In Nondestructive Evaluation Techniques for Aging Infrastructure and Manufacturing, edited by Raymond D. Rempt and Alfred L. Broz. SPIE, 1996. http://dx.doi.org/10.1117/12.259089.

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Rýzek, Dušan, and Martin Bugaj. "Maintenance and reliability of aircraft technology." In Práce a štúdie. University of Zilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.2.36.

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The paper deals with the maintenance and influencing the human factor in aircraft maintenance. The work is divided into three basic parts. In the first part of the paper, the aim was to describe the maintenance from a historical point of view, to describe the individual stages of maintenance and to summarize how to maintain the years of development. We also have specified individual types of maintenance, maintenance intervals. The most extensive part in the theory are the laws and regulations that must comply with when performing maintenance in the Slovak Republic. This part is indeed included, but we consider it important to mention it in the work. The second part of the paper is the analysis of accidents of commercial aircraft in commercial aviation for the last 3 years. The analysis contains 43 accidents, from which we came to a conclusion. In the first part of the analysis, we selected those accidents that occurred due to maintenance, and then from these accidents, we further determined which accidents occurred due to human error in maintenance. The aim was to determine whether the number of accidents in commercial aviation in civil aviation due to maintenance should increase or decrease, and subsequently, whether the number of accidents in terms of human factor inmaintenance would increase or decrease. The last part so the conclusion is of course focused on the evaluation of the results of the analytical part and the declaration of whether we managed to meet the goal of the paper.
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Fielding, J., and M. Vaziry-Z. "Avionics reliability modelling for aircraft conceptual design." In Aircraft Engineering, Technology, and Operations Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3906.

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MCCANN, CATHERINE, and DANIEL PALUMBO. "Reliability Model Generator for fault-tolerant systems." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4435.

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Reports on the topic "Aircraft reliability"

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La Porte, Todd R., Karlene Roberts, and Gene I. Rochlin. Aircraft Carrier Operations at Sea: The Challenges of High Reliability Performance. Fort Belvoir, VA: Defense Technical Information Center, July 1988. http://dx.doi.org/10.21236/ada198692.

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Marangoni-Simonsen, David. Development of Predictive Models for Fleet Reliability in the Aircraft Industry. Office of Scientific and Technical Information (OSTI), October 2017. http://dx.doi.org/10.2172/1761807.

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Tuegel, Eric J., Robert P. Bell, Alan P. Berens, Thomas Brussat, Joseph W. Cardinal, Joseph P. Gallagher, and James Rudd. Aircraft Structural Reliability and Risk Analysis Handbook Volume 1: Basic Analysis Methods. Fort Belvoir, VA: Defense Technical Information Center, June 2013. http://dx.doi.org/10.21236/ada587824.

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Sutin, Alexander. Quantitative Nondestructive Evaluation and Reliability Assessment of the Aging Aircraft Structure Components. Fort Belvoir, VA: Defense Technical Information Center, April 2000. http://dx.doi.org/10.21236/ada377667.

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Zishang, Li, and Mao Jingli. An Analysis Of The Reliability And Maintainability Of The Jian 6 And Jian 7 Aircraft And Ways To Improve Them. Fort Belvoir, VA: Defense Technical Information Center, January 1993. http://dx.doi.org/10.21236/ada261060.

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Seale, Maria, Natàlia Garcia-Reyero, R. Salter, and Alicia Ruvinsky. An epigenetic modeling approach for adaptive prognostics of engineered systems. Engineer Research and Development Center (U.S.), July 2021. http://dx.doi.org/10.21079/11681/41282.

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Prognostics and health management (PHM) frameworks are widely used in engineered systems, such as manufacturing equipment, aircraft, and vehicles, to improve reliability, maintainability, and safety. Prognostic information for impending failures and remaining useful life is essential to inform decision-making by enabling cost versus risk estimates of maintenance actions. These estimates are generally provided by physics-based or data-driven models developed on historical information. Although current models provide some predictive capabilities, the ability to represent individualized dynamic factors that affect system health is limited. To address these shortcomings, we examine the biological phenomenon of epigenetics. Epigenetics provides insight into how environmental factors affect genetic expression in an organism, providing system health information that can be useful for predictions of future state. The means by which environmental factors influence epigenetic modifications leading to observable traits can be correlated to circumstances affecting system health. In this paper, we investigate the general parallels between the biological effects of epigenetic changes on cellular DNA to the influences leading to either system degradation and compromise, or improved system health. We also review a variety of epigenetic computational models and concepts, and present a general modeling framework to support adaptive system prognostics.
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Webb, Philip, and Sarah Fletcher. Unsettled Issues on Human-Robot Collaboration and Automation in Aerospace Manufacturing. SAE International, November 2020. http://dx.doi.org/10.4271/epr2020024.

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This SAE EDGE™ Research Report builds a comprehensive picture of the current state-of-the-art of human-robot applications, identifying key issues to unlock the technology’s potential. It brings together views of recognized thought leaders to understand and deconstruct the myths and realities of human- robot collaboration, and how it could eventually have the impact envisaged by many. Current thinking suggests that the emerging technology of human-robot collaboration provides an ideal solution, combining the flexibility and skill of human operators with the precision, repeatability, and reliability of robots. Yet, the topic tends to generate intense reactions ranging from a “brave new future” for aircraft manufacturing and assembly, to workers living in fear of a robot invasion and lost jobs. It is widely acknowledged that the application of robotics and automation in aerospace manufacturing is significantly lower than might be expected. Reasons include product variability, size, design philosophy, and relatively low volumes. Also, the occasional reticence due to a history of past false starts plays a role too. Unsettled Issues on Human-Robot Collaboration and Automation in Aerospace Manufacturing goes deep into the core questions that really matter so the necessary step changes can move the industry forward.
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