Zeitschriftenartikel: „Aircraft reliability“

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Hauka, Maris, und Jurijs Paramonovs. „Airline and Aircraft Reliability“. Transport and Aerospace Engineering 1 (08.05.2014): 9. http://dx.doi.org/10.7250/tae.2014.002.

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Wang, Zhipeng, Zhiqin Qian, Ziye Song, Hongzhou Liu, Wenjun Zhang und Zhuming Bi. „Instrumentation and self-repairing control for resilient multi-rotor aircrafts“. Industrial Robot: An International Journal 45, Nr. 5 (20.08.2018): 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 und Mariusz Michalski. „Reliability Assessment of Aircraft Commutators“. Energies 14, Nr. 21 (06.11.2021): 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 und MARCEL MONGEAU. „COMPUTING IN-SERVICE AIRCRAFT RELIABILITY“. International Journal of Reliability, Quality and Safety Engineering 16, Nr. 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, und Jianghua Zhang. „Mechanical Structure Design of the Aircraft ASD Control Isolation Control“. Journal of Applied Mathematics 2022 (16.11.2022): 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 und Yi Chen. „Characteristic of Corrosive Damages about Aircraft Structures in Service“. Applied Mechanics and Materials 543-547 (März 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 und Zhiqiang Wei. „The Study on Dispatch Reliability Prediction Model of Civil Aircraft“. Open Mechanical Engineering Journal 8, Nr. 1 (31.12.2014): 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 und De Feng Lv. „A Method to Reliability Analysis of the Aircraft’s Structural Component“. Advanced Materials Research 452-453 (Januar 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 (Dezember 2017): 687–94. http://dx.doi.org/10.1016/j.engfailanal.2017.06.008.

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Tang, Hong, Guo Guang Chen und 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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Bohata, Jan, Michael Písarík, Stanislav Zvánovec und Pavel Peterka. „Reliability of aircraft multimode optical networks“. Optical Engineering 53, Nr. 9 (03.09.2014): 096102. http://dx.doi.org/10.1117/1.oe.53.9.096102.

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Kamiyama, Takayuki, und Yujiro Yoshida. „Reliability of adhesive for aircraft structure.“ Kobunshi 35, Nr. 7 (1986): 666–69. http://dx.doi.org/10.1295/kobunshi.35.666.

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Zhou, Qiang, Yongan Wei und Longjiang Zhu. „Research on reliability modeling of unmanned aircraft system avionics systems based on 5G“. International Journal of Distributed Sensor Networks 15, Nr. 7 (Juli 2019): 155014771986038. http://dx.doi.org/10.1177/1550147719860381.

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With the development of technology, an unmanned aircraft system will play a significant role in Internet of things based on 5G. Avionics system is an important part of the unmanned aircraft system, and the reliability of the avionics system directly determines the ability to perform missions. This article deals with the problem of reliability modeling with unmanned aircraft system avionics systems built on Internet of things in the 5G scenario. First, based on the composition of the avionics system, the network structure of the unmanned aircraft system avionics system is presented. Then, to evaluate the reliability, a task model of the unmanned aircraft system avionics system is proposed. Finally, an illustration of unmanned aircraft system reliability performing reconnaissance is also presented. By analyzing the task performance, it is shown that redundancy design of the units can improve the reliability of the unmanned aircraft system avionics system.

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Wang, Yuhui, Peng Shao, Qingxian Wu und Mou Chen. „Reliability analysis for a hypersonic aircraft’s wing spar“. Aircraft Engineering and Aerospace Technology 91, Nr. 4 (01.04.2019): 549–57. http://dx.doi.org/10.1108/aeat-11-2017-0242.

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Purpose This paper aims to present a novel structural reliability analysis scheme with considering the structural strength degradation for the wing spar of a generic hypersonic aircraft to guarantee flight safety and structural reliability. Design/methodology/approach A logarithmic model with strength degradation for the wing spar is constructed, and a reliability model of the wing spar is established based on stress-strength interference theory and total probability theorem. Findings It is demonstrated that the proposed reliability analysis scheme can obtain more accurate structural reliability and failure results for the wing spar, and the strength degradation cannot be neglected. Furthermore, the obtained results will provide an important reference for the structural safety of hypersonic aircraft. Research limitations/implications The proposed reliability analysis scheme has not implemented in actual flight, as all the simulations are conducted according to the actual experiment data. Practical implications The proposed reliability analysis scheme can solve the structural life problem of the wing spar for hypersonic aircraft and meet engineering practice requirements, and it also provides an important reference to guarantee the flight safety and structural reliability for hypersonic aircraft. Originality/value To describe the damage evolution more accurately, with consideration of strength degradation, flight dynamics and material characteristics of the hypersonic aircraft, the stress-strength interference method is first applied to analyze the structural reliability of the wing spar for the hypersonic aircraft. The proposed analysis scheme is implemented on the dynamic model of the hypersonic aircraft, and the simulation demonstrates that a more reasonable reliability result can be achieved.

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Kosacki, Kamil, und Andrzej Tomczyk. „APPLICATION OF ANALYTICAL REDUNDANCY OF MEASUREMENTS TO INCREASE THE RELIABILITY OF AIRCRAFT ATTITUDE CONTROL“. Aviation 26, Nr. 3 (12.10.2022): 138–44. http://dx.doi.org/10.3846/aviation.2022.17555.

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

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Zhao, Hongxu. „New method for estimating the grounding reliability test of aircraft cable shield“. Functional materials 23, Nr. 4 (24.03.2017): 184–89. http://dx.doi.org/10.15407/fm24.01.184.

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Lei, Zhang, und Jing Yachao. „Research on Comprehensive Evaluation of Military Aircrafts’ Overhaul Performance Based on Entropy Weight and Cloud Model“. E3S Web of Conferences 257 (2021): 02065. http://dx.doi.org/10.1051/e3sconf/202125702065.

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Due to the complex evaluation of the current military aircrafts’ overhaul performance with many influencing factors, an evaluation index system of military aircrafts’ overhaul performance was constructed. It was proposed that the entropy weight method (EWM) was used to calculate the performance results, and then the performance of the reliability and validity of the results was verified based on the cloud model. By collecting the performance index data of a certain type of military aircraft overhaul from 2015 to 2018, the value of the overhaul performance of this type of military aircraft was calculated, and the feasibility and effectiveness of the method were verified.

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Hu, Jian Jun, Yue Liang Chen, Xiao Ming Tan, Gui Xue Bian und Li Xu. „Investigation on Random Parameters of Aircraft Structural Reliability Model“. Advanced Materials Research 378-379 (Oktober 2011): 51–55. http://dx.doi.org/10.4028/www.scientific.net/amr.378-379.51.

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By studying on reliability model of aircraft structure holistic life assessment, several random parameters are chosen to analyze the randomness of aircraft structure life in this document, the sensitivity of random parameters is investigated to determine the important parameters. The fuzzy random parameters are also studied in this document, the influence of these parameters to aircraft structure reliability is analyzed in the final.

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Owen, C. R., R. J. Bucci und R. J. Kegarise. „Aluminum quality breakthrough for aircraft structural reliability“. Journal of Aircraft 26, Nr. 2 (Februar 1989): 178–84. http://dx.doi.org/10.2514/3.45741.

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Mahadevan, Sankaran, und Pan Shi. „Corrosion fatigue reliability of aging aircraft structures“. Progress in Structural Engineering and Materials 3, Nr. 2 (2001): 188–97. http://dx.doi.org/10.1002/pse.77.

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Мялица, А. К., und C. Ш. Шаабдиев. „АНАЛІЗ НАДІЙНОСТІ ШАСІ РЕГІОНАЛЬНОГО ПАСАЖИРСЬКОГО ЛІТАКА АН-140 НА ПОЧАТКОВОМУ ЕТАПІ ЕКСПЛУАТАЦІЇ“. Open Information and Computer Integrated Technologies, Nr. 90 (18.06.2021): 33–44. http://dx.doi.org/10.32620/oikit.2020.90.02.

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The article presents an analysis of the reliability of the chassis of the regional passenger aircraft AN - 140 at the initial stage of operation, as well as general information about the aircraft, front and main supports of its landing gear. The average failure rate and the total number of failures over a period of time are used as reliability indicators. The calculation of reliability indicators is based on failures detected during periodic maintenance (PM) of aircraft on planned forms 1H - 4H in the maintenance organization Part - 145 and entered into defective statements in accordance with the Management Maintenance Organization. These forms are made in accordance with the Aircraft Maintenance Manual of AN - 140 with a frequency of 500±50 flight hours. To analyze the reliability of the chassis selected a fleet of six aircraft AN - 140 and AN - 140 - 100 with a total flight of 12,000 hours and is divided into three groups by the date of their manufacture and the improvements made on them - "Leader Planes," "Refined Aircraft" and "Serial Aircraft". The condition of sampling the fleet of aircraft is the flight time of 2000 hours for each instance and the execution of four forms of PM on a swoop to form 4N. The dependence of the number of failures of the landing gear of each aircraft on the shape of the PM, the average flight of failure of the fleet and each aircraft individually, the total number of failures of the landing system for each instance of the aircraft, the most denied elements of the main and front landing gear of the aircraft are presented.Based on the results of the analysis of these reliability indicators, both generalized conclusions on the distribution of the number of failures by groups and aircraft instances, and on the specific most denied elements of the chassis system as a whole are presented. The tendency to reduce the number of failures and increase the average flight to failure, depending on the duration of aircraft operation and the manufacture date, has been revealed.

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LUCULESCU, Doru. „CONSIDERATIONS REGARDING THE RELIABILITY ASSESSMENT OF THE ROLLER BEARING PROVIDING MOVEMENT IN THE DIRECTION OF ANTI-AIRCRAFT GUNS“. Review of the Air Force Academy 19, Nr. 1 (27.09.2021): 47–52. http://dx.doi.org/10.19062/1842-9238.2021.19.1.5.

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This paper analyzes a method of evaluating the reliability of the rolling bearing in anti-aircraft guns. In evaluating its reliability, the factors that depend on the operating conditions of the anti-aircraft gun are taken into account, as well as the factors of design, technology, materials and assembly

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Booker, Julian, Caius Patel und Phillip Mellor. „Modelling Green VTOL Concept Designs for Reliability and Efficiency“. Designs 5, Nr. 4 (28.10.2021): 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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ROMANCHENKO, Ihor S., Oleh SEMENENKO, Maryna SLIUSARENKO, Mykola VASIANOVYCH und Ihor LEVCHENKO. „On the development of mathematical models for the reliability evaluation of aircraft operation in combat conditions“. INCAS BULLETIN 13, S (03.08.2021): 169–78. http://dx.doi.org/10.13111/2066-8201.2021.13.s.16.

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The authors of this study propose a methodological approach to modelling the reliability evaluation of aircraft operation in combat conditions. When developing recommendations on operational and strategic requirements for promising aircraft, a very important aspect is the elicitation of the requirements for their reliability, namely no-failure operation. Reliability as a parameter of any equipment should be set in the technical specifications for development together with other operational requirements in the form of reasonable quantitative indicators – reliability standards. The establishment of specific reliability standards stimulates its growth and creates the basis for rational design, taking into account the requirements of reliable operation. The analysis showed that different models can be used to simulate aircraft reliability. In this case, for example, the final values of mean time to failure (MTTF) would be different. The test results show that the methods and mathematical models used to substantiate the values of time and probability of trouble-free operation of aircraft do not fully correspond to the actual processes of changing their state during the use in the military. This is confirmed by a significant discrepancy in the values of reliability indicators implemented in practice. This was due to the fact that the acquainted mathematical models of aircraft reliability do not take into account the combat conditions in which they are supposed to operate. In addition, the reliability indicators used do not take into account possible changes (decrease) in these indicators during the period of aircraft operation. In general, the shortcomings inherent in the methods and mathematical models currently used to describe the aircraft reliability reduce the accuracy of the results obtained, and also do not quite adequately reflect the features of the corresponding process. When using different models, the cost of time to failure differs significantly. The more factors are taken into account, the greater the operating time to failure will be. This means that when designing aircraft, it is necessary to set the value of this indicator greater than indicated in the form. Taking into account additional factors complicates the model, but at the same time makes it more accurate.

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Zhang, Xing Yuan, Hai Rong Xu, Da Min Cao und Sheng Bin Hu. „Reliability Assessment Using Fuzzy Evidence Theory“. Applied Mechanics and Materials 220-223 (November 2012): 2165–68. http://dx.doi.org/10.4028/www.scientific.net/amm.220-223.2165.

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Aiming at many uncertain factors in the reliability assessment of aircraft, a new approach to reliability assessment combining D-S theory of evidence and fuzzy theory was discussed. The concepts of inclusion degree and intersection degree of fuzzy sets were redefined, and fuzzy evidence theory was extended to the circumstance when the framework of discrimination is a continuous and in finite set. Finally, the practical assessment process was given in an illustrative example of aircraft system. The results show that the method is effective and reliable.

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Glowacki, Pawel Jan, Leszek Loroch und Wlodzimierz Balicki. „Operations reliability study of small aircraft powered by piston engines“. Aircraft Engineering and Aerospace Technology 92, Nr. 3 (12.10.2018): 285–95. http://dx.doi.org/10.1108/aeat-01-2018-0005.

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Purpose Europe has adopted Flight Path 2050 (FP 2050) challenge with an objective of 90 per cent of the travelers being able to reach door-to-door European destinations within 4 hours by 2050. The aim can be achieved by reliable, well-organized small aircraft transport (SAT). Analysis of the currently operating small aircraft operational reliability data will support the development of future aircraft designs as well as reliability and safety requirements necessary for commercial operations. Design/methodology/approach The paper provides results of a statistical analysis of small aircraft current operations based on the reported events contained in the Database named European Coordination Centre for Aviation Incident Reporting Systems database. It presents identified safety indicators and focuses particularly on those related to the aviation technology. Findings It has been found that certain airframe and powerplant systems have the biggest influence on flight safety. Practical implications Multidisciplinary analysis of the operational and aircraft components reliability data will help in a proper preparation of the SAT supporting facilities, a design process of new aircraft and improvements of the existing airframe and powerplant systems. Originality/value Presented results are valuable for further developments of the statistical tools facilitating new product introduction.

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Qi, Xuanxuan, Jian’an Cao und Xiaojiao Li. „Reliability Evaluation of Power Supply for More-Electric-Aircraft Based on Information Entropy“. MATEC Web of Conferences 288 (2019): 02002. http://dx.doi.org/10.1051/matecconf/201928802002.

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In order to overcome the shortcomings of traditional power supply reliability evaluation model of multi-electric aircraft in the process of multi-component system research, this paper introduces the approximate probability distribution of multi-component system by cross-entropy, it proposes a Monte Carlo method based on information entropy to evaluate the power supply reliability of multi-electric aircraft, and obtains the approximate probability distribution by differential evolution to make the reliability evaluation. The estimated variance is approximately zero. Finally, taking an aircraft power supply system as an example, the convergence and accuracy of several reliability analysis methods are compared and analyzed. The results show the superiority of this method.

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Yan, Chu Liang, und K. G. Liu. „Fatigue Scatter Factor of Whole Life and Reliability of Aircraft Structure Service Life“. Advanced Materials Research 44-46 (Juni 2008): 739–44. http://dx.doi.org/10.4028/www.scientific.net/amr.44-46.739.

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The prediction of aircraft structure service life is of great importance to safety of aircraft structure and human beings. The relation between aircraft structure service life and reliability can be found by utilizing the fatigue scatter factor of whole life. Only when the service life satisfies the requirements of reliability, can the safety of airplane be ensured. The fatigue scatter factors of the service life accords with lognormal distribution and Weibull distribution were studied to provide important reference for predicting the safe service life of aircraft structure.

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Ng, Yang Siong Robson, und Hamad Rashid. „Enhancing human performance reliability in aircraft pushback operations“. International Journal of Quality & Reliability Management 36, Nr. 4 (01.04.2019): 485–509. http://dx.doi.org/10.1108/ijqrm-01-2018-0008.

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Purpose The purpose of this paper is to investigate the aircraft pushback operations to predict and manage human errors, particularly those associated with the complex team work of carrying out the pushback operation. This should improve air ramp operations reliability. Design/methodology/approach The study applied the human reliability assessment “Systematic Human Error Reduction and Prediction Approach” that involved a total of 60 semi-structured interviews with practicing experts. Past ramp accident reports were also reviewed to provide more in-depth insights to the problem. Findings Some of the key performance reliability-degrading errors identified relate to some frequent critical technical inabilities within the team of headset operator and tug driver, as well as the vulnerable intra-team communications. Several best practices were similarly identified. Practical implications Based on its findings, this study proposes a new technological concept that can help enhancing safety of aircraft pushback operations. This should enhance reliability of aircraft ground handling and improve aircraft availability. It also provided a generic methodological approach to improve safety-critical operations within high-risk industries. Social implications This study responses to the increasing trend in ramp accidents worldwide. Originality/value The research conducted to date in this area is still quite limited compared to that of flight and aircraft maintenance safety. The relevant existing studies focus more on ramp safety holistically, and do not go into the details of how safety and reliability of a ramp operation can be improved. The current paper aims at filling this gap.

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Xia, Qing, Man Li, Zong Jie Cao und Hong Wei Wang. „The Study of Reliability in MDO of Aircraft“. Applied Mechanics and Materials 226-228 (November 2012): 598–601. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.598.

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MDO and reliability design are independently processed in the traditional aircraft design. The designs process is thus consuming compute intensive, so that integrated design of MDO and reliability is required. To achieve the integration, there are two problems needed to be solved. First, a reliability function needs to be expressed by performance design parameters in a probability form. Second, the reliability function needs to be imported into MDO arithmetic. For the first one, stress-strength interference theory is useful. According to the theory, performance design parameters are described in the formulas which calculate probability of reliability. For the second, the reliability function is considered as a part of optimization objective functions or as a constraint function. The simulation of aircraft design shows that the above method is useful and effective to the actual project.

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Brewer, Roger. „High Reliability Electronics for Demanding Aircraft Applications – An Overview“. Additional Conferences (Device Packaging, HiTEC, HiTEN, and CICMT) 2016, HiTEC (01.01.2016): 000011–17. http://dx.doi.org/10.4071/2016-hitec-11.

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

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Chen, Jiu Sheng, und Xiao Yu Zhang. „Model of the Scheduled Aircraft Maintenance Plan Based on Reliability“. Applied Mechanics and Materials 195-196 (August 2012): 623–26. http://dx.doi.org/10.4028/www.scientific.net/amm.195-196.623.

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The scheduled aircraft maintenance mode inevitably results in gradually descending reliability of avionics equipment with the increasing service cycle and maintenance frequency. The reliability predictive method is established based on data fusion. It can realize the predictive evaluation of avionics equipment reliability. The method of defining optimum maintenance cycle on scheduled aircraft maintenance is under the MSG-3 framework at presented.

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Zieja, Mariusz, und Piotr Barszcz. „Determination of time intervals between subsequent corrosion inspections based on the example of the TS-11 ‘Iskra’ aircraft/Wyznaczanie okresów wykonywania przeglądów korozyjnych na przykładzie samolotu TS-11 „Iskra”“. Journal of KONBiN 20, Nr. 1 (01.12.2011): 141–58. http://dx.doi.org/10.2478/v10040-012-0043-3.

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Abstract When the operation is driven by the actual technical condition of the equipment with current monitoring of the reliability level the problem appears how to schedule inspections intended for restoring sound technical condition of aircrafts with regard to corrosion protective coatings and keep them permanently available for operation with determination of maintenance jobs that must be carried out in the plane. The methods that enable estimation how frequently inspections for detection of corrosion traces should be carried out include the method of characteristic sets, the Fourier spectral analysis as well as the methods of indices that reflect the process of the aircraft operation. Each of the foregoing methods is suitable for the equipment operation but the only method that takes into account the conditions that occurred during operation of the specific aircraft unit is the method of indices that reflects the process of the aircraft operation.

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Żugaj, Marcin, Przemysław Bibik und Marcin Figat. „An Unmanned Aircraft Model for Control System Reconfiguration Analysis and Synthesis“. Transactions on Aerospace Research 2017, Nr. 2 (01.06.2017): 97–116. http://dx.doi.org/10.2478/tar-2017-0018.

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Abstract Reliability of unmanned aircraft is a decisive factor for conducting air tasks in a controlled airspace. One of the means of improving unmanned aircraft reliability is reconfiguration of the control system, which will allow to maintain control over the aircraft despite an occurring failure. The control system is reconfigured by using still operational control surfaces to compensate for failure consequences and to control the damaged aircraft. Development of effective reconfiguration algorithms involves utilization of a non-linear model of unmanned aircraft dynamics, in which each control surface deflection can be controlled independently. The paper describes a non-linear model of a small unmanned aircraft with decoupled control surfaces. The paper discusses aircraft flight dynamics equations and estimated equations for controllability derivatives for each control surface, the results of comparison tests of the model and actual aircraft as well as the structure of the simulation model. The developed unmanned aircraft model may be used in development and in optimization of control algorithms for aircraft with damaged control systems as well as to test the impact of failures on dynamic properties of the aircraft.

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Zhao, Mao Tai, und Wen Qian Song. „The Study on Maintainability Design of the Air Bus A380“. Applied Mechanics and Materials 602-605 (August 2014): 465–68. http://dx.doi.org/10.4028/www.scientific.net/amm.602-605.465.

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The maintainability of aircraft has a direct relationship with the reliability, availability, security and economy of the airplane and its components. From adopting the new composite material, innovative self-test system and the close cooperation with airlines, airports and airworthiness institutions, the airbus A380 will ensure its better maintainability. This paper intends to discuss the developing and designing direction of the civil aircrafts’ maintainability in expectation of marking some active contribution to the industry of large aircrafts in China.

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Bineid, M., und J. P. Fielding. „Development of an aircraft systems dispatch reliability design methodology“. Aeronautical Journal 110, Nr. 1108 (Juni 2006): 345–52. http://dx.doi.org/10.1017/s0001924000001251.

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Abstract This paper describes the development of a generic aircraft systems dispatch reliability design methodology (ASDRDM) that has been developed for use during early phases of the aircraft systems design process. The methodology incorporates prediction of both reliability and maintainability through the aircraft design hierarchy, down to component level. It can be applied at the early design stage, but can also be used for advanced design phases and can use generic or actual failure rate and mean time to repair data. It allows designers to modify system architectures and component reliability and maintainability characteristics. The paper shows the validation that has been performed, and its use is demonstrated by a case-study.

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Liu, Sifeng, Wei Tang, Dejin Song, Zhigeng Fang und Wenfeng Yuan. „A novel GREY‒ASMAA model for reliability growth evaluation in the large civil aircraft test flight phase“. Grey Systems: Theory and Application 10, Nr. 1 (13.09.2019): 46–55. http://dx.doi.org/10.1108/gs-11-2018-0055.

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Purpose The purpose of this paper is to present a novel GREY‒ASMAA model for reliability growth evaluation in the large civil aircraft test flight phase. Design/methodology/approach As limited data are collected during the large civil aircraft test flight phase, which are not enough to meet the requirements of the ASMAA model for reliability growth, four basic GM(1, 1) models, even grey model, original difference grey model, even difference grey model and discrete grey model, are presented. Then both forward and backward grey models GM(1,1) are built to forecast and obtain virtual test data on left and right sides. Then the ASMAA model for reliability growth evaluation can be built based on original and virtual test data. Findings Aiming at the background of poor information data during the large civil aircraft test flight phase, first, a novel GREY‒ASMAA model, which was combined by the grey model GM(1,1) with the ASMAA model, has been put forward in this paper. Practical implications The GREY‒ASMAA model for reliability growth evaluation can be used to solve the problem of reliability growth evaluation with poor information data during the large civil aircraft test flight phase, and it has been used in reliability evaluation of C919 at the test flight stage. Originality/value This paper presents two new definitions of forward grey model GM(1,1) and backward grey model GM(1,1), as well as a novel GREY‒ASMAA model for reliability growth evaluation of large civil aircraft during test flight phase.

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Yang, J. N., und S. D. Manning. „Aircraft fleet maintenance based on structural reliability analysis“. Journal of Aircraft 31, Nr. 2 (März 1994): 419–25. http://dx.doi.org/10.2514/3.46502.

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Kolev, Kolyo, und Angel Tanev. „Identifying Batch Problems in Aircraft Field Reliability Analysis“. Aerospace Research in Bulgaria 34 (2022): 130–37. http://dx.doi.org/10.3897/arb.v34.e11.

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In practice, a very important task is to monitor the field reliability of aircraft systems, especially the ones related to aviation safety, and to take relevant actions to prevent from potential consequences. Zooming in that task, one can state that a very important step in that analysis is to identify batch problems where the failure mode only affects a subset of the fleet. The Weibull distribution typically provides the best fit of life data obtained either from test or from field. This is due in part to the broad range of distribution shapes that are included in the Weibull family. As well as, there are many other distributions which are included in the Weibull distribution’s family either exactly or approximately- for example, the normal, the exponential, the Rayleigh, and sometimes the Poisson and the Binomial. This paper presents a practical approach for those aviation professionals dealing with monitoring and analyzing the aircraft field reliability.

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Venkataraman, Raghu, Peter Seiler, Márk Lukátsi und Bálint Vanek. „Reliability Assessment of Actuator Architectures for Unmanned Aircraft“. Journal of Aircraft 54, Nr. 3 (Mai 2017): 955–66. http://dx.doi.org/10.2514/1.c033832.

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Pokorni, Slavko. „Experiences from reliability testing of aircraft electronic equipment“. Vojnotehnicki glasnik 51, Nr. 4-5 (2003): 413–19. http://dx.doi.org/10.5937/vojtehg0305413p.

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Dinesh Kumar, U. „New trends in aircraft reliability and maintenance measures“. Journal of Quality in Maintenance Engineering 5, Nr. 4 (Dezember 1999): 287–95. http://dx.doi.org/10.1108/13552519910298046.

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Yu, Xiongqing, und Xiaoping Du. „Reliability-based multidisciplinary optimization for aircraft wing design“. Structure and Infrastructure Engineering 2, Nr. 3-4 (September 2006): 277–89. http://dx.doi.org/10.1080/15732470600590333.

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Ming, Wang Ji, Huang Min, Yi Jun und Liu Xue Jun. „The Study of Process Reliability of Aircraft Engine“. Procedia Engineering 99 (2015): 835–39. http://dx.doi.org/10.1016/j.proeng.2014.12.609.

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IKEYAMA, Takashi, und Tatsuhiko HAYASE. „High Reliability NC Machining System for Aircraft Parts“. Journal of the Society of Mechanical Engineers 88, Nr. 795 (1985): 205–9. http://dx.doi.org/10.1299/jsmemag.88.795_205.

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Cannell, W. P. „Height-keeping reliability of aircraft at high altitude“. Quality and Reliability Engineering International 3, Nr. 4 (Oktober 1987): 273–80. http://dx.doi.org/10.1002/qre.4680030410.

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Ponomarev, Artyom I., und Mikhail Y. Sorokin. „INTEGRATION OF THE MEASURED ALTITUDE-SPEED PERFORMANCES IN THE SYSTEM“. Автоматизация процессов управления 2, Nr. 64 (2021): 18–22. http://dx.doi.org/10.35752/1991-2927-2021-2-64-18-22.

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The air data system used by modern aircrafts is a soft hardware designed to measure, compute, and display the altitude-speed performances as well as other parameters such as air temperature, angles of attack and slip; and to provide to aircrew and consumers (various on-board systems) with this information. The speed and altitude are one of the most important flight parameters of an aircraft. The operating principle of modern onboard equipment for measuring the aircraft movement parameters while in flight is based on an aerometric method. This article deals with a method for increasing the accuracy and the reliability of aerodynamic angle-of-attack measurements.

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Bai, Wen Hua, Hong Fu Zuo, Jing Cai und De Feng Lv. „Study on Affecting Factors of the Wear Reliability Based on PHM to Aircraft Airfoil’s Slide Rail“. Advanced Materials Research 452-453 (Januar 2012): 1389–97. http://dx.doi.org/10.4028/www.scientific.net/amr.452-453.1389.

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The slide rail of the airfoil is the key structural component of the aircraft, and its wear reliability has important impact to the aircraft security. The traditional method to the slide rail wear reliability analysis is based on time parameter to establish the reliability function. In fact, the actual operating and environmental parameters in the slide rails have an important impact on its reliability. The proportional hazards model (PHM) method is proposed to study the affecting factors of the slide rail’s wear reliability; the method of principal component is used to make a quantitative description to those affecting factors. and the slide rail’s reliability model of its failure function and life distribution function are obtained under many factors affecting. Finally, a study is made to the wear reliability of some regional jet’s slide rail with the PHM method; the wear reliability model is got under the contact stress, hardness and roughness three affecting factors which meet the fact. So the more accurate wear reliability models can be got by the PHM methods, and that has a practical significance to improve the overall reliability of the aircraft.

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Grishin, Vyacheslav, und Trong Vu. „Research methods to improve reliability of passive redundant control subsystems of aircraft with due consideration of tolerances“. Vestnik of Astrakhan State Technical University. Series: Management, computer science and informatics 2020, Nr. 1 (27.01.2020): 18–28. http://dx.doi.org/10.24143/2072-9502-2020-1-18-28.

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The paper studies the reliability of passively redundant subsystems of aircraft, taking into account tolerances for a decrease in their output parameters in case of sudden component failures. The influence of the reliability values of elements, tolerances of two levels and the redundancy ratio on the reliability of passively redundant subsystems as a whole have been investigated; the examples of such subsystems have been given. There have been presented the results of analysis of the aircraft subsystems features with allowance for tolerances. First of all, these include the availability of technical specifications and realized tolerances determined by the reservation structure; implementing each tolerance with different values of the multiplicities of redundancy; using the main tolerance grid by multiple backup methods; presence of critical probabilities narrowing the reliability range of the elements, where this type of reservation is beneficial from the range 0–1 to the range of the supercritical area (pkr–1). The influence of the element reliability values, tolerances of two levels and the redundancy ratio on the failure-free operation of passively redundant subsystems in general and in supercritical areas has been investigated. It is shown that the minimum redundancy multiplicities in the interests of increasing the reliability of the considered subsystems of aircraft are advantageous to use only with large tolerances and low probabilities of failure-free operation of their elements. Under close tolerances and any reliability values of elements, as well as with large tolerances (more than 25%), high reliability values of this class of aircraft subsystems can be achieved only with large redundancy multiplicities. It has been inferred that there are extreme reliability differences of a passively redundant subsystem and its element, which allows to set the task of developing highly reliable passively redundant subsystems of aircraft taking into account tolerances from relatively unreliable elements.

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McAndrew, Ian R., Elena Navarro, Orin Godsey und Brig Gen Usaf. „Drogue System Reliability Analysis Using Weibull Analysis“. Applied Mechanics and Materials 798 (Oktober 2015): 622–26. http://dx.doi.org/10.4028/www.scientific.net/amm.798.622.

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Refueling aircraft in-flight is a complex procedure at any time and has its concerns that have not fully been addressed, these are compounded if we consider remote piloting. Long term the need will exist to refuel unmanned vehicles if they are to carry out extensive applications; these complexities of in-flight refueling increases due to time delays and visual challenges between the actual remote aircraft and operators. This paper addresses the reliability of a drogue used in refueling and what can be learnt for future designs and usage. In particular what we can interpret from remote pilots andin-situpilots.

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