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Aircrafts Reliability and Health Management

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: closed (31 October 2022) | Viewed by 24389

Special Issue Editors


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Guest Editor
Department of Aeronautics and Astronautics, Fudan University, Shanghai 200433, China
Interests: aircraft design and optimization; model updating; probabilistic modeling; structural health monitoring; structural reliability
Special Issues, Collections and Topics in MDPI journals

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Guest Editor
School of Aeronautical Science and Engineering, Beihang University, Beijing 100191, China
Interests: health monitoring; evaluation models and approaches for aircrafts and aero-engine; detection, modeling, and prediction methods of the crack; failure/fault; fatigue and lifetime of systems and components
Special Issues, Collections and Topics in MDPI journals

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Guest Editor
Department of Civil Engineering, University of Zabol, Zabol, Iran
Interests: structural reliability analysis; reliability-based design optimization; data driven-based modelling approaches and artificial intelligent
Special Issues, Collections and Topics in MDPI journals

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Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi'an, China
Interests: aircrafts maintenance; reliability; safety and airworthiness
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

There have been rapid advancements in aircraft technology, such as in supersonic aircraft, civil aircrafts, and advanced fighter jets. The performance and reliability requirements of such aircrafts are high, requiring an increased focus on the reliability evaluation and health management of systems. The reliability analyses and health evaluations of aircraft systems are thus complex and inherently multidisciplinary processes, involving several disciplines ranging from aerodynamics, propulsion, structures, electric/hydraulic systems, and guidance to navigation and control, each including different groups of highly experienced experts and advanced high-fidelity simulation models. Therefore, it is imperative to develop new and efficient approaches to enable performing suitable health monitoring and reliability design analyses of advanced aircrafts. When it comes to these approaches and techniques, a large range of mathematical algorithms blossom to face up to the challenges induced by aerospace system design and simulation.

We plan to launch this Special Issue in your journal. This Special Issue will focus on the current state-of-the-art, latest advances, and future trends of aircrafts reliability and health management. The key objective is to improve the performance, reliability, safety, airworthiness, and maintainability of aircrafts and aero-engines, by overcoming relevant key technical and scientific issues. The aircraft structures include fuselage cover, wing structure, undercarriage, aero-engine structures or components (i.e., aero-engine fan, compressor, combustor, turbine, blade, casings, and other components), and other related components in an aircraft system. The topics of this Special Issue might include, but are not limited to, structural or system optimization, reliability evaluation analysis, fatigue analysis and design, lifetime analysis (or prediction) and design, faults monitoring and diagnosis, operation and maintenance, seaworthiness, safety evaluation, and health management, etc. This Special Issue welcomes theoretical, analytical, and experimental investigations on aircraft structures and systems. These contributions will advance the body of knowledge and its applications for structural/system health monitoring, optimization and reliability design with respect to the structural dynamics, nonlinear vibrations, time series modeling techniques, strategies of aerospace systems, mathematical modeling methods, computer simulation technologies, reliability-based design optimization techniques, multidisciplinary optimization approaches, and other related algorithms and new applications in aircraft reliability and health management.

Potential topics include, but are not limited to:

  • Health monitoring technologies for aircraft flight condition;
  • Evaluation models and approaches of aero-engine operation status;
  • Detection, modeling and prediction methods of the crack, failure/fault, fatigue and lifetime of systems and components;
  • Optimization design methods for assembled structures (or multi-component systems), and a single structure (component) of aircraft;
  • The optimization strategy and algorithm, multidisciplinary simulation approach and surrogate modeling technique, in optimization and reliability design of structures and systems;
  • Advanced probabilistic analysis and design methods for aircraft structures including parameter influential analysis, sensitivity analysis, and reliability-based design optimization methods;
  • The applications of emerging technologies and algorithms in aircraft system analysis, such as big data analytics, cloud computing, intelligent algorithm, etc. In particular, we look into their applications in the analysis, simulation, and modeling for structural optimization and reliability design;
  • Decision support and simulation-based optimization and reliability design which contribute to improve the performance and reliability of aircraft and structures;
  • Maintenance/reliability/safety/airworthiness modeling and optimization based on new theory, method and technology

Prof. Dr. Cheng-Wei Fei
Dr. Zhixin Zhan
Prof. Dr. Behrooz Keshtegar
Prof. Dr. Yunwen Feng
Guest Editors

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Keywords

  • aircraft system
  • performance evaluation
  • reliability design
  • modeling and simulation
  • health management
  • operation and maintenance

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Published Papers (13 papers)

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Research

14 pages, 2331 KiB  
Article
Research and Evaluation Method for Echelon Usage of Double-Life Equipment Considering Calendar Life
by Pisheng Qin, Xiaofeng Zhang, Qinglin Miao and Nachuan Liu
Appl. Sci. 2023, 13(3), 1655; https://doi.org/10.3390/app13031655 - 28 Jan 2023
Cited by 1 | Viewed by 1132
Abstract
Echelon usage is an important usage and control method for double-life equipment considering calendar life, which can improve the utilization rate of equipment life and give full play to the economic benefits of the equipment. However, the life indicator considered by the most [...] Read more.
Echelon usage is an important usage and control method for double-life equipment considering calendar life, which can improve the utilization rate of equipment life and give full play to the economic benefits of the equipment. However, the life indicator considered by the most common echelon usage method is single, and most methods evaluate the echelon usage through the echelon uniformity of working life. The conclusions obtained are limited for the usage and control of double-life equipment, so it is necessary to study the life evaluation method considering calendar life. In this paper, by analyzing the life consumption law of double-life equipment, the recursive method is used to calculate the controllable life range in the process of echelon usage. The evaluation method of working life distribution considering calendar life is proposed. The equipment life reserve is evaluated according to the unit task quantity of the equipment. The results show that the new method can quickly analyze the equipment beyond the usage and control range, evaluate the distribution of working life more accurately, reflect the shortage of equipment reserve life, and has guiding significance for the usage and control of equipment. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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16 pages, 5562 KiB  
Article
Modeling and I-NSGA-III-VLC Solution of Aircraft Equipment Rotation and Echelon Usage under Uncertainty
by Qinglin Miao, Xiaofeng Zhang, Pisheng Qin and Xianguang Liu
Appl. Sci. 2022, 12(20), 10482; https://doi.org/10.3390/app122010482 - 17 Oct 2022
Cited by 1 | Viewed by 1320
Abstract
Optimizing the aircraft equipment usage scheme of different units according to their task intensity has great significance in improving aircraft reliability and health management. This paper studied the modeling and solving methods of the rotation and echelon usage problems of aircraft equipment measured [...] Read more.
Optimizing the aircraft equipment usage scheme of different units according to their task intensity has great significance in improving aircraft reliability and health management. This paper studied the modeling and solving methods of the rotation and echelon usage problems of aircraft equipment measured by dual-life indexes, one of which cannot be controlled. In order to maximize the waste rate of the rotation quantity, echelon uniformity index, life matching index and life utilization index, a decision-making model of the equipment rotation and echelon usage problem under uncertainty was constructed, and an improved NSGA-III with a variable length chromosome was proposed. An improved segmented coding method and operators were proposed, and the repeated individual control mechanism was used to improve the population diversity. When the scale of the problem was large, this method could search a wider range in a short time and obtain more feasible solutions, which verified the feasibility of this method. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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22 pages, 8217 KiB  
Article
The Characteristics and Mechanisms of High-Intensity Sound in a High-Speed Multistage Compressor
by Fengtong Zhao, Bo Cui, Haitao Liu, Fei Wu and Yundong Sha
Appl. Sci. 2022, 12(14), 6865; https://doi.org/10.3390/app12146865 - 7 Jul 2022
Viewed by 1398
Abstract
An experiment with a multistage high-speed compressor is conducted to investigate the high noise with abnormal blade vibration. Different points are selected to monitor the noise in the compressor and the amplitude of blade vibration. The evolution rhythm of sound frequency and sound [...] Read more.
An experiment with a multistage high-speed compressor is conducted to investigate the high noise with abnormal blade vibration. Different points are selected to monitor the noise in the compressor and the amplitude of blade vibration. The evolution rhythm of sound frequency and sound pressure level against speed is captured. The relation between the vibration and the noise is obtained. A research method based on an acoustic analogy is developed to investigate the characteristics and mechanisms of high-intensity sound in a rectangular cavity pipeline. The calculated distribution of the first four-order acoustic mode inside the rectangular cavity pipe is consistent with the results in the literature, and the maximum calculation error of the acoustic mode frequency value is 2.7%, which certifies the effectiveness of the method. A simplified compressor model is established to study the vortex system and the sound field characteristics of this method when high-intensity sound occurs. The results present the motion law of shedding vortices with high-intensity sound, and the calculation error of the frequency corresponding to the high-intensity sound is 3.6%. The “frequency-locked phase-locked” characteristics (i.e., character frequency) keep constant at a range of velocities, showing similarity with the phenomenon obtained in experiment above, and beta mode forms of Parker are captured. The study in the present paper makes a contribution for the cognition of mechanisms with high-intensity sound in aeroengine compressors. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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22 pages, 5868 KiB  
Article
Stress Optimization of Vent Holes with Different Shapes Using Efficient Switching Delayed PSO Algorithm
by Cheng Yan, Wenkang Hao, Yiqi Yin, Nianyin Zeng, Han Du and Dandan Song
Appl. Sci. 2022, 12(11), 5395; https://doi.org/10.3390/app12115395 - 26 May 2022
Cited by 3 | Viewed by 2149
Abstract
An effective integrated design optimization method is developed to reduce the maximum von Mises stress around vent holes of a high-pressure turbine sealing disk. It mainly includes four different shape designs (circular, elliptical, race-track, and four-arc) for holes, an updated self-developed modelling and [...] Read more.
An effective integrated design optimization method is developed to reduce the maximum von Mises stress around vent holes of a high-pressure turbine sealing disk. It mainly includes four different shape designs (circular, elliptical, race-track, and four-arc) for holes, an updated self-developed modelling and meshing tool, an APDL-based strength analysis, and a self-proposed efficient switching delayed particle swarm optimization (SDPSO) algorithm. The main idea of SDPSO is: (1) by evaluating an evolutionary factor and utilizing a probability transition matrix, a non-homogeneous Markov chain is determined and auto-updated in each generation; (2) the evolutionary factor and the Markov chain are used to adaptively select the inertia weight, acceleration coefficients, and delayed information to adjust the particle’s velocity. The performance of SDPSO is evaluated through two benchmark optimization problems with constraints. The results show that SDPSO is superior to two well-known PSO algorithms in optimization capability, numerical robustness, and convergence speed. Furthermore, SDPSO is used for the stress optimization of vent holes with four different shapes. The results show that: (1) SDPSO is suitable and valuable for practical engineering optimization problems with constraints; (2) the developed integrated design optimization method is effective and advanced for reducing the maximum von Mises stress around the vent holes; and (3) the four-arc hole has more tremendous advantages in reducing the maximum von Mises stress, followed by the elliptical hole, the race-track hole, and the circular hole. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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14 pages, 2106 KiB  
Article
The Optimization of Civil Aircraft Product Option Selection Considering the Economy Response with an Improved Non-Dominated Sorting Genetic Algorithm
by Yunwen Feng, Zhicen Song and Cheng Lu
Appl. Sci. 2022, 12(11), 5294; https://doi.org/10.3390/app12115294 - 24 May 2022
Cited by 4 | Viewed by 1576
Abstract
To serve customized option selection for civil aircraft, a mathematical product option selection optimization model combined with an Improved Non-dominated Sorting Genetic Algorithm for decreasing aircraft fleet maintenance cost was investigated. For airlines, considering the economy and reliability in customized option selection is [...] Read more.
To serve customized option selection for civil aircraft, a mathematical product option selection optimization model combined with an Improved Non-dominated Sorting Genetic Algorithm for decreasing aircraft fleet maintenance cost was investigated. For airlines, considering the economy and reliability in customized option selection is the most intuitive way to improve aircraft performance to generate the optimal formation configuration. Product option selection usually takes certain indicators as constraints (reliability and economy) to meet and maximize performance through equipment selection (the selected parameters include mean time between failures, price, etc.). To describe the customization needs of airlines by a mathematical model and find the optimal decision through an algorithm, a multi-objective, mathematical product option selection optimization model response with reliability parameters as a decision variable, maintainability as a link, and aircraft fleet maintenance and availability as an objective function is established to serve aircraft option selection in this paper. Next, the multi-objective genetic algorithm is used to solve the model, and the convergence, distribution and fitting accuracy of the objective functions are analyzed. Eventually, the landing gear system is used to verify the effectiveness of the model and method. After optimization, the aircraft fleet maintenance cost is reduced by 20.71%, and the availability is increased by 2.576%. Through the mathematical optimization model, the product configuration is provided for the development of the customization option selection project. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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21 pages, 5552 KiB  
Article
Investigation on Characterization of Typical Characteristic in Compressor Based on Flat Plate Model
by Fengtong Zhao, Bo Cui, Fei Wu, Shan Jiang, Mingsui Yang and Yuying Chen
Appl. Sci. 2022, 12(10), 4956; https://doi.org/10.3390/app12104956 - 13 May 2022
Viewed by 1560
Abstract
The acoustic resonance of aero-engine compressors is very harmful, which can lead to the failure of components such as blades. The mechanism of acoustic resonance is very complicated. To solve this problem, characteristics of the noise signal under the abnormal vibration state of [...] Read more.
The acoustic resonance of aero-engine compressors is very harmful, which can lead to the failure of components such as blades. The mechanism of acoustic resonance is very complicated. To solve this problem, characteristics of the noise signal under the abnormal vibration state of the rotor blade are analyzed through the noise measurement in the compressor in the paper. The frequency spectrum characteristics, sound pressure level, and phase relationship of the noise signal corresponding to the abnormal vibration of the rotor blade are captured, and the feature of “frequency locked” which is consistent with the acoustic resonance in the compressor is obtained. Numerical simulation is a better way to study the mechanism of acoustic resonance. Therefore, based on the Parker model, a research method of acoustic resonance characteristics and mechanism based on acoustic analogy is proposed from the solution of the sound-induced in the pipe cavity. The vortex system and sound field characteristics when the acoustic resonance occurs are calculated. The results show that the distribution characteristics of the shedding vortex can be recognized, which are consistent with the experimental results of Welsh when the acoustic resonance occurs. The error of the acoustic resonance frequency from numerical simulation results to experimental is 3.6%. The characteristic of “frequency locked” and Parker β mode of the acoustic resonance is captured. The acoustic analogy method is suitable for the characterization of the acoustic resonance performance and mechanism in the pipeline and in the aeroengine compressor. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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21 pages, 4537 KiB  
Article
Synthetical Modal Parameters Identification Method of Damped Oscillation Signals in Power System
by Huan Li, Siqi Bu, Jiong-Ran Wen and Cheng-Wei Fei
Appl. Sci. 2022, 12(9), 4668; https://doi.org/10.3390/app12094668 - 6 May 2022
Cited by 16 | Viewed by 1908
Abstract
It is vital to improve the stability of the power system by accurately identifying the modal parameters of damped low-frequency oscillations (DLFO) and controlling the oscillation in time. A new method based on empirical mode decomposition (EMD), stochastic subspace identification (SSI), and Prony [...] Read more.
It is vital to improve the stability of the power system by accurately identifying the modal parameters of damped low-frequency oscillations (DLFO) and controlling the oscillation in time. A new method based on empirical mode decomposition (EMD), stochastic subspace identification (SSI), and Prony algorithms, called synthetical modal parameters identification (SMPI) method, is developed by efficiently matching the modal parameters of DLFO which are acquired from the SSI and Prony algorithm. In this approach, EMD is used for denoising the raw oscillation signals thereby enhancing the noise resistance, and then using the SSI and Prony algorithms to identify the precise modal parameters assisted by parameter matching. It is demonstrated that the proposed SMPI method holds great accuracy in identifying full modal parameters including natural frequencies, damping ratios, amplitudes, and phase angles with simulated signals with known modal parameters and real-time signals from some power system case studies. The strategy of SMPI has effectively overcome the weakness of a single approach, and the identification results are promising to heighten the stabilization of power systems. Besides, SMPI shows the potential to troubleshoot in different fields, such as construction, aeronautics, and marine, for its satisfactory robustness and generalization ability. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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14 pages, 3605 KiB  
Article
Reliability Prediction Method for Low-Cycle Fatigue Life of Compressor Disks Based on the Fusion of Simulation and Zero-Failure Data
by Ruoqi Chen, Gaoxiang Chen, Xi Liu, Xing Ai and Haiyan Zhu
Appl. Sci. 2022, 12(9), 4318; https://doi.org/10.3390/app12094318 - 25 Apr 2022
Cited by 6 | Viewed by 1611
Abstract
Targeting reliability assessment problems with a small sample size and large amount of zero-failure data which appear in the life assessment tests of aero-engine compressor disks, a reliability assessment method and simulation test method were developed by fusing numerical simulation and zero-failure data [...] Read more.
Targeting reliability assessment problems with a small sample size and large amount of zero-failure data which appear in the life assessment tests of aero-engine compressor disks, a reliability assessment method and simulation test method were developed by fusing numerical simulation and zero-failure data based on the life reliability assessment method for zero-failure data. The developed method was verified by numerical examples, and further applied in the reliability analysis of compressor disks by combining the test and simulation results. The results indicated that fusing the test data with the simulation data increased the amount of information, improved the life prediction accuracy, and increased the lower confidence limit of the reliable life by 6.02% compared with the case where the test data alone were used. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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21 pages, 6493 KiB  
Article
Dynamic Finite Element Model Updating Based on Correlated Mode Auto-Pairing and Adaptive Evolution Screening
by Huajin Shao, Yanfei Zuo and Zhinong Jiang
Appl. Sci. 2022, 12(6), 3175; https://doi.org/10.3390/app12063175 - 20 Mar 2022
Cited by 2 | Viewed by 1927
Abstract
A method for dynamic finite element (FE) model updating based on correlated mode auto-pairing and adaptive evolution screening (CMPES) is proposed to overcome difficulties in pairing inaccurate analytical modal data and incomplete experimental modal data. In each generation, the correlated mode pairings (CMPs) [...] Read more.
A method for dynamic finite element (FE) model updating based on correlated mode auto-pairing and adaptive evolution screening (CMPES) is proposed to overcome difficulties in pairing inaccurate analytical modal data and incomplete experimental modal data. In each generation, the correlated mode pairings (CMPs) are determined by modal assurance criterion (MAC) values and the symbiotic natural frequency errors, according to an auto-pairing strategy. The objective function values constructed by correlated and penalized subitems are calculated to screen the better individuals. Then, both the updating parameters and the CMPs can be adjusted adaptively to simultaneously approach the ideal results during the iteration of population evolution screening. Three examples (a thin plate with small holes, an F-shaped structure, and an intermediate case with multi-layer thin-walled complex structure) were presented to validate the accuracy, effectiveness, and engineering application potential of the proposed method. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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19 pages, 2380 KiB  
Article
Reliability Uncertainty Analysis Method for Aircraft Electrical Power System Design Based on Variance Decomposition
by Yao Wang, Yuanfeng Cai, Xiaomin Hu, Xinqin Gao, Shujuan Li and Yan Li
Appl. Sci. 2022, 12(6), 2857; https://doi.org/10.3390/app12062857 - 10 Mar 2022
Cited by 2 | Viewed by 2453
Abstract
As a safety critical system, affected by cognitive uncertainty and flight environment variability, aircraft electrical power system proves highly uncertain in its failure occurrence and consequences. However, there are few studies on how to reduce the uncertainty in the system design stage, which [...] Read more.
As a safety critical system, affected by cognitive uncertainty and flight environment variability, aircraft electrical power system proves highly uncertain in its failure occurrence and consequences. However, there are few studies on how to reduce the uncertainty in the system design stage, which is of great significance for shortening the development cycle and ensuring flight safety during the operation phrase. For this reason, based on the variance decomposition theory, this paper proposes an importance measure index of the influence of component failure rate uncertainty on the uncertainty of power supply reliability (system reliability). Furthermore, an algorithm to calculate the measure index is proposed by combining with the minimum path set and Monte Carlo simulation method. Finally, the proposed method is applied to a typical series-parallel system and an aircraft electrical power system, and a criteria named as “quantity and degree optimization criteria” is drawn from the case study. Results demonstrate that the proposed method indeed realizes the measurement of the contribution degree of component failure rate uncertainty to system reliability uncertainty, and combined with the criteria, proper solutions can be quickly determined to reduce system reliability uncertainty, which can be a theoretical guidance for aircraft electrical power system reliability design. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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22 pages, 688 KiB  
Article
On-the-Fly Repairing of Atomicity Violations in ARINC 653 Software
by Eu-teum Choi, Tae-hyung Kim, Yong-Kee Jun, Seongjin Lee and Mingyun Han
Appl. Sci. 2022, 12(4), 2014; https://doi.org/10.3390/app12042014 - 15 Feb 2022
Cited by 3 | Viewed by 1935
Abstract
Airborne health management systems prevent functional failure caused by errors or faults in airborne software. The on-the-fly repairing of atomicity violations in ARINC 653 concurrent software is critical for guaranteeing the correctness of software execution. This paper introduces RAV (Repairing Atomicity Violation), which [...] Read more.
Airborne health management systems prevent functional failure caused by errors or faults in airborne software. The on-the-fly repairing of atomicity violations in ARINC 653 concurrent software is critical for guaranteeing the correctness of software execution. This paper introduces RAV (Repairing Atomicity Violation), which efficiently treats atomicity violations. RAV diagnoses an error on the fly by utilizing the training results of software and treats to control access to the shared variable of the thread where the error has occurred. The evaluation of RAV measured the time overhead by applying methods found in previous works and RAV to five synthesis programs containing an atomicity violation. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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15 pages, 10928 KiB  
Article
Study on Low-Frequency Abnormal Signal and Structural Characteristics of 2015 Azuoqi Ms5.8 Earthquake
by Shasha Liang and Haibin Li
Appl. Sci. 2022, 12(1), 259; https://doi.org/10.3390/app12010259 - 28 Dec 2021
Viewed by 1269
Abstract
In this article, the phenomenon of low-frequency abnormal signals before earthquakes, which reflects the three elements of earthquakes and the beneath structure change information, is discussed. Based on the data recorded at the Shizuishan (SZS), Wuhai (WUH) and Dongshenmiao seismic stations around the [...] Read more.
In this article, the phenomenon of low-frequency abnormal signals before earthquakes, which reflects the three elements of earthquakes and the beneath structure change information, is discussed. Based on the data recorded at the Shizuishan (SZS), Wuhai (WUH) and Dongshenmiao seismic stations around the epicenter of the Ms5.8 earthquake in Azuoqi, Inner Mongolia, in 2015, the low-frequency abnormal signal from the seismic waves before this earthquake is extracted. At the same time, the autocorrelation method is used to extract the reflected waves of the main interface from teleseismic events recorded by the seismic array in the epicenter area, and then the change information from the beneath structure is obtained. It is explained in time and space that the low-frequency abnormal signal before the main earthquake, extracted from the continuous waveform, is directly related to the change in the underground structure near the epicenter, and it can be determined that the wave propagation direction f the crustal stress before the earthquake is from south to north, and it continues to accumulate near the epicenter until the main earthquake occurs. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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16 pages, 1599 KiB  
Article
Fiducial Lower Confidence Limit of Reliability for a Power Distribution System
by Xia Cai, Liang Yan, Yan Li and Yutong Wu
Appl. Sci. 2021, 11(23), 11317; https://doi.org/10.3390/app112311317 - 29 Nov 2021
Cited by 2 | Viewed by 1602
Abstract
Reliability performance, especially the lower confidence limit of reliability, plays an important role in system risk and safety assessment. A good estimator of the lower confidence limit of system reliability can help engineers to make the right decisions. Based on the lifetime of [...] Read more.
Reliability performance, especially the lower confidence limit of reliability, plays an important role in system risk and safety assessment. A good estimator of the lower confidence limit of system reliability can help engineers to make the right decisions. Based on the lifetime of the key component in a typical satellite intelligent power distribution system, the generalized fiducial method is adopted to estimate the lower confidence limit of the system reliability in this paper. First, the generalized pivotal quantity and the lower confidence limit of reliability for the key component are derived for the lifetimes of the exponential-type and Weibull-type components. Simulations show that the sample median is more appropriate than the sample mean when the lower confidence limit of reliability is estimated. Moreover, the lower confidence limit of reliability is obtained for the typical satellite intelligent power distribution system through the pseudo-lifetime data of the metallic oxide semiconductor field effect transistor. The lower confidence limit of reliability for this power distribution system at 15 years is 0.998, which meets the factory’s reliability requirement. Finally, through the comparison, a hot standby subsystem can be substituted with a cold standby subsystem to increase the lower confidence limit of the system reliability. Full article
(This article belongs to the Special Issue Aircrafts Reliability and Health Management)
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