This study experimentally investigates the hydrodynamic characteristics,geometric configurations,fluttering motions of the codend,and the instantaneous flow fields inside and around the codend,with and without a liner...This study experimentally investigates the hydrodynamic characteristics,geometric configurations,fluttering motions of the codend,and the instantaneous flow fields inside and around the codend,with and without a liner,under varying catch sizes and inflow velocities.A proper orthogonal decomposition method is employed to extract phase-averaged mean properties of unsteady turbulent flows from flow measurement data obtained using an electromagnetic current velocity meter inside and around the codend.The results reveal that as catch size increases,the drag force,codend motion,Reynolds number,and codend volume increase while the drag coefficient decreases.Owing to the codend shape and pronounced motion,a complex fluid–structure interaction occurs,demonstrating a strong correlation between drag force and codend volume.The oscillation amplitudes of the hydrodynamic forces and codend motions increase with increasing catch size,and their oscillations mainly involve low-frequency activity.A significant reduction in the flow field occurs inside and around the unlined codend without a catch.The flow field is 5.81%,14.39%,and 27.01%lower than the unlined codend with a catch,the codend with a liner but without a catch,and the codend with both a liner and a catch,respectively.Fourier analysis reveals that the codend motions and hydrodynamic forces are mainly characterized by low-frequency activity and are synchronized with the unsteady turbulent flow street.Furthermore,the proper orthogonal decomposition results reveal the development of unsteady turbulent flow inside and around the codend,driven by flow passage blockage caused by the presence of the liner,intense codend motions,and the catch.Understanding the hydrodynamic characteristics and flow instabilities inside and around the codend,particularly those associated with its fluttering motions,is crucial for optimizing trawl design and improving trawl selectivity.展开更多
The dynamic coupling between the fluttering motions and hydrodynamic characteristics of codend is essential in understanding the trawl selectivity through fish response and the drag force acting on the whole trawl.Thi...The dynamic coupling between the fluttering motions and hydrodynamic characteristics of codend is essential in understanding the trawl selectivity through fish response and the drag force acting on the whole trawl.This study investigated the effect of towing speed,warp length,warp tension,and catch size on the fluttering motions of Antarctic krill trawl codend during net shooting,towing,and hauling by using sea trial data.The time-periodicity of codend oscillation was analyzed by the Morlet wavelet transform method.Results indicated that the period of codend oscillation was between 50 s and 90 s and showed an increasing trend with the warp tension but a decreased value at the towing stage.The coefficient amplitude of codend oscillation was between 0 and 4 at the net shooting and hauling stages,and between 0.2 and 0.6 at the towing stage.The amplitude of codend oscillation increased with the warp tension,towing speed,and catch size,but decreased with the increase of the warp length.In addition,the period of codend oscillation increased with the towing speed at the net shooting and hauling stages,but decreased at the towing stage.These results from codend fluttering motions can improve the understanding of fish behavior and gear shape that modify the hydrodynamic force on the codend instantaneously.展开更多
This work describes investigations performed on the interaction of uniform current and freely rotating plate about a fixed vertical axis. Fluttering and autorotation are two different motions that may occur during the...This work describes investigations performed on the interaction of uniform current and freely rotating plate about a fixed vertical axis. Fluttering and autorotation are two different motions that may occur during the flow induced rotation. The dimensional analysis proves that the motion in flow induced rotation motion is governed essentially by the dimensionless moment of inertia and Reynolds number. Certain combinations define the stability boundaries between fluttering and autorotation. Fluttering is oscillation of body about a vertical axis and the autorotation is a name given to the case when the body turns continuously about the vertical axis First, the loads and moment coefficients are calculated by experiments and streamline theory for different angles of attack for a fixed fiat plate. Then for dynamic case, a bifurcation diagram is presented based on experiments to classify different motion states of flow induced rotation. Finally, a dynamical model is proposed for stability analysis of flow induced rotation of a flat plate.展开更多
Atrial fibrillation(AF)/atrial flutter(AFL)is the most common sustained cardiac arrhythmia.The known risk factors for developing AF/AFL include age,structural heart disease,hypertension,diabetes mellitus,or hyperthyro...Atrial fibrillation(AF)/atrial flutter(AFL)is the most common sustained cardiac arrhythmia.The known risk factors for developing AF/AFL include age,structural heart disease,hypertension,diabetes mellitus,or hyperthyroidism.This study aims to attribute the trends in AF/AFL-related mortalities over the past two decades 1999-2020 concerning race and sex and disparity among them.To the best of our knowledge,this is the first study that estimates the trends and mortality due to AF/AFL from 1999-2020 in older adults in the United States.In this 21-year analysis of mortality data,we found a constant increase in mortality rates due to AF/AFL in older adults.From 1999 to 2020,the overall mortality in older adults aged 65 and above,regardless of sex and race,is found to be almost doubled i.e.about a 50.2%increase in the number of deaths due to AF/AFL.Furthermore,other confounding risk factors such has obesity,prior myocardial infarction,inflammation,hypertension,birth weight,diabetes mellitus,hyperthyroidism,hormone replacement therapy in menopausal women increases the risk in the occurrence or recurrent occurrence of AF.展开更多
目的:为了提高医疗设备验收的信息化管理水平,设计多端协同医疗设备验收管理系统。方法:多端协同医疗设备验收管理系统采用前后端分离的设计架构,前端采用跨平台框架Flutter和Dart语言开发,后端采用Tornado 6.1框架和Python语言开发,前...目的:为了提高医疗设备验收的信息化管理水平,设计多端协同医疗设备验收管理系统。方法:多端协同医疗设备验收管理系统采用前后端分离的设计架构,前端采用跨平台框架Flutter和Dart语言开发,后端采用Tornado 6.1框架和Python语言开发,前端与后端服务之间的通信遵循RESTful设计原则,通过超文本传输协议(hypertext transfer protocol,HTTP)请求进行交互。整个系统包括用户管理、基础信息管理、验收管理3个功能模块。结果:该系统实现了医疗设备验收过程的信息化管理,支持跨平台管理验收报告及相关附件、医疗器械注册证等内容,提高了验收的工作质量与效率。结论:该系统实现了医疗设备验收的多端协同管理,为医院医疗设备管理的数字化和智能化转型奠定了基础。展开更多
This study introduces a novel approach for coupled aeroelastic analysis of panel subjected to supersonic airflow,utilizing Add-On Acoustic Black Hole(AABH)to mitigate panel flutter.Employing Galerkin's method to d...This study introduces a novel approach for coupled aeroelastic analysis of panel subjected to supersonic airflow,utilizing Add-On Acoustic Black Hole(AABH)to mitigate panel flutter.Employing Galerkin's method to discretize aeroelastic equation of panel and leveraging finite element method to derive a reduced discrete model of AABH,this study effectively couples two substructures via interface displacement.Investigation into the interactive force highlights the modal effective mass,frequency discrepancy between oscillation and AABH mode,and modal damping ratio as critical factors influencing individual AABH mode in flutter suppression.The selection of effective AABH modes,closely linked to these factors,directly influences the accuracy of simulations.The results reveal that AABH notably enhances the panel's critical flutter boundary by14.6%,a significant improvement over the 3.6%increase afforded by equivalent mass.Furthermore,AABH outperforms both the tuned mass damper and nonlinear energy sink in flutter suppression efficacy.By adjusting the AABH's geometrical parameters to increase the accumulative modal effective mass within the pertinent frequency range,or choosing a suitable installation position for AABH,its performance in flutter suppression is further optimized.These findings not only underscore the AABH's potential in enhancing aeroelastic stability but also provide a foundation for its optimal design.展开更多
The integration of wearable technology and remote monitoring (RM) has significantlytransformed the early detection, continuous monitoring, and managementof cardiac arrhythmias. These conditions, characterized by irreg...The integration of wearable technology and remote monitoring (RM) has significantlytransformed the early detection, continuous monitoring, and managementof cardiac arrhythmias. These conditions, characterized by irregular heart rhythms,arise from various etiological factors, including congenital, structural, immunological,metabolic, and infectious diseases, with atrial fibrillation being themost prevalent type. Diagnosing arrhythmias remains challenging due to variableclinical presentations and episodic symptom manifestations, necessitating individualizedmanagement strategies. Recent advances in wearable technology offerscalable, cost-effective solutions for real-time arrhythmia monitoring. These devicesare equipped with sophisticated sensors and data analytics that enable earlydetection and personalized interventions, while empowering patients to activelyengage in their healthcare. Integrating RM systems enhances diagnostic accuracyand facilitates timely medical interventions. Despite their potential, regulatory,legal, privacy, security, and infrastructural challenges hinder the widespreadadoption of wearable technology and RM. Addressing these barriers requirescollaboration among stakeholders and rigorous clinical trials to assess theirefficacy and feasibility. Future research should focus on refining wearable technology,improving user experience, and integrating these innovations into existinghealthcare frameworks. Overcoming these challenges will maximize the potentialof wearable technology and RM, ultimately enhancing the management of cardiacarrhythmias and improving patient outcomes.展开更多
An aileron is a crucial control surface for rolling.Any jitter or shaking caused by the aileron mechatronics could have catastrophic consequences for the aircraft’s stability,maneuverability,safety,and lifespan.This ...An aileron is a crucial control surface for rolling.Any jitter or shaking caused by the aileron mechatronics could have catastrophic consequences for the aircraft’s stability,maneuverability,safety,and lifespan.This paper presents a robust solution in the form of a fast flutter suppression digital control logic of edge computing aileron mechatronics(ECAM).We have effectively eliminated passive and active oscillating response biases by integrating nonlinear functional parameters and an antiphase hysteresis Schmitt trigger.Our findings demonstrate that self-tuning nonlinear parameters can optimize stability,robustness,and accuracy.At the same time,the antiphase hysteresis Schmitt trigger effectively rejects flutters without the need for collaborative navigation and guidance.Our hardware-in-the-loop simulation results confirm that this approach can eliminate aircraft jitter and shaking while ensuring expected stability and maneuverability.In conclusion,this nonlinear aileron mechatronics with a Schmitt positive feedback mechanism is a highly effective solution for distributed flight control and active flutter rejection.展开更多
Flutter and forced response, as two main branches of aeroelasticity, can lead to high-cycle fatigue failure of turbomachinery blades. Efficiently and accurately assessing aeroelastic performance of turbomachinery blad...Flutter and forced response, as two main branches of aeroelasticity, can lead to high-cycle fatigue failure of turbomachinery blades. Efficiently and accurately assessing aeroelastic performance of turbomachinery blades is essential in the routine design. In this work, the Time Collocation Method (TCM) which uses the cubic B-spline to approximate flow variables is first thoroughly studied and then combined with the moving grid technique to analyze aeroelastic flow fields. To showcase its advantage over the Harmonic Balance (HB) method which uses a truncated Fourier series to approximately represent flow variables, a matrix analysis of the one-dimensional advection equation is first performed. The results of stability analysis are verified by two test cases: the Durham linear oscillating turbine cascade and a two-blade-row transonic compressor. The vibration of the blade of the first case is driven by a motor while the excitation force of the second case comes from blade row interaction. The results show that the time collocation method has a faster convergence rate and is more stable than the harmonic balance method, especially for cases with a large maximum grid reduced frequency. More importantly, the time collocation method is capable of accurately predicting aeroelastic performance of turbomachinery blades.展开更多
The implicit partition algorithm used to solve fluid–structure coupling problems has high accuracy,but it requires a long computation time.In this paper,a semi-implicit fluid–structure coupling algorithm based on mo...The implicit partition algorithm used to solve fluid–structure coupling problems has high accuracy,but it requires a long computation time.In this paper,a semi-implicit fluid–structure coupling algorithm based on modal force prediction-correction is proposed to improve the computational efficiency.In the pre-processing stage,the fluid domain is assumed to be a pseudo-elastic solid and merged with the solid domain to form a holistic system,and the normalized modal information of the holistic system is calculated and stored.During the sub-step cycle,the modal superposition method is used to obtain the response of the holistic system with the predicted modal force as the load,so that the deformation of the structure and the updating of the fluid mesh can be achieved simultaneously.After solving the Reynolds-averaged Navier-Stokes equations in the fluid domain,the predicted modal force is corrected and a new sub-step cycle is started until the converged result is obtained.In this method,the computation of the fluid equations and the updating of the dynamic mesh are done implicitly,while the deformation of the structure is done explicitly.Two numerical cases,vortex induced oscillation of an elastic beam and fluid–structure interaction of a final stage blade,are used to verify the efficiency and accuracy of the proposed algorithm.The results show that the proposed method achieves the same accuracy as the implicit method while the computational time is reduced.In the case of the vortex-induced oscillation problem,the computational time can be reduced to 18.6%.In the case of the final stage blade vibration,the computational time can be reduced to 53.8%.展开更多
Quantum flutter is a ubiquitous phenomenon which can be observed from the fast moving impurity injected into a fermionic or bosonic medium of quantum liquid.In this scenario,one usually considers a medium of a fully p...Quantum flutter is a ubiquitous phenomenon which can be observed from the fast moving impurity injected into a fermionic or bosonic medium of quantum liquid.In this scenario,one usually considers a medium of a fully polarized state and injects a spin-flipped impurity as the initial state.When the initial velocity of the impurity is beyond the intrinsic sound velocity of the medium,the impurity momentum dramatically exhibits a long-lived periodic oscillation with the periodicity remaining invariant with respect to the initial velocity.In this paper,we show that such a novel phenomenon can be explained by a linear Luttinger liquid coupled to a deep hole in the Fermi sea.Once the deep hole excitations are involved and the impurity momentum surpasses the Fermi momentum,the propagator thus displays a periodic oscillation after a quick relaxation decay.The oscillation periodicity is solely determined by the energy of the deepest hole excitation.Our result provides deep insights into the dynamical behavior of quantum impurities immersed into one-dimensional quantum liquids.展开更多
Stall flutter poses great challenges to flight safety.To alleviate this problem,a steady blowing control considering the perturbation and wake-induced vibration at a large angle of attack is developed in this paper,wh...Stall flutter poses great challenges to flight safety.To alleviate this problem,a steady blowing control considering the perturbation and wake-induced vibration at a large angle of attack is developed in this paper,where two blowings are configured on upper and lower tail surfaces to suppress the stall flutter.The stall flutter with one-degree-of-freedom is first evaluated by numerical simulation.The equation of motion for stall flutter is solved by the Newmark-β method.Then,the stall flutter responses for five blowing speeds,i.e.,0,4,12,20,and 28 m/s under the airspeed range of 3–9 m/s,are studied in detail.The stall flutter suppression mechanism can be summarized as follows:a large blowing speed can inject energy into the boundary layer and enhance the high-pressure zone,which delays the flow separation on the suction surface.In this way,the formation of the leading-edge separation vortex is suppressed.Thus,the dynamic stall vortex is weakened and accelerates shedding.In addition,the driving moment is reduced,which leads to a decrement in the stall flutter amplitude.When the blowing speed is 28 m/s(stall flutter amplitude=0.1357 rad),compared with uncontrolled case(stall flutter amplitude=0.6002 rad),the amplitude can decrease by 77.39%,which demonstrates the effectiveness of the proposed steady blowing based active control strategy.展开更多
With the gradual increase in the size and flexibility of composite blades in large wind turbines,problems related toaeroelastic instability and blade vibration are becoming increasingly more important.Given their impa...With the gradual increase in the size and flexibility of composite blades in large wind turbines,problems related toaeroelastic instability and blade vibration are becoming increasingly more important.Given their impact on thelifespan of wind turbines,these subjects have become important topics in turbine blade design.In this article,firstaspects related to the aeroelastic(structural and aerodynamic)modeling of large wind turbine blades are summarized.Then,two main methods for blade vibration control are outlined(passive control and active control),including the case of composite blades.Some improvement schemes are proposed accordingly,with a specialfocus on the industry’s outstanding suppression scheme for stall-induced nonlinear flutter and a new high-frequencymicro-vibration control scheme.Finally,future research directions are indicated based on existingresearch.展开更多
Aeroelastic control is a critical technique for high-aspect-ratio flexible wings.A novel aeroelastic control method is introduced,utilizing the internal Moving Mass Control(MMC)technique,which demonstrates the potenti...Aeroelastic control is a critical technique for high-aspect-ratio flexible wings.A novel aeroelastic control method is introduced,utilizing the internal Moving Mass Control(MMC)technique,which demonstrates the potential to fulfill hybrid control demands without incurring a drag penalty.Dynamic equations for a flexible wing equipped with a spanwise moving mass under unsteady aerodynamic loading are derived using mass position as the input variable.Controloriented analyses indicate that intrinsic structural frequencies,flutter characteristics,and gust response can be actively modified by varying the spanwise and chordwise positions of the mass element.Among these,the chordwise position exerts a more significant impact on the structural modes and flutter speed of the wing.A hybrid aeroelastic control system,incorporating motion planning and control law,is proposed to evaluate real-time performance in Active Flutter Suppression(AFS)and Gust Load Alleviation(GLA).Control outcomes suggest that,with a mass ratio of 1/16 and a half-chord installation area for the guide rail,flutter speed increases by about 10%.Additionally,excitation amplitudes across different gust frequencies are substantially mitigated,achieving a maximum reduction of vibration amplitude by about 73%.These findings offer a comprehensive understanding of the MMC technique and its application to flexible aircraft.展开更多
In this paper,a series of flutter simulations are carried out to investigate the effects of split drag rudder(SDR)on the transonic flutter characteristic of rigid NACA 64A010.A structural dynamic model addressing two-...In this paper,a series of flutter simulations are carried out to investigate the effects of split drag rudder(SDR)on the transonic flutter characteristic of rigid NACA 64A010.A structural dynamic model addressing two-degree-of-freedom pitch-plunge aeroelastic oscillations was coupled with the unsteady Reynolds-averaged Navier-Stokes equations to perform flutter simulation.Meanwhile,the influence mechanism of SDR on flutter boundary is explained through aerodynamic work and the correlated shock wave location.The results show that the SDR delays the shock wave shifting downstream,and the Mach number corresponding to reaching freeze region increases as the split angle increases.Therefore,the peak value of aerodynamic moment coefficient amplitude and the sharp ascent process of phase occurs at higher Mach number,which leads to the delay in the occurrence of the transonic dip.Besides,before the transonic dip of airfoil without SDR occurs,the aerodynamic moment phase of airfoil with the SDR decreases slowly due to the decrease in the speed of shock wave moving downstream.This results in an increased flutter speed when employing the SDR before the transonic dip of airfoil without SDR occurs.Meanwhile,the effects of asymmetric split angles on the transonic flutter characteristics are also investigated.Before the transonic dip of airfoil without SDR occurs,the flutter characteristic is dominated by the smaller split angle.展开更多
Advanced propulsion systems experience critical challenges under extreme service conditions,including aerodynamic loads and thermal loads.Especially,flutter stability is a key bottleneck restricting the design and saf...Advanced propulsion systems experience critical challenges under extreme service conditions,including aerodynamic loads and thermal loads.Especially,flutter stability is a key bottleneck restricting the design and safe op⁃eration of hot structures in advanced propulsion systems employing ceramic matrix composites(CMCs).Compared to traditional nickel-based alloys,CMCs offer superior high-temperature resistance and specific strength,making them ideal for next-generation engine hot structures.The inherent anisotropy,heterogeneity,and complex nonlinear behav⁃ior of CMCs,coupled with extreme operating environments,result in strong multi-physics interactions,including aero-thermo-structural,thermo-mechanical,and damage-aeroelastic coupling.These complexities significantly com⁃plicate vibration stability and flutter analysis.The recent research progresses on these problems are systematically ex⁃amined,focusing on multi-field coupling mechanisms,material constitutive and damage evolution models,multi-scale modeling methods,coupled solution strategies,and the influence of key parameters on flutter characteristics.The current challenges are highlighted,including the complexity of high-temperature nonlinear modeling,the effi⁃ciency of multi-field coupling calculations,and the multi-scale modeling of complex weaving structures.Finally,an outlook on future development directions is presented to provide theoretical support for the design and safety assess⁃ment of hot structures of advanced CMCs.展开更多
Current research on active flutter suppression considering time delays tends to focus on fixed time delays.To address situations where the control loop may experience time-varying delays with uncertainty,a time-varyin...Current research on active flutter suppression considering time delays tends to focus on fixed time delays.To address situations where the control loop may experience time-varying delays with uncertainty,a time-varying-delay Active Disturbance Rejection Control(TVD-ADRC)is proposed.First,a parameterized unsteady aerodynamic reduced-order model(ROM)based on a long short-term memory network is introduced into the aeroservoelastic modeling.This model is applied to predict unsteady aerodynamic forces and aeroservoelastic(ASE)behaviors across a wide range of Mach numbers.Its effectiveness in capturing the characteristics of unsteady aerodynamics is validated through comparisons with the high-fid elity computational fluid dynamics(CFD)simulations.Second,the proposed method integrates ADRC with a delayed input and a time-d elay identification module in the controller design.Specifically,the timevarying delay is identified using the cross-correlation function method with a moving window,and this method dynamically updates the time-delay compensation module.Additionally,a genetic algorithm is employed to optimize controller parameters,and the integral of the time-weighted absolute error is selected as the performance evaluation index for the control system.Finally,a three-degree-of-freedom aeroservoelastic system of an airfoil with a trailing-edge control surface is studied for flutter suppression.Flutter control under uncertain time-varying delays during flutter occurrence is investigated,and the impact of the magnitude of the time delay on the effectiveness of the flutter control is analyzed.Simulation results indicate that the proposed TVDADRC controller could effectively suppress the aeroelastic instabilities across a wide range of Mach numbers and effectively counteract the negative effects of time-varying delays.展开更多
Lung transplantation(LT)is now an accepted therapy for end stage lung disease in appropriate patients.Atrial arrhythmias(AA)can occur after LT.Early AA after LT are most often atrial fibrillation,whereas late arrhythm...Lung transplantation(LT)is now an accepted therapy for end stage lung disease in appropriate patients.Atrial arrhythmias(AA)can occur after LT.Early AA after LT are most often atrial fibrillation,whereas late arrhythmias which occur many months or years after LT are often atrial tachycardia.The causes of AA are multifactorial.The review begins with a brief history of LT and AA.This review further describes the pathophysiology of the AA.The risk factors,incidence,recipient characteristics including intra-operative factors are elaborated on.Since there are no clear and specific guidelines on the management of atrial arrhythmia following LT,the recommended guidelines on the management of AA in general are often extrapolated and used in the setting of post LT arrhythmia.The strategy of rate control vs rhythm control is discussed.The pros and cons of various drug regimen,need for direct current cardioversion and catheter ablation therapies are considered.Possible methods to prevent or reduce the incidence of AA after LT are considered.The impact of AA on the short-term and long-term outcomes following LT is discussed.展开更多
基金sponsored by the National Natural Science Foundation of China(Grant No.32373187)the Research Fund for International Scientists of the National Natural Science Foundation of China(Grant No.32350410404)the Natural Science Foundation of Shanghai(Grant No.23ZR1427000).
文摘This study experimentally investigates the hydrodynamic characteristics,geometric configurations,fluttering motions of the codend,and the instantaneous flow fields inside and around the codend,with and without a liner,under varying catch sizes and inflow velocities.A proper orthogonal decomposition method is employed to extract phase-averaged mean properties of unsteady turbulent flows from flow measurement data obtained using an electromagnetic current velocity meter inside and around the codend.The results reveal that as catch size increases,the drag force,codend motion,Reynolds number,and codend volume increase while the drag coefficient decreases.Owing to the codend shape and pronounced motion,a complex fluid–structure interaction occurs,demonstrating a strong correlation between drag force and codend volume.The oscillation amplitudes of the hydrodynamic forces and codend motions increase with increasing catch size,and their oscillations mainly involve low-frequency activity.A significant reduction in the flow field occurs inside and around the unlined codend without a catch.The flow field is 5.81%,14.39%,and 27.01%lower than the unlined codend with a catch,the codend with a liner but without a catch,and the codend with both a liner and a catch,respectively.Fourier analysis reveals that the codend motions and hydrodynamic forces are mainly characterized by low-frequency activity and are synchronized with the unsteady turbulent flow street.Furthermore,the proper orthogonal decomposition results reveal the development of unsteady turbulent flow inside and around the codend,driven by flow passage blockage caused by the presence of the liner,intense codend motions,and the catch.Understanding the hydrodynamic characteristics and flow instabilities inside and around the codend,particularly those associated with its fluttering motions,is crucial for optimizing trawl design and improving trawl selectivity.
基金This study was supported by the National Natural Science Foundation of China(No.31902426)the Shanghai Sailing Program(No.19YF1419800)the Special Project for Exploitation and Utilization of Antarctic Biological Resources of the Ministry of Agriculture and Rural Affairs(No.D-8002-18-0097).
文摘The dynamic coupling between the fluttering motions and hydrodynamic characteristics of codend is essential in understanding the trawl selectivity through fish response and the drag force acting on the whole trawl.This study investigated the effect of towing speed,warp length,warp tension,and catch size on the fluttering motions of Antarctic krill trawl codend during net shooting,towing,and hauling by using sea trial data.The time-periodicity of codend oscillation was analyzed by the Morlet wavelet transform method.Results indicated that the period of codend oscillation was between 50 s and 90 s and showed an increasing trend with the warp tension but a decreased value at the towing stage.The coefficient amplitude of codend oscillation was between 0 and 4 at the net shooting and hauling stages,and between 0.2 and 0.6 at the towing stage.The amplitude of codend oscillation increased with the warp tension,towing speed,and catch size,but decreased with the increase of the warp length.In addition,the period of codend oscillation increased with the towing speed at the net shooting and hauling stages,but decreased at the towing stage.These results from codend fluttering motions can improve the understanding of fish behavior and gear shape that modify the hydrodynamic force on the codend instantaneously.
文摘This work describes investigations performed on the interaction of uniform current and freely rotating plate about a fixed vertical axis. Fluttering and autorotation are two different motions that may occur during the flow induced rotation. The dimensional analysis proves that the motion in flow induced rotation motion is governed essentially by the dimensionless moment of inertia and Reynolds number. Certain combinations define the stability boundaries between fluttering and autorotation. Fluttering is oscillation of body about a vertical axis and the autorotation is a name given to the case when the body turns continuously about the vertical axis First, the loads and moment coefficients are calculated by experiments and streamline theory for different angles of attack for a fixed fiat plate. Then for dynamic case, a bifurcation diagram is presented based on experiments to classify different motion states of flow induced rotation. Finally, a dynamical model is proposed for stability analysis of flow induced rotation of a flat plate.
文摘Atrial fibrillation(AF)/atrial flutter(AFL)is the most common sustained cardiac arrhythmia.The known risk factors for developing AF/AFL include age,structural heart disease,hypertension,diabetes mellitus,or hyperthyroidism.This study aims to attribute the trends in AF/AFL-related mortalities over the past two decades 1999-2020 concerning race and sex and disparity among them.To the best of our knowledge,this is the first study that estimates the trends and mortality due to AF/AFL from 1999-2020 in older adults in the United States.In this 21-year analysis of mortality data,we found a constant increase in mortality rates due to AF/AFL in older adults.From 1999 to 2020,the overall mortality in older adults aged 65 and above,regardless of sex and race,is found to be almost doubled i.e.about a 50.2%increase in the number of deaths due to AF/AFL.Furthermore,other confounding risk factors such has obesity,prior myocardial infarction,inflammation,hypertension,birth weight,diabetes mellitus,hyperthyroidism,hormone replacement therapy in menopausal women increases the risk in the occurrence or recurrent occurrence of AF.
文摘目的:为了提高医疗设备验收的信息化管理水平,设计多端协同医疗设备验收管理系统。方法:多端协同医疗设备验收管理系统采用前后端分离的设计架构,前端采用跨平台框架Flutter和Dart语言开发,后端采用Tornado 6.1框架和Python语言开发,前端与后端服务之间的通信遵循RESTful设计原则,通过超文本传输协议(hypertext transfer protocol,HTTP)请求进行交互。整个系统包括用户管理、基础信息管理、验收管理3个功能模块。结果:该系统实现了医疗设备验收过程的信息化管理,支持跨平台管理验收报告及相关附件、医疗器械注册证等内容,提高了验收的工作质量与效率。结论:该系统实现了医疗设备验收的多端协同管理,为医院医疗设备管理的数字化和智能化转型奠定了基础。
基金the National Key Research and Development Program of China(No.2021YFB3400100)the National Natural Science Foundation of China(Nos.52235003&U2241261)。
文摘This study introduces a novel approach for coupled aeroelastic analysis of panel subjected to supersonic airflow,utilizing Add-On Acoustic Black Hole(AABH)to mitigate panel flutter.Employing Galerkin's method to discretize aeroelastic equation of panel and leveraging finite element method to derive a reduced discrete model of AABH,this study effectively couples two substructures via interface displacement.Investigation into the interactive force highlights the modal effective mass,frequency discrepancy between oscillation and AABH mode,and modal damping ratio as critical factors influencing individual AABH mode in flutter suppression.The selection of effective AABH modes,closely linked to these factors,directly influences the accuracy of simulations.The results reveal that AABH notably enhances the panel's critical flutter boundary by14.6%,a significant improvement over the 3.6%increase afforded by equivalent mass.Furthermore,AABH outperforms both the tuned mass damper and nonlinear energy sink in flutter suppression efficacy.By adjusting the AABH's geometrical parameters to increase the accumulative modal effective mass within the pertinent frequency range,or choosing a suitable installation position for AABH,its performance in flutter suppression is further optimized.These findings not only underscore the AABH's potential in enhancing aeroelastic stability but also provide a foundation for its optimal design.
文摘The integration of wearable technology and remote monitoring (RM) has significantlytransformed the early detection, continuous monitoring, and managementof cardiac arrhythmias. These conditions, characterized by irregular heart rhythms,arise from various etiological factors, including congenital, structural, immunological,metabolic, and infectious diseases, with atrial fibrillation being themost prevalent type. Diagnosing arrhythmias remains challenging due to variableclinical presentations and episodic symptom manifestations, necessitating individualizedmanagement strategies. Recent advances in wearable technology offerscalable, cost-effective solutions for real-time arrhythmia monitoring. These devicesare equipped with sophisticated sensors and data analytics that enable earlydetection and personalized interventions, while empowering patients to activelyengage in their healthcare. Integrating RM systems enhances diagnostic accuracyand facilitates timely medical interventions. Despite their potential, regulatory,legal, privacy, security, and infrastructural challenges hinder the widespreadadoption of wearable technology and RM. Addressing these barriers requirescollaboration among stakeholders and rigorous clinical trials to assess theirefficacy and feasibility. Future research should focus on refining wearable technology,improving user experience, and integrating these innovations into existinghealthcare frameworks. Overcoming these challenges will maximize the potentialof wearable technology and RM, ultimately enhancing the management of cardiacarrhythmias and improving patient outcomes.
基金supported in part by the Aeronautical Science Foundation of China under Grant 2022Z005057001the Joint Research Fund of Shanghai Commercial Aircraft System Engineering Science and Technology Innovation Center under CASEF-2023-M19.
文摘An aileron is a crucial control surface for rolling.Any jitter or shaking caused by the aileron mechatronics could have catastrophic consequences for the aircraft’s stability,maneuverability,safety,and lifespan.This paper presents a robust solution in the form of a fast flutter suppression digital control logic of edge computing aileron mechatronics(ECAM).We have effectively eliminated passive and active oscillating response biases by integrating nonlinear functional parameters and an antiphase hysteresis Schmitt trigger.Our findings demonstrate that self-tuning nonlinear parameters can optimize stability,robustness,and accuracy.At the same time,the antiphase hysteresis Schmitt trigger effectively rejects flutters without the need for collaborative navigation and guidance.Our hardware-in-the-loop simulation results confirm that this approach can eliminate aircraft jitter and shaking while ensuring expected stability and maneuverability.In conclusion,this nonlinear aileron mechatronics with a Schmitt positive feedback mechanism is a highly effective solution for distributed flight control and active flutter rejection.
基金supported by the Science Center for Gas Turbine Project,China(No.P2022-C-II-001-001)the National Science and Technology Major Project,Chinathe Innovation Foundation for Doctor Dissertation of Northwestern Polytechnical University,China(No.CX2022045).
文摘Flutter and forced response, as two main branches of aeroelasticity, can lead to high-cycle fatigue failure of turbomachinery blades. Efficiently and accurately assessing aeroelastic performance of turbomachinery blades is essential in the routine design. In this work, the Time Collocation Method (TCM) which uses the cubic B-spline to approximate flow variables is first thoroughly studied and then combined with the moving grid technique to analyze aeroelastic flow fields. To showcase its advantage over the Harmonic Balance (HB) method which uses a truncated Fourier series to approximately represent flow variables, a matrix analysis of the one-dimensional advection equation is first performed. The results of stability analysis are verified by two test cases: the Durham linear oscillating turbine cascade and a two-blade-row transonic compressor. The vibration of the blade of the first case is driven by a motor while the excitation force of the second case comes from blade row interaction. The results show that the time collocation method has a faster convergence rate and is more stable than the harmonic balance method, especially for cases with a large maximum grid reduced frequency. More importantly, the time collocation method is capable of accurately predicting aeroelastic performance of turbomachinery blades.
基金support of the National Natural Science Foundation of China(No.51675406)the Basic Research Project Group,China(No.514010106-205)。
文摘The implicit partition algorithm used to solve fluid–structure coupling problems has high accuracy,but it requires a long computation time.In this paper,a semi-implicit fluid–structure coupling algorithm based on modal force prediction-correction is proposed to improve the computational efficiency.In the pre-processing stage,the fluid domain is assumed to be a pseudo-elastic solid and merged with the solid domain to form a holistic system,and the normalized modal information of the holistic system is calculated and stored.During the sub-step cycle,the modal superposition method is used to obtain the response of the holistic system with the predicted modal force as the load,so that the deformation of the structure and the updating of the fluid mesh can be achieved simultaneously.After solving the Reynolds-averaged Navier-Stokes equations in the fluid domain,the predicted modal force is corrected and a new sub-step cycle is started until the converged result is obtained.In this method,the computation of the fluid equations and the updating of the dynamic mesh are done implicitly,while the deformation of the structure is done explicitly.Two numerical cases,vortex induced oscillation of an elastic beam and fluid–structure interaction of a final stage blade,are used to verify the efficiency and accuracy of the proposed algorithm.The results show that the proposed method achieves the same accuracy as the implicit method while the computational time is reduced.In the case of the vortex-induced oscillation problem,the computational time can be reduced to 18.6%.In the case of the final stage blade vibration,the computational time can be reduced to 53.8%.
基金SW is supported by the HK GRF under Grant Nos.17306024 and 17313122the CRF under Grant No.C7012-21G+2 种基金a RGC Fellowship Award under No.HKU RFS2223-7S03XWG and ZHZ are supported by the NSFC key under Grant Nos.12134015,92365202,12121004,12175290the National Key R&D Program of China under Grant No.2022YFA1404102.
文摘Quantum flutter is a ubiquitous phenomenon which can be observed from the fast moving impurity injected into a fermionic or bosonic medium of quantum liquid.In this scenario,one usually considers a medium of a fully polarized state and injects a spin-flipped impurity as the initial state.When the initial velocity of the impurity is beyond the intrinsic sound velocity of the medium,the impurity momentum dramatically exhibits a long-lived periodic oscillation with the periodicity remaining invariant with respect to the initial velocity.In this paper,we show that such a novel phenomenon can be explained by a linear Luttinger liquid coupled to a deep hole in the Fermi sea.Once the deep hole excitations are involved and the impurity momentum surpasses the Fermi momentum,the propagator thus displays a periodic oscillation after a quick relaxation decay.The oscillation periodicity is solely determined by the energy of the deepest hole excitation.Our result provides deep insights into the dynamical behavior of quantum impurities immersed into one-dimensional quantum liquids.
基金co-supported by the National Natural Science Foundation of China(Nos.52472394,52425211,52201327,52272360)。
文摘Stall flutter poses great challenges to flight safety.To alleviate this problem,a steady blowing control considering the perturbation and wake-induced vibration at a large angle of attack is developed in this paper,where two blowings are configured on upper and lower tail surfaces to suppress the stall flutter.The stall flutter with one-degree-of-freedom is first evaluated by numerical simulation.The equation of motion for stall flutter is solved by the Newmark-β method.Then,the stall flutter responses for five blowing speeds,i.e.,0,4,12,20,and 28 m/s under the airspeed range of 3–9 m/s,are studied in detail.The stall flutter suppression mechanism can be summarized as follows:a large blowing speed can inject energy into the boundary layer and enhance the high-pressure zone,which delays the flow separation on the suction surface.In this way,the formation of the leading-edge separation vortex is suppressed.Thus,the dynamic stall vortex is weakened and accelerates shedding.In addition,the driving moment is reduced,which leads to a decrement in the stall flutter amplitude.When the blowing speed is 28 m/s(stall flutter amplitude=0.1357 rad),compared with uncontrolled case(stall flutter amplitude=0.6002 rad),the amplitude can decrease by 77.39%,which demonstrates the effectiveness of the proposed steady blowing based active control strategy.
基金supported by the Natural Science Foundation of Shandong Provincial of China(Grant Number ZR2022ME093)the Natural Science Foundation of China(Grant Number 51675315).
文摘With the gradual increase in the size and flexibility of composite blades in large wind turbines,problems related toaeroelastic instability and blade vibration are becoming increasingly more important.Given their impact on thelifespan of wind turbines,these subjects have become important topics in turbine blade design.In this article,firstaspects related to the aeroelastic(structural and aerodynamic)modeling of large wind turbine blades are summarized.Then,two main methods for blade vibration control are outlined(passive control and active control),including the case of composite blades.Some improvement schemes are proposed accordingly,with a specialfocus on the industry’s outstanding suppression scheme for stall-induced nonlinear flutter and a new high-frequencymicro-vibration control scheme.Finally,future research directions are indicated based on existingresearch.
基金supported by the National Natural Science Foundation of China(No.12102096)the Guangdong Basic and Applied Basic Research Foundation,China(No.2022A1515011885)the Research Fund of National Key Laboratory of Aerospace Physics in Fluids,China(No.2024-APF-KFQMJJ-08)。
文摘Aeroelastic control is a critical technique for high-aspect-ratio flexible wings.A novel aeroelastic control method is introduced,utilizing the internal Moving Mass Control(MMC)technique,which demonstrates the potential to fulfill hybrid control demands without incurring a drag penalty.Dynamic equations for a flexible wing equipped with a spanwise moving mass under unsteady aerodynamic loading are derived using mass position as the input variable.Controloriented analyses indicate that intrinsic structural frequencies,flutter characteristics,and gust response can be actively modified by varying the spanwise and chordwise positions of the mass element.Among these,the chordwise position exerts a more significant impact on the structural modes and flutter speed of the wing.A hybrid aeroelastic control system,incorporating motion planning and control law,is proposed to evaluate real-time performance in Active Flutter Suppression(AFS)and Gust Load Alleviation(GLA).Control outcomes suggest that,with a mass ratio of 1/16 and a half-chord installation area for the guide rail,flutter speed increases by about 10%.Additionally,excitation amplitudes across different gust frequencies are substantially mitigated,achieving a maximum reduction of vibration amplitude by about 73%.These findings offer a comprehensive understanding of the MMC technique and its application to flexible aircraft.
文摘In this paper,a series of flutter simulations are carried out to investigate the effects of split drag rudder(SDR)on the transonic flutter characteristic of rigid NACA 64A010.A structural dynamic model addressing two-degree-of-freedom pitch-plunge aeroelastic oscillations was coupled with the unsteady Reynolds-averaged Navier-Stokes equations to perform flutter simulation.Meanwhile,the influence mechanism of SDR on flutter boundary is explained through aerodynamic work and the correlated shock wave location.The results show that the SDR delays the shock wave shifting downstream,and the Mach number corresponding to reaching freeze region increases as the split angle increases.Therefore,the peak value of aerodynamic moment coefficient amplitude and the sharp ascent process of phase occurs at higher Mach number,which leads to the delay in the occurrence of the transonic dip.Besides,before the transonic dip of airfoil without SDR occurs,the aerodynamic moment phase of airfoil with the SDR decreases slowly due to the decrease in the speed of shock wave moving downstream.This results in an increased flutter speed when employing the SDR before the transonic dip of airfoil without SDR occurs.Meanwhile,the effects of asymmetric split angles on the transonic flutter characteristics are also investigated.Before the transonic dip of airfoil without SDR occurs,the flutter characteristic is dominated by the smaller split angle.
基金supported by the Na⁃tional Science and Technology Major Project(No.Y2019-Ⅰ⁃0018-0017)the National Natural Science Foundation of China(No.U24A2051)+2 种基金the Natural Science Foundation of Jiangsu Province(No.BK20232037)the Foundation of Key Laboratory of Aero-engine Thermal Environment and Structure,Ministry of Industry and Information Technology(No.CEPE2024002)the Postgraduate Research&Practice Innovation Program of Jiangsu Province(No.KY⁃CX24_0605)。
文摘Advanced propulsion systems experience critical challenges under extreme service conditions,including aerodynamic loads and thermal loads.Especially,flutter stability is a key bottleneck restricting the design and safe op⁃eration of hot structures in advanced propulsion systems employing ceramic matrix composites(CMCs).Compared to traditional nickel-based alloys,CMCs offer superior high-temperature resistance and specific strength,making them ideal for next-generation engine hot structures.The inherent anisotropy,heterogeneity,and complex nonlinear behav⁃ior of CMCs,coupled with extreme operating environments,result in strong multi-physics interactions,including aero-thermo-structural,thermo-mechanical,and damage-aeroelastic coupling.These complexities significantly com⁃plicate vibration stability and flutter analysis.The recent research progresses on these problems are systematically ex⁃amined,focusing on multi-field coupling mechanisms,material constitutive and damage evolution models,multi-scale modeling methods,coupled solution strategies,and the influence of key parameters on flutter characteristics.The current challenges are highlighted,including the complexity of high-temperature nonlinear modeling,the effi⁃ciency of multi-field coupling calculations,and the multi-scale modeling of complex weaving structures.Finally,an outlook on future development directions is presented to provide theoretical support for the design and safety assess⁃ment of hot structures of advanced CMCs.
基金supported by the National Natural Science Foundation of China(12302027,11702255)the Natural Science Foundation of Henan(232300421357)+1 种基金the Scientific Research Team Plan of Zhengzhou University of Aeronautics(23ZHTD01006)the Open Funding of Henan Key Laboratory of General Aviation Technology(ZHKF-240211)。
文摘Current research on active flutter suppression considering time delays tends to focus on fixed time delays.To address situations where the control loop may experience time-varying delays with uncertainty,a time-varying-delay Active Disturbance Rejection Control(TVD-ADRC)is proposed.First,a parameterized unsteady aerodynamic reduced-order model(ROM)based on a long short-term memory network is introduced into the aeroservoelastic modeling.This model is applied to predict unsteady aerodynamic forces and aeroservoelastic(ASE)behaviors across a wide range of Mach numbers.Its effectiveness in capturing the characteristics of unsteady aerodynamics is validated through comparisons with the high-fid elity computational fluid dynamics(CFD)simulations.Second,the proposed method integrates ADRC with a delayed input and a time-d elay identification module in the controller design.Specifically,the timevarying delay is identified using the cross-correlation function method with a moving window,and this method dynamically updates the time-delay compensation module.Additionally,a genetic algorithm is employed to optimize controller parameters,and the integral of the time-weighted absolute error is selected as the performance evaluation index for the control system.Finally,a three-degree-of-freedom aeroservoelastic system of an airfoil with a trailing-edge control surface is studied for flutter suppression.Flutter control under uncertain time-varying delays during flutter occurrence is investigated,and the impact of the magnitude of the time delay on the effectiveness of the flutter control is analyzed.Simulation results indicate that the proposed TVDADRC controller could effectively suppress the aeroelastic instabilities across a wide range of Mach numbers and effectively counteract the negative effects of time-varying delays.
文摘Lung transplantation(LT)is now an accepted therapy for end stage lung disease in appropriate patients.Atrial arrhythmias(AA)can occur after LT.Early AA after LT are most often atrial fibrillation,whereas late arrhythmias which occur many months or years after LT are often atrial tachycardia.The causes of AA are multifactorial.The review begins with a brief history of LT and AA.This review further describes the pathophysiology of the AA.The risk factors,incidence,recipient characteristics including intra-operative factors are elaborated on.Since there are no clear and specific guidelines on the management of atrial arrhythmia following LT,the recommended guidelines on the management of AA in general are often extrapolated and used in the setting of post LT arrhythmia.The strategy of rate control vs rhythm control is discussed.The pros and cons of various drug regimen,need for direct current cardioversion and catheter ablation therapies are considered.Possible methods to prevent or reduce the incidence of AA after LT are considered.The impact of AA on the short-term and long-term outcomes following LT is discussed.
