检索结果-南通市图书馆

正义缺席、自由丧失与人性异化——数字劳动的伦理困境及其应对之策

在线全文

学校读者我要写书评

暂无评论

兵团党校学报 2024年第3期208卷 26-34页

作者：黄金泉华中科技大学湖北武汉430074

随着信息科技与人工智能的飞速发展,数字技术的应用已经成为我们日常生活的常态,我们已经进入了一个“数字化生存”的时代。“数字劳动”作为“数字化生存”时代产生的一种新型的劳动方式,颠覆了传统劳动者与劳动之间的关系,虽然在一定... 详细信息

随着信息科技与人工智能的飞速发展,数字技术的应用已经成为我们日常生活的常态,我们已经进入了一个“数字化生存”的时代。“数字劳动”作为“数字化生存”时代产生的一种新型的劳动方式,颠覆了传统劳动者与劳动之间的关系,虽然在一定程度上实现了数据的自由、开放和共享,但与此同时也具有多重伦理上的困境。首先是正义的缺席,即数据贡献与成果应得的不相匹配,具体来说就是产消合一导致数字资本家与数字劳动者之间的地位不平等,“数字玩工”的娱乐化性质导致数字劳动者被隐蔽的剥削,算法歧视导致数据弱势群体被边缘化。其次是自由的丧失,即积极自由与消极自由的双重沦丧,具体来说就是全时段、多方位的时空剥削导致积极自由的丧失,全景监视与共景监视的双重控制导致消极自由的丧失。最后则是人性的异化,即人与人的类本质相异化的主体性丧失与人同人相异化的社会性丧失。为了应对数字劳动的伦理困境,首先要确立一条总的原则:坚持“人是目的”的本体论导向,杜绝数字劳动中的工具化行为;其次从平等的角度出发,我们打破数据的垄断和霸权,坚持数据的透明和共享,对数字劳动成果进行公平的分配,并规制算法歧视;再次从自由的角度出发,我们要强化数字劳动者的个人隐私意识以及数据使用者的责任意识,保护好数字劳动者的积极自由和消极自由;最后从人性的角度出发,我们要制定相关的数字劳动法,完善立法保障,确立数字劳动者的主体地位,促使技术向善发展,不做有损人性和人类尊严的事。

关键词：数字劳动数字化生存正义自由人性

Direct thrust control for multivariable turbofan approach

同方期刊数据库博看期刊评论

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2022年第6期35卷 125-136页

作者： Yiyang ZHU jinquan huang Muxuan PAN Wenxiang ZHOU Jiangsu Province Key Laboratory of Aerospace Power System College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China

A novel turbofan Direct Thrust Control(DTC)architecture based on Linear ParameterVarying(LPV)approach for a two-spool turbofan engine thrust control is proposed in this *** of transforming thrust command to shaft speed command and pressure ratio command,the thrust will be directly controlled by an optimal controller with two control *** model of the engine is established for the designing of thrust estimator and controller.A robust LPV H∞filter is introduced to estimate the unmeasurable thrust according to measurable engine *** thrust estimation error system is proved to be Affinely Quadratically Stable(AQS)in the whole parameter box with a prescribed H∞performance indexγ.Due to the existence of overdetermined equations,the solving of controller parameters is a multi-solution ***,Particle Swarm Optimization(PSO)algorithm is used to optimize the controller parameters to obtain satisfactory control performance based on the engine’s LPV *** simulations show that the thrust estimator can acquire smooth and accurate estimating results when sensor noise *** optimal controller can receive desired control performance both in steady and transition control tasks within the engine working states above the idle,verifying the effectiveness of the proposed DTC architecture’s application in thrust direct control problem.

关键词： Turbofan engine Direct thrust control Linear Parameter Varying(LPV)approach Particle Swarm Optimization(PSO) Robust LPV H∞filter

Neural network-based model predictive control with fuzzy-SQP optimization for direct thrust control of turbofan engine

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2022年第12期35卷 59-71页

作者： Yangjing WANG jinquan huang Wenxiang ZHOU Feng LU Wenhao XU Jiangsu Province Key Laboratory of Aerospace Power System College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China

A nonlinear model predictive control method based on fuzzy-Sequential Quadratic Programming(SQP)for direct thrust control is proposed in this paper for the sake of improving the accuracy of thrust *** designed control system includes four parts,namely a predictive model,rolling optimization,online correction,and feedback *** the strong nonlinearity of engine,a predictive model is established by Back Propagation(BP)neural network for the entire flight envelope,whose input and output are determined with random forest algorithm and actual situation *** optimization typically uses SQP as the optimization algorithm,but SQP algorithm is easy to trap into local ***,the fuzzy-SQP algorithm is proposed to prevent this disadvantage using fuzzy algorithm to determine the initial value of *** addition to the traditional three parts of model predictive control,an online correction module is added to improve the predictive accuracy of the predictive model in the predictive time *** results show that the BP predictive model can reach a certain degree of predictive accuracy,and the proposed control system can achieve good tracking performance with the limited parameters within the safe range。

关键词： Direct thrust control Fuzzy-SQP algorithm Limit protection Neural network Nonlinear model predictive control Random forest Turbofan engine

Fault diagnosis based on measurement reconstruction of HPT exit pressure for turbofan engine

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2019年第5期32卷 1156-1170页

作者： Xin ZHOU Feng LU jinquan huang College of Energy and Power Engineering Jiangsu Province Key Laboratory of Aerospace Power System Nanjing University of Aeronautics and Astronautics

Aero-engine gas path health monitoring plays a critical role in Engine Health Management(EHM). To achieve unbiased estimation, traditional filtering methods have strict requirements on measurement parameters which sometimes cannot be measured in engineering. The most typical one is the High-Pressure Turbine(HPT) exit pressure, which is vital to distinguishing failure modes between different turbines. For the case of an abrupt failure occurring in a single turbine component, a model-based sensor measurement reconstruction method is proposed in this paper. First,to estimate the missing measurements, the forward algorithm and the backward algorithm are developed based on corresponding component models according to the failure hypotheses. Then,a new fault diagnosis logic is designed and the traditional nonlinear filter is improved by adding the measurement estimation module and the health parameter correction module, which uses the reconstructed measurement to complete the health parameters estimation. Simulation results show that the proposed method can well restore the desired measurement and the estimated measurement can be used in the turbofan engine gas path diagnosis. Compared with the diagnosis under the condition of missing sensors, this method can distinguish between different failure modes, quantify the variations of health parameters, and achieve good performance at multiple operating points in the flight envelope.

关键词： Component-level model Condition monitoring Fault diagnosis Measurement reconstruction Turbofan engines Unscented Kalman filter

New function of gossypol,a natural product of cotton

在线全文

学校读者我要写书评

暂无评论

Journal of Cotton Research 2022年第4期5卷 42-43页

作者： huang jinquan CHEN Xiaoya State Key Laboratory of Plant Molecular Genetics CAS Center for Excellence in Molecular Plant SciencesShanghai Institute of Plant Physiology and EcologyUniversity of CASChinese Academy of SciencesShanghai 200032China

Cotton plants are not only the global crops integrating fiber,oil and protein(Hu et al.2020;Xiao et al.2017),but also the medicinal plants with potent application values,which were well described in the most complete and comprehensive medical book such as Compendium of Materia Medica and Chinese Materia ***-ton extract has various activities such as stopping bleed-ing,relieving pain,removing phlegm,and curing chronic *** types of metabolites or defense compounds are produced in cotton plants.

关键词： removing integrating crops

Application of multi-outputs LSSVR by PSO to the aero-engine model

在线全文

学校读者我要写书评

暂无评论

Journal of Systems Engineering and Electronics 2009年第5期20卷 1153-1158页

作者： Lu Feng huang jinquan Qiu Xiaojie Coll. of Energy and Power Engineering Nanjing Univ. of Aeronautics and Astronautics Nanjing 210016 P. R. China

Considering the modeling errors of on-board self-tuning model in the fault diagnosis of aero-engine, a new mechanism for compensating the model outputs is proposed. A discrete series predictor based on multi-outputs least square support vector regression （LSSVR） is applied to the compensation of on-board self-tuning model of aero-engine, and particle swarm optimization （PSO） is used to the kernels selection of multi-outputs LSSVR. The method need not reconstruct the model of aero-engine because of the differences in the individuals of the same type engines and engine degradation after use. The concrete steps for the application of the method are given, and the simulation results show the effectiveness of the algorithm.

关键词： aero-engine on-board self-tuning model multi-outputs least square support vector regression particle swarm optimization.

Limit protection design in turbofan engine acceleration control based on scheduling command governor

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2021年第10期34卷 67-80页

作者： Wenhao XU jinquan huang Jiakun QIN Muxuan PAN College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China

A new limit protection method based on Scheduling Command Governor(SCG) is proposed for imposing multiple constraints on a turbofan engine during acceleration process. A Gain Scheduling Controller(GSC) is designed for the transient state control and its stability proof is developed using Linear Matrix Inequalities(LMIs). The SCG is an add-on control scheme which manages engine limits effectively based on reference trajectory optimization. Unlike the traditional min–max architecture with switching logic, the SCG method utilizes the Linear Parameter Varying(LPV) closed-loop model to form a prediction of future constraint violation and per instant solves a constraint-admissible reference within an approximate Maximal Output Admissible Set(MOAS).The influence of the variation of engine dynamic characteristics and equilibrium points during transient state control is handled by the design of contractive sets. Simulation results on a turbofan engine component-level model show the applicability and effectiveness of the SCG method. Compared to the traditional min–max method, the SCG method has less conservativeness. In addition,the design of contractive sets makes conservativeness tunable.

关键词： Command governors Constrained control Contractive sets Gain scheduling Limit protection LPV model Turbofan engines

A multi-rate sensor fusion approach using information filters for estimating aero-engine performance degradation

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2019年第7期32卷 1603-1617页

作者： Feng LU Chunyu JIANG jinquan huang Xiaojie QIU Jiangsu Province Key Laboratory of Aerospace Power System College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing210016China Aviation Motor Control System Institute Aviation Industry Corporation of ChinaWuxi214063China

Gas-path performance estimation plays an important role in aero-engine health management, and Kalman Filter(KF) is a well-known technique to estimate performance degradation. In previous studies, it is assumed that different kinds of sensors are with the same sampling rate, and they are used for state estimation by the KF simultaneously. However, it is hard to achieve state estimation using various kinds of sensor measurements at the same sampling rate due to a complex network and physical characteristic differences between sensors, especially in an advanced multisensor architecture. For this purpose, a multi-rate sensor fusion using the information filtering approach is proposed based on the square-root cubature rule, which is called Multi-rate Squareroot Cubature Information Filter(MSCIF) to track engine performance degradation. Soft measurement synchronization of the MSCIF is designed to provide a sensor fusion condition for multiple sampling rates of measurement, and a fault sensor is isolated by maximum likelihood validation before state estimation. The contribution of this paper is to supply a novel multi-rate informationfilter approach for sensor fault tolerant health estimation of an aero-engine in a multi-sensor system. Tests are conducted for aero-engine performance degradation estimation with multiple sampling rates of sensor measurement on both digital simulation and semi-physical *** results illustrate the superiority of the proposed algorithm in terms of degradation estimation accuracy and robustness to sensor failure in a multi-sensor system.

关键词： Aero-engine Cubature information filter Performance degradation Sensor fusion State estimation

Robust decentralized control design for aircraft engines: A fractional type

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2019年第2期32卷 347-360页

作者： Muxuan PAN Liangjin CAO Wenxiang ZHOU jinquan huang Ye-Hwa CHEN College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics The George W.Woodruff School of Mechanical Engineering Georgia Institute of Technology

A new decentralized control for aircraft engines is proposed. In the proposed control approach, aircraft engines are considered as uncertain large-scale systems composed of interconnected uncertain subsystems. For each subsystem, the time-varying uncertainty, including parameter disturbances and interconnections in/between subsystems, is depicted by a class of general nonlinear functions. A fractional robust decentralized control with two parts, the nominal one and the fractional one, is presented. The nominal control guarantees the asymptotical stability of the engine system without uncertainty. The fractional part aims at overcoming the influences of uncertainty. Compared to the previous studies, the presented control provides not only an extra flexibility for the system performance tuning by the fraction-type gain but also a facility for the control input calculation. The proposed control approach is applied to a turbofan engine with two subsystems. The computer simulation shows that, in the flight envelope, the fractional control not only guarantees the closed-loop system uniform boundedness and ultimate uniform boundedness but also shows good economy.

关键词： Aircraft engines Large-scale systems Robust decentralized control Uncertainty Uniform boundedness Uniform ultimate boundedness