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| 1 | Deformation and failure mechanism of slope in three dimensions显示文摘Understanding three-dimensional(3D)slope deformation and failure mechanism and corresponding stability analyses are crucially important issues in geotechnical engineering.In this paper,the mechanisms of progressive failure with thrust-type and pull-type landslides are described in detail.It is considered that the post-failure stress state and the pre-peak stress state may occur at different regions of a landslide body with deformation development,and a critical stress state element(or the soil slice block)exists between the post-failure stress state and the pre-peak stress state regions.In this regard,two sorts of failure modes are suggested for the thrust-type and three sorts for pull-type landslides,based on the characteristics of shear stress and strain(or tensile stress and strain).Accordingly,a new joint constitutive model(JCM)is proposed based on the current stability analytical theories,and it can be used to describe the mechanical behaviors of geo-materials with softening properties.Five methods,i.e.CSRM(comprehensive sliding resistance method),MTM(main thrust method),CDM(comprehensive displacement method),SDM(surplus displacement method),and MPM(main pull method),for slope stability calculation are proposed.The S-shaped curve of monitored displacement vs.time is presented for different points on the sliding surface during progressive failure process of landslide,and the relationship between the displacement of different points on the sliding surface and height of landslide body is regarded as the parabolic curve.The comparisons between the predicted and observed load e displacement and displacement e time relations of the points on the sliding surface are conducted.The classi fi cation of stable/unstable displacement e time curves is proposed.The de fi nition of the main sliding direction of a landslide is also suggested in such a way that the failure body of landslide(simpli fi ed as'collapse body')is only involved in the main sliding direction,and the strike and the dip are the same as the collapse body.The rake angle is taken as the direction of the sum of sliding forces or the sum of displacements in collapse body,in which the main slip direction is dependent on progressive deformation.The reason of non-convergence with fi nite element method(FEM)in calculating the stability of slope is also numerically analyzed,in which a new method considering the slip surface associated with the boundary condition is proposed.It is known that the boundary condition of sliding surface can be described by perfect elasto-plastic model(PEPM)and JCM,and that the stress and strain of a landslide can be described properly with the JCM. | Yingfa Lu | 2015 | Journal of Rock Mechanics and Geotechnical Engineering2015，7，2： | 17 |
| 2 | Effects of temperature on the tribological behavior of Al0.25CoCrFeNi high-entropy alloy显示文摘The tribological behavior of Al0.25 CoCrFeNi high-entropy alloy(HEA) sliding against Si3N4 ball was investigated from room temperature to 600°. The microstructure of the alloys was characterized by simple FCC phase with 260 HV. Below 300°, with increasing temperature, the wear rate increased due to high temperature softening. The wear rate remained stabilized above 300°due to the anti-wear effect of the oxidation film on the contact interface. The dominant wear mechanism of HEA changed from abrasive wear at room temperature to delamination wear at 200°, then delamination wear and oxidative wear at 300°and became oxidative above 300°. Moreover, the adhesive wear existed concomitantly below 300°. | L.M.Du L.W.Lan S.Zhu H.J.Yang X.H.Shi P.K.Liaw J.W.Qiao | 2019 | Journal of Materials Science & Technology2019，35，5： | 17 |
| 3 | 阀控非对称缸系统鲁棒反馈线性化控制显示文摘针对阀控非对称缸液压系统存在不确定性和干扰问题,提出综合滑模变结构控制与反馈线性化控制的鲁棒反馈线性化控制策略.利用反馈线性化控制提高非线性系统控制精度,利用变结构控制补偿外界干扰与系统不确定性,并采用边界层法减少滑模变结构控制可能导致系统高频抖动.针对位移信号直接微分得到的加速度信号存在高频噪声问题,提出利用改进二阶滑模算法抑制干扰的影响.通过建立统一的阀控非对称缸液压伺服系统非线性数学模型,以时变负载力扰动为例对系统的动态特性进行了研究,结果表明:鲁棒反馈线性化策略能有效抑制外界的干扰和负载力扰动对液压位置追踪精度的影响,提高了液压控制系统的精度和鲁棒性. | 杨俊 谭建平 | 2014 | 华中科技大学学报(自然科学版)2014，42，2： | 15 |
| 4 | Multivariable sliding mode backstepping controller design for quadrotor UAV based on disturbance observer显示文摘This paper deals with the tracking control problem of quadrotor unmanned aerial vehicles(QUAVs) with external disturbances. First, because the QUAV model contains two non-integrity constraints,the dynamic model of the QUAV is decomposed into two subsystems which are independently controlled, so as to reduce controller design complexity. Secondly, the nonlinear disturbance observer(DOB) technique is integrated into a backstepping control method to design the controller for the first subsystem, in which a DOB is applied to estimate the lumped uncertainty. Based on the double power reaching law and the DOB,a multivariable sliding mode control(MSMC) scheme is developed for the second subsystem. Thirdly, based on Lyapunov theory, the closed-loop system is proved to be asymptotically stable. Finally, our comparative simulation results demonstrate that the presented control scheme behaves better in terms of tracking performance than the adaptive backstepping control(ABC) approach. | Zheng ZHANG Fang WANG Ying GUO Changchun HUA | 2018 | Science China(Information Sciences)2018，61，11： | 13 |
| 5 | Extended state observer-based third-order sliding mode finite-time attitude tracking controller for rigid spacecraft显示文摘In this paper, the attitude tracking control problem for a rigid spacecraft in the presence of system parameter uncertainties and external disturbances is addressed. First, a new nonsingular finite-time sliding surface is introduced and third-order sliding mode finite-time attitude control law is designed to achieve precise accurate tracking responses and robustness against inertia uncertainties and external disturbances.The stability of the closed-loop system is rigorously proved using the Lyapunov stability theory. Then, a new finite-time extended state observer is established to estimate total disturbances of the system. The extended stated observer-based sliding mode control technique yields improved disturbance rejection and high-precision attitude tracking. Moreover, this control law can avoid the unwinding phenomenon and overcome the input saturation constraint by introducing an auxiliary variable to compensate for the overshooting. A Lyapunov based analysis is provided to guarantee sufficiently small observation error and stabilization of the closed-loop system in finite time. Numerical simulations are conducted to verify the effectiveness of the proposed control method. | Chutiphon PUKDEBOON | 2019 | Science China(Information Sciences)2019，62，1： | 12 |
| 6 | Fractional order nonsingular terminal sliding mode control for flexible spacecraft attitude tracking显示文摘This paper investigates a fractional terminal sliding mode control for flexible spacecraft attitude tracking in the presence of inertia uncertainties and external disturbances. The controller is based on the fractional calculus and nonsingular terminal sliding mode control technique,and it guarantees the convergence of attitude tracking error in finite time rather than in the asymptotic sense. With respect to the controller,a fractional order sliding surface is given,the corresponding control scheme is proposed based on Lyapunov stability theory to guarantee the sliding condition,and the finite time stability of the whole close loop system is also proven. Finally,numerical simulations are presented to illustrate the performance of the proposed scheme. | GAO Junshan DENG Liwei SONG Shenmin | 2016 | Instrumentation2016，3，1： | 12 |
| 7 | Sliding Mode Control with Disturbance Observer for a Class of Nonlinear Systems显示文摘This paper is concerned with the stabilization problem for a class of nonlinear systems with disturbance. The disturbance model is unknown and the first derivative of disturbance is bounded. Firstly, a general disturbance observer is proposed to estimate disturbance approximatively. Secondly, since the bound of the disturbance observer error is unknown, an adaptive sliding mode controller is designed to guarantee that the state of system asymptotically converges to zero and the unknown bound can be adjusted by an adaptive law. Finally, an example is given to illustrate the effectiveness of the proposed method. | Lei-Po Liu Zhu-Mu Fu Xiao-Na Song College of Electric and Information Engineering, Henan University of Science and Technology, Luoyang 471003, China | 2012 | International Journal of Automation and computing2012，9，5： | 11 |
| 8 | Finite Time Convergent Wavelet Neural Network Sliding Mode Control Guidance Law with Impact Angle Constraint显示文摘This paper presents a novel guidance law to intercept non-maneuvering targets with impact angle and lateral acceleration command constraints. Firstly, we formulate the impact angle control to track the desired line-of-sight(LOS) angle, which is achieved by selecting the missile s lateral acceleration to enforce the sliding mode on a sliding surface at impact time. Secondly, we use the Lyapunov stability theory to prove the stability and finite time convergence of the proposed nonlinear sliding surface. Thirdly, we introduce the wavelet neural network(WNN) to adaptively update the additional control command and reduce the high-frequency chattering of sliding mode control(SMC). The proposed guidance law, denoted WNNSMC guidance law with impact angle constraint,combines the SMC methodology with WNN to improve the robustness and reduce the chattering of the system. Finally, numerical simulations are performed to demonstrate the validity and effectiveness of the WNNSMC guidance law. | Qing-Chun Li Wen-Sheng Zhang Gang Han Ying-Hua Zhang | 2015 | International Journal of Automation and computing2015，12，6： | 10 |
| 9 | Anisotropism of the Non-Smooth Surface of Butterfly Wing显示文摘Twenty-nine species of butterflies were collected for observation and determination of the wing surfaces using a ScanningElectron Microscope(SEM).Butterfly wing surface displays structural anisotropism in micro-,submicro- and nano-scales.Thescales on butterfly wing surface arrange like overlapping roof tiles.There are submicrometric vertical gibbosities,horizontallinks,and nano-protuberances on the scales.First-incline-then-drip method and first-drip-then-incline method were used tomeasure the Sliding Angle(SA)of droplet on butterfly wing surface by an optical Contact Angle(CA)measuring system.Relatively smaller sliding angles indicate that the butterfly wing surface has fine self-cleaning property.Significantly differentSAs in various directions indicate the anisotropic self-cleaning property of butterfly wing surface.The SAs on the butterfly wingsurface without scales are remarkably larger than those with scales,which proves the crucial role of scales in determining theself-cleaning property.Butterfly wing surface is a template for design and fabrication ofbiomimetic materials and self-cleaningsubstrates.This work may offer insights into how to design directional self-cleaning coatings and anisotropic wetting surface. | Gang Sun~(1,2), Yan Fang~(1,2), Qian Cong~1, Lu-quan Ren~11. Key Laboratory of Terrain-Machine Bionics Engineering (Ministry of Education, China), Jilin University,Changchun 130022, P. R. China2. School of Life Science, Changchun Normal University, Changchun 130032, P. R. China | 2009 | Journal of Bionic Engineering2009，6，1： | 10 |
| 10 | Sliding resistance of plates with bionic bumpy surface against soil显示文摘The non-smooth surface morphology of dung beetle, Copris ochus, was analyzed. The bulldozing plates with bionic geometric non-smooth or the chemical uneven surface were designed for the soil sliding test based on the simulation of the bumpy surface of the dung beetle. Special black metals— with different contents of alloys of manganese, silicon, chromium, copper and rare earth— were developed for making geometric non-smooth and chemical uneven surfaces by means of surface welding at the surfaces of a middle carbon steel plate. Four metals, with different surface properties including hardness and water contact angle were used to make the bulldozing plates for measuring the soil sliding resistance. Test results of soil sliding resistance indicate that all the geometric non-smooth plates and the chemical uneven plates reducing soil friction. Considering the materials and surface morphology, the bionic plate can reduce the soil sliding resistance from 18.1 % up to 42.2%, compared to the traditional smooth bulldozing plate made from middle carbon steel. The test results also show that the smaller the normal load, the greater effect on resistance reduction by the bionic non-smooth surface plates. | LI Jian-qiao1, SUN Jiu-rong2, REN Lu-quan1, CHEN Bing-cong1 1. Key Laboratory for Terrain-Machine Bionics Engineering (Ministry of Education, China), Jilin University, Changchun 130022, P. R. China 2. College of Life Science, Peking University, Beijing 100871, P. R. China 1 | 2004 | Journal of Bionic Engineering2004，1，4： | 9 |
| 11 | Terminal sliding mode control based on super-twisting algorithm显示文摘An improved non-singular terminal sliding mode control based on the super-twisting algorithm is proposed for a class of second-order uncertain nonlinear systems. This method can effectively avoid the singularity problem and obviously reduce the chattering phenomenon. The stability of the proposed procedure is proven to be finite-time convergence using the Lyapunov theory against uncertain unmodeled dynamic and external disturbances.An example is given to show the proposed improved non-singular terminal sliding mode control(SMC) law effectively. | Zhanshan Zhao Hongru Gu Jing Zhang Gang Ding | 2017 | Journal of Systems Engineering and Electronics2017，28，1： | 8 |
| 12 | Fixed-time adaptive model reference sliding mode control for an air-to-ground missile显示文摘This paper addresses the fixed-time adaptive model reference sliding mode control for an air-to-ground missile associated with large speed ranges, mismatched disturbances and un-modeled dynamics. Firstly, a sliding mode surface is developed by the tracking error of the state equation and the model reference state equation with respect to the air-to-ground missile. More specifically,a novel fixed-time adaptive reaching law is presented. Subsequently, the mismatched disturbances and the un-modeled dynamics are treated as the model errors of the state equation. These model errors are estimated by means of a fixed-time disturbance observer, and they are also utilized to compensate the proposed controller. Therefore, the fixed-time controller is obtained by an adaptive reaching law and a fixed-time disturbance observer. Closed-loop stability of the proposed controller is established. Finally, simulation results including Monte Carlo simulations, nonlinear six-DegreeOf-Freedom(6-DOF) simulations and different ranges are presented to demonstrate the efficacy of the proposed control scheme. | Liang ZHANG Changzhu WEI Rong WU Naigang CUI | 2019 | Chinese Journal of Aeronautics2019，32，5： | 8 |
| 13 | A Real-Time and Ubiquitous Network Attack Detection Based on Deep Belief Network and Support Vector Machine显示文摘In recent years, network traffic data have become larger and more complex, leading to higher possibilities of network intrusion. Traditional intrusion detection methods face difficulty in processing high-speed network data and cannot detect currently unknown attacks. Therefore, this paper proposes a network attack detection method combining a flow calculation and deep learning. The method consists of two parts: a real-time detection algorithm based on flow calculations and frequent patterns and a classification algorithm based on the deep belief network and support vector machine(DBN-SVM). Sliding window(SW) stream data processing enables real-time detection, and the DBN-SVM algorithm can improve classification accuracy. Finally, to verify the proposed method, a system is implemented.Based on the CICIDS2017 open source data set, a series of comparative experiments are conducted. The method's real-time detection efficiency is higher than that of traditional machine learning algorithms. The attack classification accuracy is 0.7 percentage points higher than that of a DBN, which is 2 percentage points higher than that of the integrated algorithm boosting and bagging methods. Hence, it is suitable for the real-time detection of high-speed network intrusions. | Hao Zhang Yongdan Li Zhihan Lv Arun Kumar Sangaiah Tao Huang | 2020 | IEEE/CAA Journal of Automatica Sinica2020，7，3： | 7 |
| 14 | 基于滑模磁链观测器的感应电机模型预测控制显示文摘感应电机模型预测控制通过系统状态预测的方法,利用设计好的目标函数直接控制磁链和转矩。该方案易于实现多变量控制和处理非线性约束,但因为预测过程需要使用电机的真实磁链,所以对磁链观测的精度有很高的要求,以滑模磁链观测器替代传统的电流模型和电压模型磁链观测器可大大提高该方案的控制性能。常规的滑模磁链观测器依据电流观测误差设计滑模控制函数,在实现对转子电阻变化的高鲁棒性的同时也引入了定子电阻变化的影响。文章中提出一种基于磁链观测误差的滑模控制函数设计方法,对滑模观测器的性能进行改进。因为磁链的真实值无法直接获取,磁链误差值以近似计算的方式得到。通过仿真和物理实验验证了该方案对电机参数变化的高鲁棒性。 | 孙佳将 卢勇辉 赵金 | 2019 | 微电机2019，52，5： | 6 |
| 15 | Adaptive sliding mode backstepping control for near space vehicles considering engine faults显示文摘A fault tolerant control methodology based adaptive sliding mode(ASM) backstepping is proposed for near space vehicle(NSV) attitude control system under engine faults. The proposed scheme combined adaptive backstepping with the sliding mode control strategy could guarantee the system's stability and track desired signals under external disturbances and engine faults. Firstly, attitude mode description and the engine faulty model are given. Secondly, a nominal control law is designed.Thirdly, a sliding mode observer is given later in order to estimate both the information of engine faults and external disturbances. An adaptive sliding mode technology based on the previous nominal control law is developed via updating faulty parameters. Finally,analyze the system's fault-tolerant performance and reliability through experiment simulation, which verifies the proposed design of fault-tolerant control can tolerate engine faults, as well as the strong robustness for external disturbance. | ZHAO Jing JIANG Bin XIE Fei GAO Zhifeng XU Yufei | 2018 | Journal of Systems Engineering and Electronics2018，29，2： | 5 |
| 16 | Parameter identification and synchronization of spatiotemporal chaos in an uncertain Gray-Scott system显示文摘The zero-asymptotic property of sliding variables in discrete systems is extended to a continuous one and applied to partial differential equations which describe spatiotemporal chaos. A method of chaos synchronization and parameter identifi-cation is proposed. The synchronization controllers and the parameter recognizers are designed. The uncertain Gray-Scott system is taken as an example to verify the effectiveness of the method. Simulation results show that the identification vari-ables in the parameter recognizers may take the place of the unknown parameters in both target and response systems. Global synchronization of the two spatio-temporal chaotic systems with uncertain parameters may be realized quickly after controllers are added. | LüLing LI Yi GUO ZhiAn | 2008 | Science China(Physics,Mechanics & Astronomy)2008，51，11： | 5 |
| 17 | Adaptive fuzzy integral sliding mode velocity control for the cutting system of a trench cutter显示文摘This paper presents a velocity controller for the cutting system of a trench cutter(TC). The cutting velocity of a cutting system is affected by the unknown load characteristics of rock and soil. In addition, geological conditions vary with time. Due to the complex load characteristics of rock and soil, the cutting load torque of a cutter is related to the geological conditions and the feeding velocity of the cutter. Moreover, a cutter's dynamic model is subjected to uncertainties with unknown effects on its function. In this study, to deal with the particular characteristics of a cutting system, a novel adaptive fuzzy integral sliding mode control(AFISMC) is designed for controlling cutting velocity. The model combines the robust characteristics of an integral sliding mode controller with the adaptive adjusting characteristics of an adaptive fuzzy controller. The AFISMC cutting velocity controller is synthesized using the backstepping technique. The stability of the whole system including the fuzzy inference system, integral sliding mode controller, and the cutting system is proven using the Lyapunov theory. Experiments have been conducted on a TC test bench with the AFISMC under different operating conditions. The experimental results demonstrate that the proposed AFISMC cutting velocity controller gives a superior and robust velocity tracking performance. | Qi-yan TIAN Jian-hua WEI Jin-hui FANG Kai GUO | 2016 | Frontiers of Information Technology & Electronic Engineering2016，17，1： | 5 |
| 18 | Attitude control for QTR using exponential nonsingular terminal sliding mode control显示文摘For the problem of attitude control of a quad tilt rotor aircraft with unknown external disturbances, a class of control methods based on a new exponential fast nonsingular terminal sliding surface, a new fast reaching law, and a super twisting sliding mode disturbance observer is investigated. First, the new exponential nonsingular terminal sliding surface is designed by using the advantages of nonsingular terminal sliding mode finite time convergence and strong robustness. Second, to solve the problem of a long convergence time and the serious shaking of the traditional reaching law, a new fast reaching law model with characteristics of the second-order sliding mode is put forward. Third,considering the existence of complex disturbances, the super twisting sliding mode disturbance observer is used to estimate and compensate the composite disturbances online. Finally, compared with the traditional nonsingular fast sliding mode control, simulation results show that the proposed control scheme achieves a good control performance. | LIU Haibo WANG Heping SUN Junlei | 2019 | Journal of Systems Engineering and Electronics2019，30，1： | 5 |
| 19 | Nano-texture of penetrative foliation in metamorphic rocks显示文摘By observing four samples obtained from Jiangxi Province, China, under the scanning electron mi-croscope (SEM), we discovered that nano-particle layers were commonly formed on sliding planes of the penetrative foliation in metamorphic rocks. We also successfully reproduced this phenomenon with a tri-axial pressure experiment. Having gone through the granulitization-alienation-partition in the shear sliding process, the nano-particles (40-95 nm in diameter) display different individual shapes and dis-tinct layered textures. This nano-confinement layer is essentially a frictional-viscous stripe with vis-cous-elastic deformation. In the micro-domain stripe, activities in structural stress field-rheological physical field-geochemical field are very dynamic, corresponding to the three stages (i.e., shear sliding strengthening-weakening-exfoliating) of the foliation development in metamorphism rocks. As such, the viscous-elastic deformation behavior helps shed light on the understanding of the micro-dynamic mechanism of the structural shearing. | SUN Yan LU XianCai ZHANG XiHui LIU Hao LIN AiMing | 2008 | Science China Earth Sciences2008，51，12： | 5 |
| 20 | Application of output feedback sliding mode control to active flutter suppression of two-dimensional airfoil显示文摘The effectiveness of the sliding mode control(SMC) method for active flutter suppression(AFS) and the issues concerning control system discretization and control input constraints were studied using a typical two-dimensional airfoil.The airfoil has a trailing-edge flap for flutter control.The aeroelastic system involves a two-degrees-of-freedom motion(pitch and plunge),and the equations were constructed by utilizing quasi-steady aerodynamic forces.The control system,designed by the output feedback SMC method,was incorporated to suppress the pitch-plunge flutter.Meanwhile,the system discretization and the flap deflection constraints were implemented.Then,a classical Runge-Kutta(RK) algorithm was utilized for numerical calculations.The results indicated that the close-loop system with the SMC system could be stable at a speed above the flutter boundary.However,when the flap deflection limits are reached,the close-loop system with the simple discretized control system loses control.Furthermore,control compensation developed by theoretical analysis was proposed to make the system stable again.The parameter perturbations and the time delay effects were also discussed in this paper. | YANG Chao,SONG Chen,WU ZhiGang & XIE ChangChuan School of Aeronautic Science and Engineering,Beijing University of Aeronautics & Astronautics,Beijing 100191,China | 2010 | Science China(Technological Sciences)2010，53，5： | 5 |
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