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Power quality control through automated demand side management in microgrid equipped with battery energy storage for protection

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IET GENERATION TRANSMISSION & DISTRIBUTION 2020年第12期14卷 2389-2398页

作者： Kaushal, Jitender Basak, Prasenjit Thapar Inst Engn & Technol Elect & Instrumentat Engn Dept Patiala Punjab India

Apparently, battery energy storage (BES), intelligent protection and power quality are considered as independent issues. These three factors can be interlinked effectively for control of microgrid through automated demand side management (ADSM). In this context, the proposed approach may change the conventional way for microgrid operation and control giving priority to the power quality issues considering protection and BES systems. The control algorithm is implemented through fuzzy inference system based power quality monitoring index and ADSM. As a part of intelligent protection, logic table for circuit breaker (CB) coordination has been developed without/with backup for relay devices to provide ADSM. The model has been simulated using Matlab-software and validated experimentally using OPAL-RT OP4510 real-time simulator through the assessment of power quality-related parameters such as voltage, frequency, total harmonic distortion and power factor. The results are found satisfactory showing the feasibility of the proposed microgrid model.

关键词： power supply quality harmonic distortion quality control battery storage plants distributed power generation power generation control demand side management microgrid model power factor total harmonic distortion power quality-related parameters circuit breaker coordination fuzzy inference system based power quality monitoring index control algorithm BES systems power quality issues microgrid operation ADSM intelligent protection battery energy storage automated demand side management power quality control

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Switching frequency reduction technique for DSVM-based predictive torque control of induction motor

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IET ELECTRIC POWER APPLICATIONS 2020年第8期14卷 1370-1380页

作者： Amiri, Mohamad Khaburi, Davood A. MiliMonfared, Jafar Khosravi, Mahyar Rodriguez, Jose Iran Univ Sci & Technol IUST Elect Engn Dept Tehran Iran Amirkabir Univ Technol Elect Engn Dept Tehran Iran Univ Andres Bello Fac Engn Santiago Chile

This study proposes a new strategy to decrease the switching frequency of the predictive torque control-discrete space vector modulation (PTC-DSVM) method, which is a combination of the PTC scheme and the DSVM. The principle of the PTC-DSVM method is based on selecting a sequence of voltage vectors, called virtual voltage vectors, instead of a single voltage vector and applying it to the power converter in prefixed time intervals. The proposed switching frequency reduction method operates based on appropriately arranging the voltage vectors forming the virtual voltage vector so that, on average, a maximum of one commutation per inverter switching state change is achieved. As a result of the suggested method, the average switching frequency is reduced in all operating conditions, while the performance of the proposed method remains as satisfactory as the conventional approach. The reduction of switching frequency also results in a decrease in the switching losses. The proposed method is an offline approach and selects the appropriate application order for the real voltage vectors based on the described rules, which do not impose any further computational load to the control algorithm. In order to validate the proposed method performance, the control algorithm has been implemented on a laboratory prototype.

关键词： machine control predictive control torque control switching convertors machine vector control invertors induction motors frequency reduction technique DSVM-based predictive torque control predictive torque control-discrete space vector modulation PTC scheme PTC-DSVM method called virtual voltage vectors single voltage vector switching frequency reduction method virtual voltage vector inverter switching state change average switching frequency switching losses control algorithm

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Indirect robust adaptive fault-tolerant control for attitude tracking of spacecraft

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JOURNAL OF GUIDANCE control AND DYNAMICS 2008年第5期31卷 1456-1463页

作者： Cai, Wenchuan Liao, X. H. Song, Y. D. N Carolina Agr & Tech State Univ Ctr Cooperat Syst Greensboro NC 27411 USA Volvo N Amer Inc Greensboro NC 27455 USA N Carolina Agr & Tech State Univ Dept Elect & Comp Engn Greensboro NC 27411 USA Natl Inst Aerosp Hampton VA 23666 USA

Reliable and cost-effective control of spacecraft should account for modeling uncertainties, unexpected disturbances,, subsystem failures, and limited resources simultaneously. This paper presents an indirect (nonregressor-based) approach to attitude tracking control of spacecraft. It is shown that the control algorithms developed are not only robust against external disturbances and adaptive to unknown and time-varying mass/inertia properties, but also able to accommodate actuator failures under limited thrusts. All are achieved with inexpensive online computations (a feature of practical importance in reducing the usage of onboard resources in terms of computing power and memory size). Furthermore, this method is user/designer friendly in that it does not involve a time-consuming design procedure and demands little redesigning or reprogramming during vehicle operation. The benefits of the proposed control method are analytically authenticated and also validated via simulation study.

关键词： Attitude Tracking Rigid Spacecraft Actuators control algorithm Onboard Computing Attitude Dynamics Adaptive control algorithm Variable Structure control Quaternions Numerical Simulation

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Bearing-only circumnavigation control of the multi-agent system around a moving target

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IET control THEORY AND APPLICATIONS 2019年第17期13卷 2747-2757页

作者： Yu, Yangguang Li, Zhongkui Wang, Xiangke Shen, Lincheng Natl Univ Def Technol Coll Mechatron & Automat Changsha 410073 Hunan Peoples R China Peking Univ Coll Engn Dept Mech & Aerosp Engn State Key Lab Turbulence & Complex Syst Beijing 100871 Peoples R China

The bearing-based coordinated circumnavigation control for networked multi-agent systems with only bearing measurements in the presence of moving target is studied. First, a distributed algorithm is proposed to estimate the target's velocity and the distances between the agents and the target, based on the velocity and the bearing information of the local network. Then, a distributed circumnavigation algorithm is designed to drive the agents to circumnavigate around a moving target at a desired distance. The stability of the proposed control algorithm is proven by employing the newly developed bearing rigidity theory. Finally, the simulation experiment is performed based on the Gazebo simulator to illustrate the effectiveness of the proposed circumnavigation control law.

关键词： mobile robots aerospace control multi-robot systems multi-agent systems control engineering computing numerical analysis mathematical analysis motion control space vehicles bearing-only multiagent system moving target bearing-based networked multiagent systems bearing measurements distributed algorithm bearing information local network distributed circumnavigation algorithm control algorithm circumnavigation control law

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Sensorless control of an H-bridge inverter with output inductor-capacitor filter

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IET POWER ELECTRONICS 2018年第10期11卷 1621-1627页

作者： Mohebbi, Mohammad McIntyre, Michael L. Latham, Joseph Univ Louisville Elect & Comp Engn Dept Louisville KY 40292 USA

This study presents a filter-based control scheme for an H-bridge inverter with an output inductor-capacitor filter. This approach relies only on a single output voltage measurement to reduce the system cost as well as measurement noise and disturbance injected by output current and/or inductor current measurements. Also, the proposed control algorithm is robust against parameter discrepancy. A Lyapunov stability analysis is performed to demonstrate the control objective is met and that all signals in the closed loop system are stable. Experimental results demonstrate excellent voltage tracking, insensitivity to the load and system parameter variations, and low output voltage distortion as well as the stability of the system under both linear and non-linear loads.

关键词： closed loop systems stability Lyapunov methods inductors invertors voltage measurement capacitors H-bridge inverter output inductor-capacitor filter single output voltage measurement measurement noise inductor current measurements control algorithm low output voltage distortion sensorless control filter-based control scheme Lyapunov stability analysis closed loop system

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MISSION FUNCTION control FOR A SLEW MANEUVER EXPERIMENT

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JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第5期14卷 986-992页

作者： FUJII, H OHTSUKA, T UDOU, S Tokyo Metropolitan Institute of Technology Tokyo 191 Japan

A control algorithm named mission function control is experimentally demonstrated and verified on a slew maneuver of a flexible space structure model. The mission function control algorithm employs a Lyapunov-type function that consists of generalized energy functions. The model consists of a rigid body having a cantilevered flexible appendage;it is controlled to slew in a horizontal plane by a torque motor. Analytical study indicates that vibrational motion of the flexible appendage can be sensed by strain gauges as a bending moment and shear force at the root of the appendage. Results of the experiment show that a simple implementation of the algorithm leads to excellent controlled behavior of the slew maneuver as well as excellent control robustness.

关键词： control algorithm Bernoulli Euler Beams Torque Motors Large Space Structures Strain Gauge Distributed Parameter System Numerical Simulation Bang Bang control Flexible Structures Space Environment

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Fault-Tolerant Reduced-Attitude control for Spacecraft Constrained Boresight Reorientation

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JOURNAL OF GUIDANCE control AND DYNAMICS 2022年第8期45卷 1481-1495页

作者： Shao, Xiaodong Hu, Qinglei Zhu, Zheng H. Zhang, Youmin Beihang Univ Sch Aeronaut Sci & Engn Beijing 100191 Peoples R China Beihang Univ Sch Automat Sci & Elect Engn Beijing 100191 Peoples R China York Univ Dept Mech Engn Toronto ON M3J 1P3 Canada Concordia Univ Dept Mech Ind & Aerosp Engn Montreal PQ H3G 1M8 Canada

This paper is devoted to investigating the fault-tolerant reduced-attitude control problem for boresight reorientation of an uncertain spacecraft subject to pointing and angular velocity constraints. First, the stereographic projection is used to transform this problem to an obstacle avoidance problem on a two-dimensional Euclidean sphere world with circular obstacles. Then, an adaptive fault-tolerant control strategy is proposed to solve the transformed problem, by designing two potential functions for constraint handling in conjunction with a sliding vector containing hyperbolic tangent functions. Stability analysis shows that the derived controller can achieve asymptotic convergence of the gradient of the obstacle avoidance potential and angular velocities, while ensuring the satisfaction of both pointing and angular velocity constraints, despite the presence of unknown time-varying inertia parameters, disturbances, and actuator faults. In particular, benefiting from incorporating the spacecraft principal moments of inertia into the potential field design, the risk of the system losing strong controllability under multiplicative actuator faults is greatly reduced. To accommodate actuator faults under input saturation, the adaptive fault-tolerant controller is further extended to a saturated counterpart, which is capable of making full use of the remaining actuation power to react to actuator faults. Finally, simulation results are presented to demonstrate our theoretical findings.

关键词： Spacecrafts control Moment Gyroscope Backstepping control Actuators Telescopes Hubble Space Telescope control algorithm Spacecraft Attitude Fault Tolerance Variable Structure control

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control FOR THE NEW HARSH SEA CONDITIONS SALVAGE CRANE BASED ON MODIFIED FUZZY PID

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ASIAN JOURNAL OF control 2018年第4期20卷 1582-1594页

作者： Liu, Xiangyong Li, Wanli Wang, Wenjia Xu, Zhiqiang Tongji Univ Sch Mech Engn Dept Mech Engn Shanghai 201804 Peoples R China Minist Agr Key Lab Fishery Equipment & Engn Shanghai 200092 Peoples R China

The new salvage crane for harsh sea conditions is a salvage and rescue device that is used for the space launch capsule. The wave compensation algorithm can improve search and rescue ability at sea, and can also provide wave compensation guidance for other sea vessels under harsh sea conditions. Firstly, compared with the traditional fuzzy PID algorithm, the wave compensation algorithm is improved in three aspects: fuzzy rules, fuzzy inputs, and fuzzy outputs. For the fuzzy rules, E and EC are used separately. E plays a main role and EC plays an auxiliary role. For the fuzzy inputs, the angle deviation is the sum of current angle and angle's changing rate. For the fuzzy outputs, the cylinder's inertia and the electro-hydraulic valve's reverse dead zone factors are taken into account, and the PID output value is set with upper limit, lower limit, and dead zone. Secondly, the control valve and the hydraulic system's model are established in AMESim. The improved algorithm is established in SIMULINK. Combining the hydraulic model with the algorithm model, we do the co-simulation analysis. Thirdly, the improved algorithm's verification experiments are carried out on a rocky platform, which can simulate the ship's instability in different sea conditions. Finally, the simulation and experimental results verify that the improved fuzzy PID algorithm enhances the salvage crane's response and robustness, and also improves the salvage effect.

关键词： Harsh sea condition Salvage crane Wave compensation control algorithm

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Factors affecting the control of unstable combustors

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JOURNAL OF PROPULSION AND POWER 2003年第5期19卷 811-821页

作者： Cohen, JM Banaszuk, A Pratt & Whitney E Hartford CT 06108 USA United Technol Res Ctr Pratt & Whitney Program Off E Hartford CT 06108 USA

Active control systems for the attenuation of pressure oscillations in unstable combustors have been under development by a wide variety of investigators. Whereas many of these applications have been in simplified, bench-scale combustors, some significant efforts have been made in realistic systems including full-scale gas turbine engines. Results from these efforts, although generally positive, have been varied. As the technology has matured, the understanding of the factors that currently limit its capability has improved. Some of these factors and how they may be quantified through experiments, models, or combined approaches are addressed. The application focus was lean, premixed combustors for industrial gas turbines. Both gas- and liquid-fueled systems were considered. In particular, the effects of actuation system time delay and actuated fuel mixing are examined, and the fundamental limits of control in systems with time delay are considered. The results indicate that the mixing of the actuated fuel with the remainder of the premixed reactants is significant in determining control authority. The effects of system time delays are shown to result in a peak splitting phenomenon, which limits the degree to which pressure oscillations can be reduced. A further examination of the fundamental limits of control demonstrates that it is not possible to arbitrarily decrease the level of pressure oscillations using linear controllers. The factors that limit the achievable reduction level are the time delay, the combustor damping, and the actuator bandwidth.

关键词： Combustor Design control System Design Nonlinear Actuators Diesel Fuel Gas Turbine Engines Open Loop Transfer Function Fuel Injection Power Spectral Density Combustion Instability control algorithm

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Multiple-model adaptive flight control scheme for accommodation of actuator failures

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JOURNAL OF GUIDANCE control AND DYNAMICS 2002年第4期25卷 712-724页

作者： Boskovic, JD Mehra, RK Sci Syst Co Inc Intelligent & Autonomous Control Syst Woburn MA 01801 USA

A new parameterization for the modeling of control effector failures in flight control applications and a stable adaptive scheme for failure detection, identification, and accommodation is proposed. The failures include lock in place, hard over, and loss of effectiveness. It is shown that the resulting representation leads naturally to a multiple-model formulation of the corresponding control problem that can be solved using a multiple-model adaptive reconfigurable control approach. We derive stable multiple-model adaptive reconfigurable control algorithms for several cases of increasing complexity, including the most complex case, wherein one of the effectors undergoes lock-in-place or hard-over failure, and all others lose effectiveness. In all cases, the stability of the overall reconfigurable control system is demonstrated using multiple Lyapunov functions, extensions of the Lyapunov method, and the separation between identification and control arising in the context of indirect adaptive control. The approach is illustrated through numerical simulations of the F/A-18 aircraft during carrier landing.

关键词： Linear Actuator Adaptive control algorithm control algorithm control Systems Flight control Numerical Simulation Ailerons Stabilator Full State Feedback Aircraft Dynamics

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