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Investigation of real-time adaptive energy management strategy for a series-parallel hybrid electric bus

INTERNATIONAL JOURNAL OF ELECTRIC AND HYBRID VEHICLES 2016年第3期8卷 195-212页

作者： Lin, Xinyou Zhai, Liuqing Lin, Haibo Fuzhou Univ Fujian Prov Collaborat Innovat Ctr High End Equip Coll Mech Engn & Automat Fuzhou 350000 Peoples R China

To improve fuel economy of a novel series-parallel hybrid electric bus (SPHEB) further, the control rule of battery power distribution is derived from the offline optimisation algorithm based on Pontryagin's minimum principle, internal relationship between the equivalence fuel factor. and trend of state of charge (SOC) with different driving condition is established and calculation model of SOC is formed. On the basis of the above, according to the feature of the city bus driving cycle, the algorithm of adaptive fuzzy sliding-mode control (AFSMC) is introduced to periodically update the equivalence fuel factor, and then the power-balancing adaptive control strategy is developed. To validate the proposed strategy rationality, the hardware in-the-loop integrated with bench test is applied to compare the proposed control strategy with the previous optimal control strategy. The results indicate that the efficiency of SPHEB system is improved by the proposed control strategy.

关键词： city bus hybrid electric powertrain fuel economy energy management battery power distribution adaptive control algorithm Pontryagin's minimum principle the equivalence fuel factor fuzzy sliding-mode control hardware in-the-loop PBACS power-balancing adaptive control strategy

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adaptive QUATERNION FEEDBACK-REGULATION FOR EIGENAXIS ROTATIONS

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JOURNAL OF GUIDANCE control AND DYNAMICS 1994年第6期17卷 1287-1291页

作者： CRISTI, R BURL, J RUSSO, N MICHIGAN TECHNOL UNIV DEPT ELECT ENGNHOUGHTONMI 49931 US COAST GUARD WILDWOODNJ 08260

A controller to rotate a rigid body between two successive orientations is designed. Particular features are the bet that it is based on the quaternion approach, known to provide singularity-free attitude description, and it is adaptive in the sense that it does not need specific knowledge of the inertia matrix. Global stability of the overall controller is proved analytically and tested in computer simulations.

关键词： Quaternions adaptive control algorithm Manned Maneuvering Unit Mechanical Manipulators Euler Angles Nonlinear Systems Space Stations Kalman Filter Space Robotics Attitude control

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adaptive Spacecraft Attitude control Using Single-Gimbal control Moment Gyroscopes Without Singularity Avoidance

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JOURNAL OF GUIDANCE control AND DYNAMICS 2019年第11期42卷 2342-2355页

作者： Zhao, Zhanzhan Cruz, Gerardo Bernstein, Dennis S. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Univ Michigan Ann Arbor MI 48109 USA NASA Goddard Space Flight Ctr Greenbelt MD USA

This paper applies retrospective cost adaptive control (RCAC) to spacecraft attitude control with a rotation-matrix attitude parameterization using constant-speed single-gimbal control moment gyroscopes. Unlike control laws that use torque-steering laws to synthesize torque requests while avoiding gimbal singularities, the adaptive control law requests the rate of each gimbal. Because no torque request is provided, there is no need to invert the mapping from the gimbal rates to the control torque, and thus no attempt is made to avoid gimbal singularities. The RCAC implementation is based on a target model involving a single Markov parameter corresponding to the initial gimbal configuration. The parameters and weights for RCAC are based on nominal-model tuning, which uses no explicit knowledge of the nonlinear equations of motion. This paper investigates the robustness of RCAC to off-nominal conditions of commands, noise, and unknown bus inertia;and it examines the performance of RCAC in the case where an approximately singular gimbal configuration occurs during attitude command, following as well as the case of an initial gimbal-lock singularity. The performance of the adaptive controller in the presence of sensor/actuator misalignment is also investigated.

关键词： Spacecraft Attitude Single Gimbal control Moment Gyroscopes adaptive control algorithm Sensors Steering Law Actuators Retrospective Cost Nonlinear Equation Spacecraft control Numerical Simulation

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adaptive wire diameter control of the high-precision optical fibre drawing machine

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OPTICAL FIBER TECHNOLOGY 2021年 63卷 102462-102462页

作者： Cao, Yang Qian, Yunsheng Zhang, Jiawei Hao, Jinguang Wang, Honggang Yang, Minjie Nanjing Univ Sci & Technol Coll Elect & Opt Engn Nanjing 210094 Peoples R China North Night Vis Technol Co Ltd Nanjing 210094 Peoples R China Ludong Univ Coll Informat & Elect Engn Yantai 264025 Peoples R China

Different from the conventional methods such as the Proportional-Integral-Derivative (PID)-based method, an adaptive control algorithm (ACA) is proposed in this paper to control the wire diameter of high-precision fibre drawing machines (FDMs). A simple FDM model is established to acquire the relationship between fibre diameter and drawing velocity before the ACA is introduced. The comparison simulation of the accuracy of fibre diameter between the proposed ACA and traditional PID is made, and the ACA is applied to actual fibre drawing processes, so as to validate the ACA. The comparative results show that the fluctuation of filament diameter is smaller and the accuracy is higher under the ACA control. In actual fibre filament drawing processes, the ACA can limit the diameter error within ?2?m, which meets the production requirements.

关键词： Fibre drawing machine Wire diameter control adaptive control algorithm PID control

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adaptive AUV Mission control System Tested in the Waters of Baffin Bay

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DRONES 2024年第2期8卷 45-45页

作者： Hwang, Jimin Bose, Neil Millar, Gina Bulger, Craig Nazareth, Ginelle Chen, Xi Mem Univ FEAS St John NF A1B 3X9 Canada Mem Univ Off President & Vice Chancellor St John NF A1C 5S7 Canada Mem Univ Autonomous Ocean Syst Ctr AOSCENT St John NF A1B 3X9 Canada Mem Univ Marine Inst St John NF A1B 3X9 Canada

The primary objectives of this paper are to test an adaptive sampling method for an autonomous underwater vehicle, specifically tailored to track a hydrocarbon plume in the water column. An overview of the simulation of the developed applications within the autonomous system is presented together with the subsequent validation achieved through field trials in an area of natural oil seeps near to Scott Inlet in Baffin Bay. This builds upon our prior published work in methodological development. The method employed involves an integrated backseat drive of the AUV, which processes in situ sensor data in real time, assesses mission status, and determines the next task. The core of the developed system comprises three modular components-Search, Survey, and Sample-each designed for independent and sequential execution. Results from tests in Baffin Bay demonstrate that the backseat drive operating system successfully accomplished mission goals, recovering water samples at depths of 20 m, 50 m, and 200 m before mission completion and vehicle retrieval. The principal conclusion drawn from these trials underscores the system's resilience in enhanced decision autonomy and validates its applicability to marine pollutant assessment and mitigation.

关键词： autonomous underwater vehicle adaptive control algorithm backseat driver modular control system natural oil seeps oil plume detection real-time analysis adaptive sampling

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adaptive Feedforward control for Gust Load Alleviation

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JOURNAL OF GUIDANCE control AND DYNAMICS 2010年第3期33卷 862-872页

作者： Zeng, Jie Moulin, Boris de Callafon, Raymond Brenner, Martin J. ZONA Technol Inc Scottsdale AZ 85258 USA Univ Calif San Diego La Jolla CA 92093 USA NASA Dryden Flight Res Ctr Edwards AFB CA 93523 USA

In this paper, an adaptive feedforward control framework is proposed for the suppression of aircraft structural vibrations induced by gust perturbations to increase the resilience of the flight control law in the presence of the aeroelastic/aeroservoelastic interactions. Currently, aircraft with nonadaptive control laws usually include roll-off or notch filters to avoid aeroelastic/aeroservoelastic interactions. However, if changes in the aircraft configuration are significant, the frequencies of the flexible modes of the aircraft may be shifted, and the notch filters could become totally ineffective. With the proposed approach, the flexible modes can be consistently estimated in real time via a proven system-identification algorithm. The identified flexible modes information is used in the proposed adaptive feedforward control algorithm to adjust the parametrization of the basis functions in a feedforward controller. Along with the recursive least-squares estimate, the feedforward controller is adjusted, and the structural vibration of the aircraft induced by the gust perturbation can be largely suppressed. An F/A-18 active aeroelastic wing aeroelastic model with gust perturbation based on the linear aeroelastic solver formulation is developed as a test bed to demonstrate the proposed adaptive feedforward control algorithm.

关键词： adaptive control algorithm Aerodynamic Force Coefficients Aeroservoelastic Systems Vibration Suppression Aircraft Configurations control algorithm Active Aeroelastic Wing Flight control Law Frequency Response Functions Leading Edge Flap

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adaptive control of Variable Geometry Inlet-Configured Air-Breathing Hypersonic Vehicles

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JOURNAL OF SPACECRAFT AND ROCKETS 2019年第5期56卷 1520-1530页

作者： An, Hao Wu, Qianqian Harbin Inst Technol Space Control & Inertial Technol Res Ctr 2 Yikuang St Harbin 150001 Heilongjiang Peoples R China Harbin Inst Technol Ctr Composite Mat & Struct 2 Yikuang St Harbin 150001 Heilongjiang Peoples R China

This paper studies the longitudinal fault-tolerant control problem for a class of variable geometry inlet-configured air-breathing hypersonic vehicles, whose inlet length varies dynamically to ensure an efficient scramjet thrust. After lumping the effects of uncertain parameters, external disturbances, flexible dynamics, actuator faults, and variable inlet into the linearly parameterized form, a parameterized control-oriented model (PCOM) is derived for design purpose. To handle the time-varying uncertain parameter vectors involved in the PCOM, a novel bound estimation method is developed, while greatly reducing the required parameter update laws. In the adaptive back-stepping design for altitude subsystem, the command filter technique is implemented to circumvent the analytical derivative calculations of virtual controls that are unmanageable by a standard back-stepping procedure because of the time-varying uncertain factors in the PCOM. The corresponding tracking errors are regulated into adjustable residual sets. A simulation study is implemented to verify the developed controller.

关键词： Hypersonic Vehicles adaptive control algorithm Actuators Scramjet Aerodynamic Coefficients Finite Element Modeling Hypersonic Flight Flight Path Angle Elevator Deflection Airframes

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Closed-Loop control of a Piezo-Fluidic Amplifier

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AIAA JOURNAL 2020年第6期58卷 2414-2427页

作者： Nicholls, Chris Bacic, Marko Univ Oxford Oxford Thermofluids Inst Oxford OX2 0ES England Rolls Royce PLC London England

Fluidic valves based on the Coanda effect are increasingly being considered for use in aerodynamic flow control applications. A limiting factor is their variation in switching time, which often precludes their use. The purpose of this paper was to demonstrate the closed-loop control of a recently developed novel piezo-fluidic valve that reduces response time uncertainty at the expense of operating bandwidth. Use is made of the fact that a fluidic jet responds to a piezo tone by deflecting away from its steady-state position. A control signal used to vary this deflection is amplitude modulated onto the piezo tone. Using only a pressure measurement from one of the device output channels, an output-based linear quadratic Gaussian regulator was designed to follow a desired reference deflection, achieving control of a 90 m.s(-1) jet. Finally, the controller's performance in terms of disturbance rejection and response time predictability is demonstrated.

关键词： adaptive control algorithm Coanda Effect Linear Quadratic Gaussian Aerodynamic Flows Power Spectral Density Shear Layers Mass Flow Rate Piezoelectric Transducers Dynamic Response Extended Kalman Filter

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Robust Adaptation in Dynamically Switching Load Frequency control ⁎

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IFAC-PapersOnLine 2020年第2期53卷 13460-13465页

作者： Tian Tao Spandan Roy Shuai Yuan Simone Baldi Delft Center for Systems and Control TU Delft The Netherlands Robotics Research Centre International Institute of Information Technology Hyderabad India School of Astronautics Harbin Institute of Technology China School of Mathematics Southeast University Nanjing China School of Cyber Science and Engineering Southeast University Nanjing China

In recent years, heuristics for adaptive solutions to load frequency control (LFC) in power systems have been proposed that include adapting the LFC targets or adapting the participation factor for the resources. However, stability guarantees for these adaptation ideas are missing, especially in the presence of switching/evolving topologies of the power system. In today’s smart grids, switching topologies often arise from reconfiguration and resilience against faults or from switching among different control areas in order to dampen oscillations and face cyber attacks. This work proposes a novel LFC framework in which adaptation and switching topologies are combined in a provably stable way.

关键词： Power systems load frequency control adaptive control algorithm grid resilience switching evolving topologies

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Output Feedback adaptive control of Plants with Unmodeled Dynamics and Input Uncertainties

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JOURNAL OF GUIDANCE control AND DYNAMICS 2019年第10期42卷 2143-2156页

作者： Chandramohan, Rajeev Calise, Anthony J. Gulfstream Aerosp 500 Gulfstream Rd Savannah GA 31408 USA Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA

An approach for designing an adaptive output feedback controller for uncertain systems with unmodeled dynamics and plant input uncertainty is developed. The adaptive control augments an assumed existing observer-based linear controller. The main advantages of the method are that it can be used to augment an existing linear controller without modifying the parameters of that controller, and it does not rely on the use of high gains: neither in the observer nor in the adaptation law. It is applicable to nonminimum phase systems and does not require realization of a reference model. Attitude control of a flexible spacecraft is used to illustrate effectiveness of the approach. Issues related to uncertainty in the actuation effectiveness and sensor noise are also treated.

关键词： adaptive Output Feedback control adaptive control algorithm Flexible Spacecrafts Sensors Attitude control Riccati Equations Neural Networks Nonlinear Systems Quaternions Algebraic Riccati Equation

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