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ACTIVE control OF FAN NOISE FROM A TURBOFAN ENGINE

AIAA JOURNAL 1994年第1期32卷 23-30页

作者： THOMAS, RH BURDISSO, RA FULLER, CR OBRIEN, WF Virginia Polytechnic Institute and State University Blacksburg Virginia 24061

A three-channel active control system is applied to an operational turbofan engine to reduce tonal noise produced by both the fan and the high-pressure compressor. The control approach is the feedforward filtered-x least-mean-square algorithm implemented on a digital signal processing board. Reference transducers mounted on the engine case provide blade passing and harmonics frequency information to the controller. Error information is provided by large area microphones placed in the acoustic far field. To minimize the error signal, the controller actuates loudspeakers mounted on the inlet to produce destructive interference. The sound pressure level of the fundamental tone of the fan was reduced using the three-channel controller by up to 16 dB over a +/- 30-deg angle about the engine axis. A single-channel controller could produce reduction over a +/- 15-deg angle. The experimental results show the control to be robust. Outside of the areas controlled, the levels of the tone actually increased due to the generation of radial modes by the control sources. Simultaneous control of two tones is achieved with parallel controllers. The fundamental and the first harmonic tones of the fan were controlled simultaneously with reductions of 12 and 5 dBA, respectively, measured on the engine axis. Simultaneous control was also demonstrated for the fan fundamental and the high-pressure compressor fundamental tones.

关键词： adaptive control algorithm Turbofan Engines Sound Pressure Level Multiple Input Multiple Output Turbomachines Perceived Noise Level Bypass Ratio Digital Signal Processing control algorithm Anechoic Chambers

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Design of a robust adaptive longitudinal flight control

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第2期23卷 325-331页

作者： Dillon, CH Speyer, JL Univ Calif Los Angeles Sch Engn & Appl Sci Dept Aerosp & Mech Engn Los Angeles CA 90095 USA

A recently developed adaptive controller based on a disturbance attenuation problem is applied here to the longitudinal dynamics of the F-18 high angle-of-attack research vehicle. For commanded change in angle of attack, the controller blends aerodynamic controls with thrust vectoring. The blending is based on the uncertainty of the aerodynamic control moment coefficient vs the restriction on thrust vectoring using paddles. The development of a controller for this complex control problem is based an an adaptive controller determined from solving, without any approximation, the disturbance attenuation problem, where the control coefficient matrix is uncertain. This controller estimates online not only the system state but also the uncertain parameters in the control coefficient matrix. The control is determined by maximizing a nonconcave function with respect to the uncertain parameters and is a function of the disturbance attenuation bound. In linear simulations, it is shown that as the bound is decreased, the transient response is significantly quickened, the thrust vectoring is used more heavily during the transient, and the steady state is achieved with only aerodynamic control.

关键词： Thrust Vector control Angle of Attack adaptive control algorithm Flight control Elevator Hamilton Jacobi Bellman Equation Power Spectral Density Aeroplane Nonlinear Dynamics Riccati Equations

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Active Vibration control of Helicopter Fuselage with Large Dynamic Modeling Errors

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AIAA JOURNAL 2022年第3期60卷 1895-1908页

作者： Kai, Lang Lina, Shang Pinqi, Xia Nanjing Univ Aeronaut & Astronaut Coll Aerosp Engn Natl Key Lab Rotorcraft Aeromech Nanjing 210016 Peoples R China

Active vibration control is an effective method for vibration control of a helicopter fuselage. However, when there are large dynamic modeling errors of a control system, the effectiveness of active vibration control may decrease, or even the control may diverge by using the existing harmonic control algorithms. Large modeling errors will result in inaccurate frequency response functions in the control system. In this paper, a new frequency response function updating-harmonic identification algorithm and its convergence condition have been proposed for effective active vibration control of a helicopter fuselage with large modeling errors through identifying the frequency response function of the control system in real time. In addition, to improve the accuracy of identifying frequency response function and further improve the effect of active vibration control, a dynamic harmonic control weight matrix algorithm is also proposed in this paper. The active vibration control simulations and experimental validation on a dynamically similar and geometrically scaled structure of a helicopter fuselage verify that the proposed algorithm in this paper can achieve faster speed of convergence and better effect of vibration control when there are large dynamic modeling errors over the existing harmonic control algorithms.

关键词： Vibration control Systems Helicopters Fuselages Stochastic control System control algorithm Frequency Response Functions adaptive control algorithm Vibration Amplitude Accelerometer Optimal control

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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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adaptive neuron detection-based control of single-phase SPV grid integrated system with active filtering

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IET POWER ELECTRONICS 2017年第6期10卷 657-666页

作者： Singh, Yashi Hussain, Ikhlaq Mishra, Sukumar Singh, Bhim IIT Delhi Dept Elect Engn New Delhi 110016 India

This study deals with an adaptive neuron detection-based control technique for single-phase, single-stage solar photovoltaic (SPV) array grid integrated system using a voltage-source converter (VSC). The VSC also provides power quality features such as harmonics mitigation, power factor correction and perturb and observation-based maximum power point tracking for an SPV grid-interfaced system. With this approach, the VSC has the active power flow from the SPV array to the grid and it also performs the non-linear load current harmonic compensation by keeping the grid current almost sinusoidal. On the other hand, in the night mode, if the SPV power is not available, the VSC works as an active power filter for the harmonics elimination and reactive power compensation. This increases the effective utilisation of the VSC. The adaptive neuron detection technique has lesser noise and oscillation in extraction of fundamental component in comparison of conventional adaptive control algorithm. It has also satisfied an IEEE-519 standard of harmonics by improving the quality of power of SPV grid integrated system. The proposed system is modelled and simulated using MATLAB/Simulink and the response of the system under non-linear loads and varying environmental conditions are evaluated experimentally on a prototype developed in the laboratory.

关键词： power harmonic filters active filters power supply quality photovoltaic power systems power generation control power factor correction maximum power point trackers load flow adaptive neuron detection-based control single-phase SPV grid integrated system active filtering single-phase single-stage solar photovoltaic array grid integrated system SPV array grid integrated system voltage-source converter VSC power quality harmonics mitigation power factor correction perturb and observation-based maximum power point tracking active power flow nonlinear load current harmonic compensation harmonics elimination reactive power compensation adaptive neuron detection technique adaptive control algorithm MATLAB Simulink

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Continuous Robust control for Two-Dimensional Airfoils with Leading- and Trailing-Edge Flaps

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JOURNAL OF GUIDANCE control AND DYNAMICS 2012年第2期35卷 510-519页

作者： Wang, Z. Behal, A. Marzocca, P. Univ Cent Florida Dept Elect Engn & Comp Sci Orlando FL 32826 USA Clarkson Univ Dept Elect Engn Comp Sci & NanoSci Technol Ctr Potsdam NY 13699 USA

In this paper, a class of multi-input/multi-output aeroelastic systems with unstructured nonlinear uncerta inty is considered. By using leading- and trailing-edge control surface actuations, a continuous robust controller is proposed to suppress the aeroelastic vibrations of a nonlinear wing-section model with plunging and pitching degrees of freedom. Under a mild restriction that the system uncertainties are second-order differentiable, the control design yields a semiglobal asymptotic stability result, leading to rapid suppression of the plunging and pitching motions. Numerical simulation results demonstrate the performance of the multi-input/multi-output continuous robust control toward suppressing aeroelastic vibration and limit cycle oscillations at pre- and postflutter flight speed regimes, even in the presence of bounded unknown external disturbance.

关键词： adaptive control algorithm Trailing Edge Flap Two Dimensional Airfoil adaptive Output Feedback control Aeroservoelastic Stability Aerodynamic Moments Angle of Attack control algorithm control Surfaces Neural Networks

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RECENT ADVANCES IN ACTIVE NOISE-control

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AIAA JOURNAL 1991年第7期29卷 1058-1067页

作者： STEVENS, JC AHUJA, KK Georgia Institute of Technology Atlanta Georgia 30332

Recent progress in the field of active noise control is reviewed. The advent of the digital computer and subsequent speed and capacity improvements have made active noise control more practical and have encouraged rapid advancement in research. Several surveys of research have been done in the past, so emphasis is placed on the newest and most innovative research. In particular, the advancement of research on active noise control during the decade of the eighties is reviewed.

关键词： Digital Computers adaptive control algorithm adaptive Filter Transformer Aircraft Fuselages Noise Attenuation Propeller Noise Turbulent Flow Sound Pressure Level Internal Combustion Engines

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Rigid-Body Noncertainty Equivalence adaptive control on the Tangent Bundle of SE(3)

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JOURNAL OF GUIDANCE control AND DYNAMICS 2023年第10期46卷 1892-1900页

作者： Seo, Dongeun Nazari, Morad Arabi, Ehsan Embry Riddle Aeronaut Univ Daytona Beach Florida FL 32114 USA Ford Motor Co Dearborn MI 48126 USA

This paper addresses an adaptive rigid-body pose-tracking control problem with unknown system parameters. The proposed control is based on a noncertainty equivalence (NCE) adaptive principle applied to the configuration manifold of rigid-body motion, i.e., special Euclidean group SE(3), and its tangent bundle TSE(3). The controller drives the system to follow an arbitrary reference trajectory with bounded time derivatives. The system states are composed of the elements of SE(3), consisting of rotations and translations, and the six-dimensional vector of angular and translational velocities in Euclidean space. Almost-global-asymptotic stability of the system is demonstrated using a Morse-Lyapunov stability analysis. Then, the performance of the proposed controller is verified and is compared to the results obtained by a certainty-equivalence (CE) adaptive control applied to exponential coordinates associated with the linear space of the Lie algebra se(3). It is shown that the TSE(3)-based NCE adaptive control design can eliminate the performance degradation due to the cancellation of uncertain parameter effects that would otherwise appear when the CE adaptive controller is used. As a result, the proposed NCE-based adaptive pose-tracking controller recovers the closed-loop pose-tracking controller performance with the system parameters fully known to the controller.

关键词： Model Reference adaptive control Numerical Simulation Attitude Dynamics adaptive control algorithm Spacecraft Guidance and control Feedback control Nonlinear control Theory

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Comprehensive Review of Distributed FACTS control algorithms for Power Quality Enhancement in Utility Grid With Renewable Energy Penetration

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IEEE ACCESS 2020年 8卷 107614-107634页

作者： Chawda, Gajendra Singh Shaik, Abdul Gafoor Mahela, Om Prakash Padmanaban, Sanjeevikumar Holm-Nielsen, Jens Bo IIT Jodhpur Dept Elect Engn Jodhpur 342037 Rajasthan India Rajasthan Rajya Vidyut Prasaran Nigam Ltd Power Syst Planning Div Jaipur 302005 Rajasthan India Aalborg Univ Dept Energy Technol DK-6700 Aalborg Denmark

Rapid industrialization and its automation on the globe demands increased generation of electrical energy with more reliability and quality. Renewable energy (RE) sources are considered as a green form of energy and extensively used as an alternative source of energy for conventional energy sources to meet the increased demand for electrical power. However, these sources, when integrated to the utility grid, pose challenges in maintaining the power quality (PQ) and stability of the power system network. This is due to the unpredictable and variable nature of generation by these sources. The distributed flexible AC transmission system (DFACTS) devices such as distributed static compensator (DSTATCOM) and dynamic voltage restorer (DVR) play an active role in mitigating PQ issues associated with RE penetration. The performance of DFACTS devices is mostly dependent on the type of control algorithms employed for switching of these devices. This paper presents a comprehensive review of various conventional and adaptive algorithms used to control DFACTS devices for improvement of power quality in utility grids with RE penetration. This review intends to provide a summary of the design, experimental hardware, performance and feasibility aspects of these algorithms reported in the literature. More than 170 research publications are critically reviewed, classified, and listed for quick reference for the advantage of engineers and academician working in this area.

关键词： adaptive control algorithm conventional control algorithm DFACTS device modern utility grid power quality renewable energy source

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Intelligent Flight control Systems Evaluation for Loss-of-control Recovery and Prevention

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第4期40卷 890-904页

作者： Smaili, M. H. Breeman, J. Lombaerts, T. J. J. Mulder, J. A. Chu, Q. P. Stroosma, O. NLR Netherlands Aerosp Ctr Aerosp Operat Cockpit & Flight Operat POB 90502 NL-1006 BM Amsterdam Netherlands NLR Netherlands Aerosp Ctr Aerospace Syst Aircraft Syst POB 90502 NL-1006 BM Amsterdam Netherlands NASA Ames Res Ctr Mail Stop 269-1 Moffett Field CA 94035 USA Delft Univ Technol Control & Simulat Div Fac Aerosp Engn POB 5058 NL-2600 GB Delft Netherlands

Recent developments in the field of loss-of-control recovery and prevention included improved pilot training, cockpit automation, and fault-tolerant control. The Flight Mechanics Action Group on Fault-Tolerant control of the Group for Aeronautical Research and Technology in Europe demonstrated the advantages of fault-tolerant "intelligent," flight control systems. The research enabled the improvement of the technology readiness level of these systems by evaluating one of them in realistic operational scenarios. The handling qualities results of a piloted flight simulator assessment with a damaged aircraft model showed that an online physical model identification approach contributed to improved pilot performance following potentially catastrophic structural and flight critical system failures. After the failures and subsequent control reconfiguration by the intelligent flight control system, airline and engineering test pilots experienced no difficulties in conducting a safe approach and landing.

关键词： Intelligent Flight control System Test Pilots Handling Qualities Aircraft Configurations adaptive control algorithm Full Flight Simulator Flight Trajectory Technology Readiness Level Fly By Wire control Systems Digital Flight Data Recorder

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