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active Flutter Suppression: Quantification of Performance Loss Due to Actuator Saturation

JOURNAL OF GUIDANCE control AND DYNAMICS 2024年第11期47卷 2333-2350页

作者： Micheli, Boris German Aerosp Ctr DLR Inst Aeroelast Dept Aeroelast Simulat Bunsenstr 10 D-37073 Gottingen Germany

active flutter suppression technologies have the potential to lead to major weight savings while keeping the envisaged flight envelope for the future generation of commercial aircraft. Since the stabilization of aeroelastic systems undergoing flutter instabilities is strongly affected by actuators' characteristics and delays in the closed loop, the degradation of closed-loop performance due to actuators' nonlinearities must be thoroughly understood. Comparisons between the region of attraction and the controllable region can support the quantification of performance loss due to common actuators' nonlinearities, such as amplitude and rate limits. At first, this paper illustrates a numerically robust algorithm for the full characterization of the controllable region of a generic unstable system under input amplitude and rate constraints. Secondly, the concept of region of attraction is expanded to assess the boundedness of the closed-loop response in the presence of input saturation and atmospheric disturbances. These concepts are here employed to define two nonlinear performance measures that quantify the performance loss due to actuators' saturation in an unstable aeroelastic system stabilized by a flutter suppression controller. The approach is demonstrated on a realistic aeroelastic system for which different H2 and H infinity output feedback controllers are synthesized to augment the damping of the critical flutter mode.

关键词： Electro Hydraulic Actuator Linear Time Invariant Aeroservoelastic Systems Full State Feedback Commercial Aircraft Dynamic Pressure benchmark active control technology Aeroservoelasticity Flutter Suppression System Robust control

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Predictive Cost Adaptive control of the BACT Flutter Model

Predictive Cost Adaptive Control of the BACT Flutter Model

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AIAA SciTech Forum

作者： Richards, Riley J. Islam, S. A. U. Bernstein, Dennis S. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper provides a numerical investigation of the performance of predictive cost adaptive control (PCAC) of the NASA BACT flutter model. PCAC is an indirect adaptive control extension of model predictive control that includes online closed-loop system identification. System identification is based on recursive least squares with variable-rate forgetting based on the F-test. PCAC is applied to the BACT flutter model, and the ability of PCAC to extend the flutter boundary using minimal prior modeling of the aeroelastic dynamics is investigated through detailed and systematic numerical simulations.

关键词： benchmark active control technology Closed Loop System Identification NASA Numerical Simulation Airspeed Aerodynamic Damping Accelerometer Angle of Attack Inertial Coupling Turbulence Models

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Composite Adaptive Aeroelastic System control and Multifold Regressor Integrals-based Identification

Composite Adaptive Aeroelastic System Control and Multifold ...

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AIAA Aviation Forum

作者： Lee, Keum W. Rajt, Kaushik Singh, Sahjendra N. Catholic Kwandong Univ Dept Elect Engn Gangwon 25601 South Korea Univ Nevada Las Vegas Dept Elect & Comp Engn Las Vegas NV 89154 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The paper presents a composite adaptive control system for the stabilization and parameter estimation of a multi-input multi-output two degree of freedom aeroelastic system equipped with leading- and trailing-edge control surfaces. The model describes the pitch and plunge motion of a prototypical wing section. The control law consists of a control module and a composite identifier. The novelty of the identifier lies in inclusion of multifold regressor matrix integrals for parameter estimation. Based on the Lyapunov stability analysis, asymptotic convergence of state vector to zero is established. The adaptive system achieves parameter error convergence if a mild initially exciting (IE) condition is satisfied. Interestingly, for the choice of..-fold regressor matrix integral, the trajectories of the system converge to (.. + 1) parameter error-dependent manifolds in an extended state space. Simulation results show the suppression of limit cycle oscillations as well as parameter estimation despite wind gust, and unmodeled actuator dynamics. Furthermore, the results show that parameter error converges faster as the number of regressor integrals increases in the adaptation law.

关键词： Aeroelastic Modeling Closed Loop control Flap Deflection Actuators benchmark active control technology control Surfaces Free Stream Velocity Structural Dynamics Wind Tunnel Models Neural Networks

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Data-Driven Retrospective Cost Adaptive control for Flight control Applications

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JOURNAL OF GUIDANCE control AND DYNAMICS 2021年第10期44卷 1732-1758页

作者： Ul Islam, Syed Aseem Nguyen, Tam W. Kolmanovsky, Ilya, V Bernstein, Dennis S. Univ Michigan Aerosp Engn 1320 Beal Ave Ann Arbor MI 48109 USA

Unlike fixed-gain robust control, which trades off performance with modeling uncertainty, direct adaptive control uses partial modeling information for online tuning. The present paper combines retrospective cost adaptive control (RCAC), a direct adaptive control technique for sampled-data systems, with online system identification based on recursive least squares (RLS) with variable-rate forgetting (VRF). The combination of RCAC and RLS-VRF constitutes data-driven RCAC (DDRCAC), where the online system identification is used to construct the target model, which defines the retrospective performance variable. This paper investigates the ability of RLS-VRF to provide the modeling information needed for the target model, especially non-minimum-phase (NMP) zeros. DDRCAC is applied to single-input, single-output and multiple-input, multiple-output numerical examples with unknown NMP zeros, as well as several flight control problems, namely, unknown transition from minimum phase to NMP lateral dynamics, flexible modes, flutter, and nonlinear planar missile dynamics.

关键词： Retrospective Cost Flight control Closed Loop System Identification benchmark active control technology Sampled Data Systems Missile Dynamics Linear Quadratic Gaussian Gaussian White Noise Elevator Deflection Aerodynamic Coefficients

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Discrete Time State Space Modeling for Gust Aerodynamics with Component Load Monitoring

Discrete Time State Space Modeling for Gust Aerodynamics wit...

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AIAA Science and technology Forum and Exposition (AIAA SciTech Forum)

作者： Wang, Z. Sarhaddi, D. Chen, P. C. ZONA Technol Inc Scottsdale AZ 85258 USA

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

In this paper, we extend our previous work on the discrete time state space aeroelastic modeling technique using FUN3D further for the gust analysis. We have utilized a subspace realization algorithm to identify the individual aerodynamic sub-systems, i.e., due to the structural deformations (modal coordinates), control surface deflections, respectively. The dataset needed for the aerodynamic system identifications are obtained by a wrapper program, called OVERFUN, driving the underlying FUN3D solver. In current work, a generalized table format gust input is implemented for FUN3D so that the random gust profile can be utilized. Efficiency of the table look up algorithm for the computation of gust velocity at each CFD grid is carefully addressed. The sectional/component loads are included as a part of the system outputs in addition to the generalized aerodynamic forces during the aerodynamic sub-system identification, thus the final assembled aeroelastic state space model is enabled with component load monitoring capability. A normalization and denormalization procedure is implemented to the system identification algorithm to circumvent potential numerical issues associated with the different levels of amplitudes of the system inputs/outputs. Numerical results for the Goland wing configuration at two Mach numbers 0.85 and 0.94 are presented both without and with the inclusion of component loads to demonstrate the success of the presented methodology.

关键词： Aerodynamic Stability FUN3D System Identification State Space Aeroelastic Models Wing Configurations Structural Modeling Structural Finite Elements Trailing Edge Flap benchmark active control technology Navier Stokes Solver

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Experimental Nonlinear control for Flutter Suppression in a Nonlinear Aeroelastic System

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第8期40卷 1925-1938页

作者： Jiffri, Shakir Fichera, Sebastiano Mottershead, John E. Da Ronch, Andrea Univ Liverpool Dept Mech Mat & Aerosp Engn Sch Engn Brownlow Hill Liverpool L69 3GH Merseyside England Univ Liverpool Appl Mech Brownlow Hill Liverpool L69 3GH Merseyside England Univ Liverpool Inst Risk & Uncertainty Brownlow Hill Liverpool L69 3GH Merseyside England Univ Southampton Fac Engn & Environm Univ Rd Southampton SO17 1BJ Hants England

Experimental implementation of input-output feedback linearization in controlling the dynamics of a nonlinear pitch-plunge aeroelastic system is presented. The control objective is to linearize the system dynamics and assign the poles of the pitch mode of the resulting linear system. The implementation 1)addresses experimentally the general case where feedback linearization-based control is applied using as the output a degree of freedom other than that where the physical nonlinearity is located, using a single trailing-edge control surface, to stabilize the entire system;2)includes the unsteady effects of the airfoil's aerodynamic behavior;3)includes the embedding of a tuned numerical model of the aeroelastic system into the control scheme in real time;and 4)uses pole placement as the linear control objective, providing the user with flexibility in determining the nature of the controlled response. When implemented experimentally, the controller is capable of not only delaying the onset of limit-cycle oscillation but also successfully eliminating a previously established limit-cycle oscillation. The assignment of higher levels of damping results in notable reductions in limit-cycle oscillation decay times in the closed-loop response, indicating good controllability of the aeroelastic system and effectiveness of the pole-placement objective. The closed-loop response is further improved by incorporating adaptation so that assumed system parameters are updated with time. The use of an optimum adaptation parameter results in reduced response decay times.

关键词： Nonlinear Aeroelastic Systems Nonlinear control Numerical Integration Linear Time Invariant System Feedback Linearization Flap Deflection Aerodynamic Loads Airspeed benchmark active control technology Damping Coefficient

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Design of an active Disturbance Rejection control for Transonic Flutter Suppression

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第11期40卷 2905-2916页

作者： Yang, Zhijun Huang, Rui Zhao, Yonghui Hu, Haiyan Nanjing Univ Aeronaut & Astronaut State Key Lab Mech & Control Mech Struct Inst Vibrat Engn Res Nanjing 210016 Jiangsu Peoples R China

Conventional controls, such as an optimal control with a notch filter, are able to remove the flutter instability under subsonic flows but may need higher adaptability to make the controllers stable under transonic flows with oscillating shocks, especially for the wing model with parameter uncertainties. In this paper, an error-based control law designed via the active disturbance rejection control algorithm is proposed for the transonic flutter suppression of a wing model with parameter uncertainties and measurement noises taken into account. With the proposed control law, the observed output signal and its time derivative, the unmodeled dynamics, and the measurement noises are consistently estimated. The observed output signal and its time derivative are used to design a feedback control law for adjusting the output errors, whereas the observed unmodeled dynamics and the measurement noises are used to guarantee the adaptability and anti-interference of the proposed controller. To demonstrate the control performances, the wing of benchmark active control technology is studied for the transonic flutter suppression. The numerical results show that the present control law can effectively suppress the transonic flutter at a wide range of Mach numbers and has noticeable adaptability to the variation in stiffness parameters.

关键词： active Disturbance Rejection control benchmark active control technology Aerodynamic Force Feedback control Linear Quadratic Gaussian Transonic Flow Numerical Simulation Reynolds Averaged Navier Stokes Mathematical Models Aeroelastic Response

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Flutter Suppression for Underactuated Aeroelastic Wing Section: Nonlinear Gain-Scheduling Approach

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第8期40卷 2102-2109页

作者： Lhachemi, H. Chu, Y. Saussie, D. Zhu, G. Ecole Polytech Montreal Dept Elect Engn Montreal PQ H3T 1J4 Canada

Presented as Paper 2017-1735 at the AIAA Guidance, Navigation, and control Conference, Grapevine, TX, 9-13 January 2017

Presented as Paper 2017-1735 at the AIAA Guidance, Navigation, and control Conference, Grapevine, TX, 9-13 January 2017

关键词： Distributed Parameter System benchmark active control technology Aerodynamic Configurations Feedback Linearization Angle of Attack Flutter Suppression System Damping Coefficient Aircraft Structures Flexible Structures Transonic Wind Tunnel

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Wind-Tunnel Tests for active Flutter control and Closed-Loop Flutter Identification

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AIAA JOURNAL 2016年第7期54卷 2089-2099页

作者： Huang, Rui Zhao, Yonghui Hu, Haiyan Nanjing Univ Aeronaut & Astronaut Inst Vibrat Engn Res State Key Lab Mech & Control Mech Struct Nanjing 210016 Jiangsu Peoples R China

In this study, active flutter control and closed-loop flutter identification were experimentally studied for a low-aspect-ratio wing model in an Nanhang-2 subsonic wind tunnel. To actively suppress the flutter of the wing model in wind-tunnel tests, a real-time digital control system was developed so as to complete the data acquisition, digital signal processing, computation of the control strategy, and servo control of the actuator. Using the digital control system, wind-tunnel tests were conducted to examine the flutter control of the wing model. The experimental results showed that the linear feedback controller designed via the optimization of pole assignment can effectively suppress the flutter instability. Moreover, for the high-dimensional aeroservoelastic system, the online estimation of closed-loop flutter modes is a challenging problem because the flutter identification from closed-loop measurements may lead to biased estimates, and the identification efficiency must be improved. Therefore, as the second task of this study, the online closed-loop flutter identification of the wing model was explored. To efficiently identify the flutter modes, a fast recursive subspace identification method was used. The experimental results show that the natural frequencies and modal damping ratios of the closed-loop flutter modes could be accurately tracked over a wide range of flow speeds.

关键词： Wind Tunnel Models Routh Hurwitz Stability Criterion Harmonic Excitation Aeroservoelastic Systems Actuators Data Acquisition benchmark active control technology Low Aspect Ratio Wings Digital Signal Processing Aerodynamic Force

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Output Regulation with Actuator Saturation for the benchmark active control technology Model

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JOURNAL OF GUIDANCE control AND DYNAMICS 2010年第6期33卷 1951-1966页

作者： Applebaum, Ellen Adin, Zvi J. Ben-Asher, Joseph Z. Technion Israel Inst Technol Fac Aerosp Engn IL-32000 Haifa Israel

A study was conducted to address the problem of output regulation of the continuous-time linear benchmark active control technology (BACT) model with control saturation and exogenous input additive disturbance. The BACT wind-tunnel aeroservoelastic (ASE) model was developed by NASA Langley Research Center that exhibited classical flutter instability at transonic speeds, with system dynamics that varied with the dynamic pressure. The study proposed an alternative strategy and methodology to that of sliding mode control for achieving output regulation of a linear system with actuator saturation and exogenous disturbances. The proposed method was also based upon the construction of invariant sets for maximizing domains of attraction and achieving continuous control action in small invariant neighborhoods of the equilibrium point.

关键词： benchmark active control technology Actuators Gain Scheduled control Feedback control Dynamic Pressure Numerical Simulation Algebraic Riccati Equation Resonance Frequencies Dynamic Response Hinge Moment

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