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

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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Envelope-Aware Flight Management for Loss of control Prevention Given Rudder Jam

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第4期40卷 1027-1041页

作者： Di Donato, Pedro F. A. Balachandran, Sweewarman McDonough, Kevin Atkins, Ella Kolmanovsky, Ilya Natl Civil Aviat Agey Brazil ANAC BR-12242 Sao Jose Dos Campos SP Brazil Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Univ Michigan Ann Arbor MI 48109 USA

The Envelope-Aware Flight Management System is an augmentation to a conventional flight management system that prevents or recovers from loss of control. Loss of control is defined in this work as an excursion outside the admissible flight envelope. The Envelope-Aware Flight Management System combines flight safety assessment and management, envelope estimation, flight planning, system identification, and adaptive control functions. This paper describes integration of envelope estimation, flight planning, and flight safety assessment and management to identify situations of high loss-of-control risk, override the nominal crew/flight-management-system just in time to prevent loss of control, and safely recover the aircraft. The Envelope-Aware Flight Management System is applied to prevent in-flight loss of control for a Twin Otter experiencing a rudder jam, a failure that can be identified and modeled a priori. Recovery translates to identifying and maintaining states within the contracted flight envelope, as well as building and following an emergency landing plan that respects the new envelope.

关键词： Roll control FMS Current Flight Plan adaptive control algorithm Flight Envelope Emergency Landing Flight Safety Knots True Airspeed Markov Decision Process Aircraft Flight Dynamics

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Online Aerodynamic Model Structure Selection and Parameter Estimation for Fault-Tolerant control

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JOURNAL OF GUIDANCE control AND DYNAMICS 2010年第3期33卷 707-723页

作者： Lombaerts, T. J. J. Van Oort, E. R. Chu, Q. P. Mulder, J. A. Joosten, D. A. Delft Univ Technol Control & Simulat Div Aerosp Software & Technol Inst NL-2600 GB Delft Netherlands Delft Univ Technol Delft Ctr Syst & Control NL-2600 GB Delft Netherlands

This paper describes a new recursive algorithm for the approximation of time-varying nonlinear aerodynamic models by means of a joint adaptive selection of the model structure and parameter estimation. This procedure is called adaptive recursive orthogonal least squares and is an extension and modification of the classical recursive orthogonal least-squares procedure. This algorithm is considered to be particularly useful for indirect fault-tolerant flight control, making use of model-based adaptive control routines. After the failure, a completely new aerodynamic model can be elaborated recursively with respect to structure, as well as parameter values. The performance of the identification algorithm is demonstrated on some simulation data sets.

关键词： adaptive control algorithm Recursive algorithm Flight control control Surfaces Calibrated Airspeed Angle of Attack Aerodynamic Properties GPS Angle of Sideslip Inertial Navigation System

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Reduction of vertical tail buffet response using active control

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JOURNAL OF AIRCRAFT 1996年第3期33卷 617-622页

作者： Hauch, RM Jacobs, JH Dima, C Ravindra, K McDonnell Douglas Aerospace St. Louis Missouri 63166 Parks College of St. Louis University Cahokia Illinois 62206

The active vertical tail (AVT) successfully reduced the buffet response of structures by utilizing piezoelectric actuators, strain gauge sensors, and simple control techniques. The AVT is a 5%-scale aero-elastically tailored structure that exhibits vibration response similar to a full-scale aircraft structure, and was designed such that it's piezoelectric actuators could provide control authority in the first two bending modes. The AVT was wind tunnel tested on a generic twin-tailed double-delta fighter model at angles of attack and dynamic pressures representative of actual aircraft flight envelopes, At high angles of attack, the model's leading-edge vortices impinge upon the AVT. Simple control algorithms were used with plezoelectric actuators and collocated strain gauge sensors to either minimize the acceleration at the AVT's tip or the strain at the root of the tail, control gains were verified to be a nonlinear function or angle of attack, dynamic pressure, and location of the actuator/sensor pair. Spectral analysis showed that the peak response of the controlled AVT was up to 65% lower than the uncontrolled response, This represents approximately an order of magnitude improvement in the fatigue life of a similar aircraft structure, The rms response below 200 Hz was reduced by over 20%.

关键词： adaptive control algorithm Piezoelectric Actuators Angle of Attack Strain Gauge Vortex Breakdown Dynamic Pressure Mean Aerodynamic Chord Structural Response Aircraft Configurations Low Speed Wind Tunnel

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Robust adaptive control of store release event for wings with external stores

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JOURNAL OF GUIDANCE control AND DYNAMICS 1999年第3期22卷 408-414页

作者： Gade, PVN Inman, DJ Virginia Polytech Inst & State Univ Dept Engn Sci & Mech Blacksburg VA 24061 USA

An adaptive control algorithm is numerically implemented to examine the effectiveness of an online estimation/control scheme for stabilizing the store release of a military aircraft. The adaptive law is based on a gradient method used for parameter estimation and is modified with the algorithms of leakage and dynamic normalization to robustify the adaptation. A linear quadratic control law based on a Luenberger observer is then used to close the loop. An active method of decoupling the wing from store pitch inertia effects for the wing/store Butter suppression problem is proposed. The proposed active decoupler pylon involves the use of a piezoceramic wafer strut as an actuator, which acts as a soft spring between the wing and the store. A two-degree-of-freedom typical section of an airfoil is used to represent the structural model of an F-16 aircraft wing, and the Butter problem is studied in incompressible flow regime, where the circulatory component of the aeroloads is modeled using Jones' approximation to the Theodorsen function. The aerodynamic effects on the store are, however, neglected to make the analysis simple. This study demonstrated the effectiveness of the proposed adaptive control strategy in improving the performance and robustness to sudden variation in store mass, a realistic situation representing the dropping of underwing bombs.

关键词： adaptive control algorithm Electro Hydraulic Actuator Thin Airfoil Aircraft Wings Gradient Method Military Aircraft Structural Modeling Aerodynamic Damping control Surfaces Radius of Gyration

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adaptive control OF THE ELECTRO-HYDRAULIC SERVO-SYSTEM WITH EXTERNAL DISTURBANCES

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ASIAN JOURNAL OF control 2013年第4期15卷 1065-1080页

作者： Wos, Piotr Dindorf, Ryszard Kielce Univ Technol PL-23314 Kielce Poland

The paper deals with the structure of the adaptive control electro-hydraulic servo-system (EHSS) with external load disturbances, practical verification of the identification, and control algorithms. The electro-hydraulic servo system composed of a servo-cylinder controlled with a servo-valve is discussed. It is a strongly nonlinear object with parameters changing over time. adaptive adjuster parameters were determined by means of current identification resulting in the parametric model. Identification was conducted on the basis of measurement of the controlling size and regulated size objects. The identified model of the object was applied to carry out the on-line synthesis of the proportional-integral-derivative (PID) controller. The selected problems connected with obtaining the algorithm of adaptive control are presented. The computer program for implementing the algorithm with numerical simulation and identification of the control physical model object were calculated. The aim of the research was to examine the effectiveness of the adaptive control method in an electro-hydraulic servo system, both theoretically and experimentally.

关键词： Electro-hydraulic servo-system system identification adaptive control algorithm forgetting adaptive control

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adaptive control of Precision Guided Airdrop Systems with Highly Uncertain Dynamics

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JOURNAL OF GUIDANCE control AND DYNAMICS 2018年第5期41卷 1025-1035页

作者： Cacan, Martin R. Costello, Mark Georgia Inst Technol Woodruff Sch Mech Engn Ctr Adv Machine Mobil Atlanta GA 30322 USA Georgia Inst Technol Auton Guggenheim Sch Aerosp Engn Atlanta GA 30322 USA

The bulk of research in the field of precision guided airdrop systems has focused on improving landing accuracy in the presence of atmospheric winds that can exceed vehicle airspeed. One important challenge of parafoil systems is their highly uncertain flight dynamic behavior and control response, which can result from canopy degradation or an offnominal inflation event. This significantly impacts the ability to reach the target and can often lead to very large miss distances. This work addresses guided airdrop system model uncertainty with a novel combined direct and indirect adaptive control strategy to quickly characterize vehicle dynamics and lateral control sensitivity in flight. Extensive simulation and experimental flight testing indicate that the proposed adaptive algorithm is capable of high-accuracy landing in a large variety of degraded conditions, including unknown nonlinear changes in control sensitivity as well as control reversals. In comparison, current industry standard algorithms experience over an order of magnitude decrease in accuracy when tested under identical scenarios.

关键词： adaptive control algorithm Parafoil Experimental Flight Test Airspeed control Reversal adaptive algorithm Navigation algorithm GPS Multiple Input Multiple Output algorithms Ability

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Design of an adaptive feedforward/feedback combined control for piezoelectric actuated micro positioning stage

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PRECISION ENGINEERING-JOURNAL OF THE INTERNATIONAL SOCIETIES FOR PRECISION ENGINEERING AND NANOTECHNOLOGY 2022年 78卷 199-205页

作者： Shi, Beichao Shi, Rui Wang, Fujun Tianjin Univ Sch Mech Engn Key Lab Mech Theory & Equipment Design Minist Educ Tianjin 300354 Peoples R China

This paper proposes a novel feedforward/feedback combined control applied to a piezoelectric (PZT) actuated micro positioning stage. Based on the rate-dependent P-I inverse hysteresis model, a feedforward controller is built to compensate the hysteresis characteristics of the piezoelectric actuators, and the relevant parameters of the model are obtained through system identification. An adaptive control algorithm is adopted in feedback controller to reduce the influence of external disturbance. By introducing error-related forgetting factors to adjust the weight of old data and new data in real time, the robustness and accuracy of the control system are improved. The simulations are carried out to estimate the performance of the time-varying forgetting factors based adaptive algorithm. Finally, experimental tests are conducted to investigate the performance of the pro-posed feedforward/feedback combined control. The experimental results indicates that the settling time is 53 ms corresponding to the square wave signal and the maximum tracking error of a sine trajectory with the frequency of 20 Hz is 1.63 mu m.

关键词： feedback combined control P -I inverse Hysteresis model adaptive control algorithm Error-related forgetting factors Micro positioning stage

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adaptive control technique for suppression of resonance in grid-connected PV inverters

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IET POWER ELECTRONICS 2019年第6期12卷 1479-1486页

作者： Goh, Hongsoo Armstrong, Matthew Zahawi, Bashar Northern Powergrid Protect & Tech Serv Castleford WF10 SDS England Newcastle Univ Sch Engn Newcastle Upon Tyne NE1 7RU Tyne & Wear England Khalifa Univ Dept Elect & Comp Engn Abu Dhabi 127788 U Arab Emirates

Grid operating conditions have a significant effect on the harmonic and resonant performance of grid-connected photovoltaic (PV) inverters and changes in grid impedance can cause a notable change in the resonant excitation between the PV inverter and the grid. This study proposes an adaptive control algorithm for grid-connected PV inverters to suppress the resonance condition excited by grid inductance variation, resulting from the dynamic changes in the operating conditions of the distribution network. The causes of resonance between grid-connected PV inverters and the distribution grid are discussed and the design of an active band-pass filter for capturing resonance is described. The proportional gain within the proportional-integral controller is then adaptively controlled in real time to compensate for changes in the grid impedance and suppress resonant excitation while maintaining excellent low-order harmonic performance compared with alternative fixed gain controller techniques, particularly for systems with high values of grid inductance. The performance of the proposed controller is experimentally verified using a 240 V, 2 kVA single-phase grid-connected inverter.

关键词： photovoltaic power systems invertors adaptive control band-pass filters power grids adaptive control technique grid-connected PV inverters grid operating conditions harmonic performance resonant performance grid-connected photovoltaic inverters grid impedance PV inverter adaptive control algorithm resonance condition grid inductance variation distribution grid single-phase grid-connected inverter resonant excitation suppression active band-pass filter voltage 240 0 V apparent power 2 0 kVA

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Nonlinear inverse dynamics control of aircraft using spoilers

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JOURNAL OF GUIDANCE control AND DYNAMICS 1996年第2期19卷 475-482页

作者： Sun, XD Woodgate, KG Allwright, JC UNIV LONDON IMPERIAL COLL SCI TECHNOL & MED DEPT ELECT ENGN & ELECTRLONDON SW7 2BYENGLAND UNIV LONDON IMPERIAL COLL SCI TECHNOL & MED INTERDISCIPLINARY RES CTR PROC SYST ENGNLONDON SW7 2BYENGLAND

The nonlinear inverse dynamics (NID) methodology and its specific application to flight control using a promising control device, the spoiler, are studied, The proper control modeling of spoiler aerodynamics leads to a generic nonlinear model for the most typical aft-mounted spoilers that is then included in a complete nonlinear aircraft model. A novel systematic design procedure for the synthesis of robust NID-based flight control systems is presented, Use of the methodology for a modern combat aircraft, the Hawk trainer, leads to the development of a multimode longitudinal flight control system, with the particular aim of using spoilers as an active control device. Promising applications of spoilers for active control of aircraft are studied, and the related control configurations designed, Simulation results for aircraft maneuvering are presented, demonstrating the effectiveness of spoilers for aircraft maneuver enhancement and, in particular, in ameliorating the effects of wind shear and microbursts.

关键词： High Performance Aircraft control Surfaces Microburst Aircraft Flight control adaptive control algorithm Aerodynamic Coefficients Aircraft Maneuvers Combat Aircraft Aircraft Systems Aircraft control

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