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An adaptive control algorithm for blood glucose regulation in Type-I Diabetes Mellitus patients

Decision Analytics Journal 2023年 8卷

作者： Patra, Akshaya Kumar Panigrahi, Girija Sankar Department of EEE ITER Siksha ‘O'Anusandhan University Odisha Bhubaneswar 751030 India Department of EE ITER Siksha ‘O'Anusandhan University Odisha Bhubaneswar 751030 India

This study presents the design and development of a Remora Optimization -Tilt Integral-Derivative-Filter (RO-TIDF) controller to infuse ideal insulin doses to manage Blood Glucose (BG) levels in Type-I Diabetes Mellitus (TIDM) patients with Artificial Pancreas (AP). In this control technique, Remora Optimization algorithm (ROA) is used, which adjusts the controller gains of the proposed patient model for better regulation of BG. This classic RO controller is designed to improve patient performance and robustness. Nonlinearities present in the patient model pose problems for glycemic control. Using an AP-based ROA efficiently overcomes the nonlinearity of patient models and maintains BG levels in the glycemic band (70–120 mg/dl). The suggested patient model with RO-TIDF is examined for precision, consistency, robustness, noise reduction, and improved uncertainty handling. A comparative study of results from different control methods reveals the causes of the advanced control performance of the proposed approach. © 2023 The Author(s)

关键词： adaptive control algorithm controller Diabetes Glucose Pancreas Remora optimization

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An adaptive fluid-solid coupling time step control algorithm for unsteady conjugate heat transfer

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PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART C-JOURNAL OF MECHANICAL ENGINEERING SCIENCE 2024年第16期238卷 8515-8530页

作者： Cai, Feixue Zhang, Long Zhou, Hua Yao, Min Ren, Zhuyin Tsinghua Univ Inst Aero Engine Beijing Peoples R China Tsinghua Univ Ctr Combust Energy Beijing Peoples R China Tsinghua Univ Beijing 100084 Peoples R China

Unsteady simulation with conjugate heat transfer has to tackle the stiffness issue that originates from the wide disparate time scales between fluid and solid heat transfer. In the loosely coupled framework, challenges remain in determining the optimal coupling time step between the fluid and solid solvers, in terms of efficiency and accuracy. This study formulates a correlation for the coupling error, together with the Proportional-Integral-Derivative (PID) control method, to propose an adaptive fluid-solid coupling time step algorithm, which dynamically adjusts the coupling time step such that the computational efficiency can be improved without sacrificing accuracy. The proposed algorithm has been tested in a 1D conjugate heat transfer application with typical operating conditions of a real engine, and the performance of different controllers (I, PI, PID) has been analyzed and compared. Results show that with the closed-loop control, all controllers can ensure the error control below the user specified tolerance at the cost of reducing efficiency. Meanwhile, with the open-loop control which is of more interest to practical applications, controllers suffer from instability issues when a conventional algorithm based on integration error is employed. The proposed coupling-error-based algorithm successfully tackles the instability issues. Compared with the baseline algorithm of the constant coupling time step, the proposed algorithm can reduce approximately 40%-90% computational cost for the 1D cases considered.

关键词： Unsteady conjugate heat transfer fluid-solid coupling time step adaptive control algorithm PID control combustor liner

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Opportunities of adaptive control algorithms Application in Railway control Systems 7

Opportunities of Adaptive Control Algorithms Application in ...

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7th International Conference on Intelligent Technologies in Logistics and Mechatronics Systems (ITELMS 2012)

作者： Potapovs, A. Gorobetz, M. Levehenkov, A. Riga Tech Univ Inst Ind Elect & Elect Engn LV-1658 Riga Latvia

ISBN: (纸本)6090205710

The authors of the article on the example of a particular crossing suggest a description of a new project of adaptive control system of railway crossings work selecting for the adaptive system the most suitable adaptive control algorithm defining its main blocks, their functions, and operation algorithms. At the beginning of the paper the essence of complex objects control adaptation is analysed, and the most optimal one is selected from them. Then the main blocks of the suggested system and their operation are described applying the selected adaptive functioning algorithm. The paper is completed with the comparison of the effectiveness of the suggested system with the present one, proving that the suggested system can significantly compete and solve the problems with traffic in the movement of railway and sity transport.

关键词： railway transport embedded systems adaptive control algorithm

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Multibody Simulation of Integrated Tiltrotor Flight Mechanics, Aeroelasticity, and control

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JOURNAL OF GUIDANCE control AND DYNAMICS 2012年第5期35卷 1391-1405页

作者： Mattaboni, Mattia Masarati, Pierangelo Quaranta, Giuseppe Mantegazza, Paolo Politecn Milan Dipartimento Ingn Aerosp I-20156 Milan Italy

This work describes the application of an adaptive control algorithm based on the generalized predictive control paradigm to a detailed nonlinear aeroelastic model of a tiltrotor aircraft that includes rigid-body degrees of freedom, restricted to the plane of symmetry. The analysis is based on an original multibody dynamics formulation. The model is augmented by an autopilot and a stability augmentation system;in relevant cases, a model of the passive biomechanics of the pilot is considered as well. The interaction of rigid-body and deformable degrees of freedom alters the aeroelastic behavior of the system compared with that of the clamped wing rotor, discussed in a previous work. The flutter mechanism, originally consisting in whirl flutter, changes after considering rigid-body degrees of freedom;the short-period flight mechanics mode now dominates high-speed stability. This issue is mainly addressed by the stability augmentation system, whereas the generalized predictive control is mainly used to reduce gust-induced wing loads, although its intervention for whirl-flutter suppression is still needed to extend the flight envelope at very high speed. The capability of the adaptive regulator RI reduce wing loads is assessed in hover and in highspeed forward flight. In the latter condition, the capability to suppress whirl flutter is assessed as well.

关键词： Flight Mechanics Aeroservoelastic Systems Tiltrotor Aircraft Multibody Simulation Stability and control Augmentation System Autopilot Pilot adaptive control algorithm Flight Envelope Wing Loading

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Observer-Based Fault-Tolerant Attitude control for Spacecraft with Input Delay

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JOURNAL OF GUIDANCE control AND DYNAMICS 2018年第9期41卷 2041-2053页

作者： Liu, Chuang Vukovich, George Sun, Zhaowei Shi, Keke Harbin Inst Technol Res Ctr Satellite Technol 2 Yikuang St Harbin 150001 Heilongjiang Peoples R China York Univ Dept Earth & Space Sci & Engn 4700 Keele Str Toronto ON M3J 1P3 Canada

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Model-Free control Design for Multi-Input Multi-Output Aeroelastic System Subject to External Disturbance

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JOURNAL OF GUIDANCE control AND DYNAMICS 2011年第2期34卷 446-458页

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

In this paper, a class of aeroelastic systems with an unmodeled nonlinearity and external disturbance is considered. By using leading- and trailing-edge control surface actuations, a full-state feedforward/feedback controller is designed to suppress the aeroelastic vibrations of a nonlinear wing section subject to external disturbance. The full-state feedback control yields a uniformly ultimately bounded result for two-axis vibration suppression. With the restriction that only pitching and plunging displacements are measurable while their rates are not, a high-gain observer is used to modify the full-state feedback control design to an output feedback design. Simulation results demonstrate the efficacy of the multi-input multi-output control toward suppressing aeroelastic vibration and limit cycle oscillations occurring in pre and postflutter velocity regimes when the system is subjected to a variety of external disturbance signals. Comparisons are drawn with a previously designed adaptive multi-input multi-output controller.

关键词： Nonlinear Aeroelasticity adaptive control algorithm Feedback Linearization Neural Networks Aerodynamic Moments control Surfaces Vibration Suppression Angle of Attack Flight Envelope Structural Nonlinearities

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Numerical simulation of adaptive control: Application to unstable solid rocket motors

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AIAA JOURNAL 2002年第5期40卷 860-868页

作者： Mettenleiter, M Vuillot, F Candel, S Ecole Cent Paris CNRS Lab EM2C F-92295 Chatenay Malabry France Off Natl Etud & Rech Aerosp F-92322 Chatillon France

Current developments in the numerical simulation of active control are described. The objective of this investigation is to devise software tools for the development of active control. The present approach uses a numerical simulation of the system based on the Navier-Stokes equations. It differs from the more standard simulations relying on lower-order dynamic models. The main difficulties associated with the present strategy are related to the representation of the actuator in the flow simulation module and with the interfacing of this module with the adaptive control routine. These issues requite careful treatment to obtain a suitable numerical model of flow control. It is first shown that,the actuator may be described by a distribution of sources in the field. The time steppings needed by the flow simulation module and by the control unit differ widely. (The ratio between the time steps is of the order of 100 or more.) This constitutes a source of perturbation, and it may introduce unwanted high-frequency components in the flow simulation. It is shown that this problem is alleviated by placing numerical filters at the controller input and output. A set of calculations are carried out to simulate vortex shedding instabilities of a simplified solid propellant rocket. These instabilities are then adaptively controlled. This example serves to illustrate the simulation methodology and provides insights into the operation of the flow controller.

关键词： Numerical Simulation adaptive control algorithm Solid Rocket Motor Vortex Shedding Phenomena Actuators Navier Stokes Equations Predictor Corrector Method Solid Propellant Rocket Software Tool Differential Pressure Sensors

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adaptive Glide Slope control for Parafoil and Payload Aircraft

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JOURNAL OF GUIDANCE control AND DYNAMICS 2013年第4期36卷 1019-1034页

作者： Ward, Michael Costello, Mark Georgia Inst Technol Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA Georgia Inst Technol Guggenheim Sch Aerosp Engn Woodruff Sch Mech Engn Atlanta GA 30332 USA

The invention of the steerable, gliding, ram-air parafoil enabled the possibility of precision, autonomous aerial payload delivery. Research and development work on guided airdrop systems has focused primarily on evolutionary improvements to the guidance algorithm, although the navigation and control algorithms have changed little since the initial autonomous systems were developed. Recent work has demonstrated the potential for dramatic improvements in landing accuracy through the incorporation of canopy incidence variation to achieve glide slope control for parafoils. The current work presents the development of a control law to implement glide slope control on an autonomous airdrop system. Autonomous landings with the control law in both simulation and flight test demonstrate an improvement in landing accuracy by a factor of two, though the improvement can be even greater in especially windy conditions. Finally, the ability to perform in-flight system identification to adapt internal control mappings to match flight data and provide dramatic improvements in landing accuracy when there is a significant discrepancy between the assumed and actual flight characteristics is demonstrated in both simulation and flight test.

关键词： Parafoil Air Vehicle Flight Test Programme adaptive control algorithm control algorithm Flight Software Navigation algorithm Autonomous Systems Airspeed GPS

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Online Dynamic Trim and control Limit Estimation

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JOURNAL OF GUIDANCE control AND DYNAMICS 2012年第5期35卷 1647-1656页

作者： Yavrucuk, Ilkay Prasad, J. V. R. Middle E Tech Univ Dept Aerosp Engn TR-06531 Ankara Turkey Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA

The online estimation of a maneuvering steady-state condition of an aircraft, called the dynamic trim, is used to estimate the allowable control travel during flight, a key information in pilot cueing for envelope limit protection. In this paper a new methodology is presented where adaptive models are used to estimate online local dynamic trim conditions, while requiring very limited a priori vehicle information. adaptive neural networks are employed to enable online learning. The models are used to estimate future aircraft responses and artificial margins on controls that would keep the aircraft response within its flight envelope limits. A linear helicopter model and the XV-15 tiltrotor model are used to demonstrate the method in simulation.

关键词： Neural Networks Pilot Flight Envelope Rotorcrafts Helicopters Flight control System adaptive control algorithm Flight Testing Cyclic control Single Input Single Output System

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Design of an aeroelastic delta wing model for active flutter control

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JOURNAL OF GUIDANCE control AND DYNAMICS 2001年第5期24卷 918-924页

作者： Rule, JA Richard, RE Clark, RL Active Control EXperts Inc Cambridge MA 02142 USA Duke Univ Dept Mech Engn & Mat Sci Durham NC 27708 USA

Ongoing research into the active control of aeroelastic structures has resulted in a new model for the control of delta wing flutter. An analytical and numerical formulation for both the aerodynamic forcing and structural response of the wing was developed. The order of the aerodynamic model was reduced through balanced model reduction, yielding an accurate, low-order representation of the three-dimensional flowfield around the delta wing. This fully coupled aero/structural model was used to investigate the optimal placement of piezoelectric sensors and actuators to design an adaptive structure that emphasized control of the flutter mode. Previous work has shown that such control schemes can delay the onset of flutter to increased dynamic pressure. This work extends the practical use of reduced-order aerodynamic modeling to the realm of real-time control system design, while simultaneously applying recently developed techniques for open-loop design and selection of sensors and actuators. Results indicate that a single sensor/actuator pair can be designed to significantly extend the flutter boundary.

关键词： Delta Wing Piezoelectric Actuators Piezoelectric Sensors adaptive control algorithm Structural Modeling Freestream Velocity Real Time control System adaptive Structures Structural Response Dynamic Pressure

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