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Author: Elisa Capello
Publisher: LAP Lambert Academic Publishing
ISBN: 9783838353067
Category :
Languages : en
Pages : 176
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Book Description
Different control laws have been analyzed, from the classical theory, like PD and LQR controllers, to an innovative theory, that is represented by the L1 adaptive controller. The validation of controllers is proposed on the experimental model (derived from flight tests) and in a formation flight application. A quadrotor is a platform with fast dynamics, thus if a sudden maneuver is implemented can cause glitches on the parameters trend and the aircraft could become uncontrollable. A key aspect of this controller is the definition of control signals as the output of a low pass-filter. This feature permits to avoid high frequency oscillations due to the large adaptation gain; in systems that use electronic devices. Moreover, this controller is robust in presence of model uncertainties and unmodeled dynamics. The simple structure and the presence of less oscillations during the implementation demonstrate that this controller can be a good candidate for an autopilot. Therefore, the low pass filter is evaluated by a trial and error method. To provide a systematic method, a mixed deterministic - randomized approach for the control law design (low pass filter) is proposed.
Author: Elisa Capello
Publisher: LAP Lambert Academic Publishing
ISBN: 9783838353067
Category :
Languages : en
Pages : 176
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Book Description
Different control laws have been analyzed, from the classical theory, like PD and LQR controllers, to an innovative theory, that is represented by the L1 adaptive controller. The validation of controllers is proposed on the experimental model (derived from flight tests) and in a formation flight application. A quadrotor is a platform with fast dynamics, thus if a sudden maneuver is implemented can cause glitches on the parameters trend and the aircraft could become uncontrollable. A key aspect of this controller is the definition of control signals as the output of a low pass-filter. This feature permits to avoid high frequency oscillations due to the large adaptation gain; in systems that use electronic devices. Moreover, this controller is robust in presence of model uncertainties and unmodeled dynamics. The simple structure and the presence of less oscillations during the implementation demonstrate that this controller can be a good candidate for an autopilot. Therefore, the low pass filter is evaluated by a trial and error method. To provide a systematic method, a mixed deterministic - randomized approach for the control law design (low pass filter) is proposed.
Author: Elisa Capello
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Prasenjit Mukherjee
Publisher:
ISBN:
Category :
Languages : en
Pages : 86
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Book Description
Recent advances in sensor and microcomputer technology and in control and aeroydynamics theories has made small unmanned aerial vehicles a reality. The small size, low cost and manoueverbility of these systems has positioned them to be potential solutions in a large class of applications. However, the small size of these vehicles pose significant challenges. The small sensors used on these systems are much noisier than their larger counterparts. The compact structure of these vehicles also makes them more vulnerable to environmental effects. This work develops several different control strategies for two sUAV platforms and provides the rationale for judging each of the controllers based on a derivation of the dynamics, simulation studies and experimental results where possible. First, the coaxial helicopter platform is considered. This sUAV's dual rotor system (along with its stabilizer bar technology) provides the ideal platform for safe, stable flight in a compact form factor. However, the inherent stability of the vehicle is achieved at the cost of weaker control authority and therefore an inability to achieve aggressive trajectories especially when faced with heavy wind disturbances. Three different linear control strategies are derived for this platform. PID, LQR and H[infin] methods are tested in simulation studies. While the PID method is simple and intuitive, the LQR method is better at handling the decoupling required in the system. However the frequency domain design of the H[infin] control method is better at suppressing disturbances and tracking more aggressive trajectories. The dynamics of the quadrotor are much faster than those of the coaxial helicopter. In the quadrotor, four independent fixed pitch rotors provide the required thrust. Differences between each of the rotors creates moments in the roll, pitch and yaw directions. This system greatly simplifies the mechanical complexity of the UAV, making quadrotors cheaper to maintain and more accessible. The quadrotor dynamics are derived in this work. Due to the lack of any mechanical stabilization system, these quadrotor dynamics are not inherently damped around hover. As such, the focus of the controller development is on using nonlinear techniques. Linear quadratic regulation methods are derived and shown to be inadequate when used in zones moderately outside hover. Within nonlinear methods, feedback linearization techniques are developed for the quadrotor using an inner/outer loop decoupling structure that avoids more complex variants of the feedback linearization methodology. Most nonlinear control methods (including feedback linearization) assume perfect knowledge of vehicle parameters. In this regard, simulation studies show that when this assumption is violated the results of the flight significantly deteriorate for quadrotors flying using the feedback linearization method. With this in mind, an adaptation law is devised around the nonlinear control method that actively modifies the plant parameters in an effort to drive tracking errors to zero. In simple cases with sufficiently rich trajectory requirements the parameters are able to adapt to the correct values (as verified by simulation studies). It can also adapt to changing parameters in flight to ensure that vehicle stability and controller performance is not compromised. However, the direct adaptive control method devised in this work has the added benefit of being able to modify plant parameters to suppress the effects of external disturbances as well. This is clearly shown when wind disturbances are applied to the quadrotor simulations. Finally, the nonlinear quadrotor controllers devised above are tested on a custom built quadrotor and autopilot platform. While the custom quadrotor is able to fly using the standard control methods, the specific controllers devised here are tested on a test bench that constrains the movement of the vehicle. The results of the tests show that the controller is able to sufficiently change the necessary parameter to ensure effective tracking in the presence of unmodelled disturbances and measurement error.
Author: Anh Tuan Le
Publisher: BoD – Books on Demand
ISBN: 9535137964
Category : Technology & Engineering
Languages : en
Pages : 364
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Book Description
This book focuses on the applications of robust and adaptive control approaches to practical systems. The proposed control systems hold two important features: (1) The system is robust with the variation in plant parameters and disturbances (2) The system adapts to parametric uncertainties even in the unknown plant structure by self-training and self-estimating the unknown factors. The various kinds of robust adaptive controls represented in this book are composed of sliding mode control, model-reference adaptive control, gain-scheduling, H-infinity, model-predictive control, fuzzy logic, neural networks, machine learning, and so on. The control objects are very abundant, from cranes, aircrafts, and wind turbines to automobile, medical and sport machines, combustion engines, and electrical machines.
Author: Robert Anderson
Publisher:
ISBN:
Category : Adaptive control systems
Languages : en
Pages : 117
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Book Description
Author: Johannes Verberne
Publisher:
ISBN:
Category : Drone aircraft
Languages : en
Pages : 406
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Book Description
Inherent stability inside the flight envelope must be guaranteed in order to safely introduce private and commercial UAV systems into the national airspace. The rejection of unknown external wind disturbances offers a challenging task due to the limited available information about the unpredictable and turbulent characteristics of the wind. This thesis focuses on the design, development and implementation of robust control algorithms for disturbance rejection in rotorcraft UAVs. The main focus is the rejection of external disturbances caused by wind influences. Four control algorithms are developed in an effort to mitigate wind effects: baseline nonlinear dynamic inversion NLDI), a wind rejection extension for the NLDI, NLDI with adaptive artificial neural networks (ANN) augmentation, and NLDI with L1 adaptive control augmentation. A simulation environment is applied to evaluate the performance of these control algorithms under external wind conditions using a Monte Carlo analysis. Outdoor flight test results are presented for the implementation of the baseline NLDI, NLDI augmented with adaptive ANN and NLDI augmented with L1 adaptive control algorithms in a DJII F330 Flamewheel quadrotor UAV system. A set of metrics is applied to compare and evaluate the overall performance of the developed control algorithms under external wind disturbances. The obtained results show that the extended NLDI exhibits undesired characteristics while the augmentation of the baseline NLDI control law with adaptive ANN and L1 output-feedback adaptive control improve the robustness of the translational and rotational dynamics of a rotorcraft UAV in the presence of wind disturbances
Author: Nihal Dalwadi
Publisher: Springer Nature
ISBN: 9811997446
Category : Technology & Engineering
Languages : en
Pages : 188
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Book Description
This book discusses the dynamics of a tail-sitter quadrotor and biplane quadrotor-type hybrid unmanned aerial vehicles (UAVs) and, based on it, various nonlinear controllers design like backstepping control (BSC), ITSMC (Integral Terminal Sliding Mode Control), and hybrid controller (BSC + ITSMC). It discusses single and multiple observer-based control strategies to handle external disturbances like wind gusts and estimate states. It covers the dynamics of slung load with a biplane quadrotor and a control architecture to handle the effect of partial rotor failure with wind gusts acting on it. An anti-swing control to prevent damage to the slung load and a deflecting surface-based total rotor failure compensation strategy to prevent damage to the biplane quadrotor are also discussed in this book. The monograph will be helpful for undergraduate and post-graduate students as well as researchers in their advanced studies.
Author: Ali Ümit Keskin
Publisher: Springer
ISBN: 3319952439
Category : Technology & Engineering
Languages : en
Pages : 791
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Book Description
This monograph presents teaching material in the field of differential equations while addressing applications and topics in electrical and biomedical engineering primarily. The book contains problems with varying levels of difficulty, including Matlab simulations. The target audience comprises advanced undergraduate and graduate students as well as lecturers, but the book may also be beneficial for practicing engineers alike.
Author: Shuyi Shao
Publisher: Springer Nature
ISBN: 3030579573
Category : Technology & Engineering
Languages : en
Pages : 207
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Book Description
This book studies selected discrete-time flight control schemes for fixed-wing unmanned aerial vehicle (UAV) systems in the presence of system uncertainties, external disturbances and input saturation. The main contributions of this book for UAV systems are as follows: (i) the proposed integer-order discrete-time control schemes are based on the designed discrete-time disturbance observers (DTDOs) and the neural network (NN); and (ii) the fractional-order discrete-time control schemes are developed by using the fractional-order calculus theory, the NN and the DTDOs. The book offers readers a good understanding of how to establish discrete-time tracking control schemes for fixed-wing UAV systems subject to system uncertainties, external wind disturbances and input saturation. It represents a valuable reference guide for academic research on uncertain UAV systems, and can also support advanced / Ph.D. studies on control theory and engineering.
Author: Moussa Labbadi
Publisher: Springer Nature
ISBN: 3030810143
Category : Technology & Engineering
Languages : en
Pages : 263
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Book Description
This book studies selected advanced flight control schemes for an uncertain quadrotor unmanned aerial vehicle (UAV) systems in the presence of constant external disturbances, parametric uncertainties, measurement noise, time-varying external disturbances, and random external disturbances. Furthermore, in all the control techniques proposed in this book, it includes the simulation results with comparison to other nonlinear control schemes recently developed for the tracking control of a quadrotor UAV. The main contributions of the present book for quadrotor UAV systems are as follows: (i) the proposed control methods are based on the high-order sliding mode controller (SMC) and hybrid control algorithm with an optimization method. (ii) the finite-time control schemes are developed by using fast terminal SMC (FTSMC), nonsingular FTSMC (NFTSMC), global time-varying SMC, and adaptive laws. (iii) the fractional-order flight control schemes are developed by using the fractional-order calculus theory, super twisting algorithm, NFTSMC, and the SMC. This book covers the research history and importance of quadrotor system subject to system uncertainties, external wind disturbances, and noise measurements, as well as the research status of advanced flight control methods, adaptive flight control methods, and flight control based on fractional-order theory. The book would be interesting to most academic undergraduate, postgraduates, researchers on flight control for drones and applications of advanced controllers in engineering field. This book presents a must-survey for advanced finite-time control for quadrotor system. Some parts of this book have the potential of becoming the courses for the modelling and control of autonomous flying machines. Readers (academic researcher, undergraduate student, postgraduate student, MBA/executive, and education practitioner) interested in nonlinear control methods find this book an investigation. This book can be used as a good reference for the academic research on the control theory, drones, terminal sliding mode control, and related to this or used in Ph.D. study of control theory and their application in field engineering.
