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Nonlinear Robust Adaptive Controller Design For An Air Breathing Hypersonic Vehicle Model
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Book Synopsis Nonlinear Robust/adaptive Controller Design for an Air-breathing Hypersonic Vehicle Model by : Lisa Fiorentini
Download or read book Nonlinear Robust/adaptive Controller Design for an Air-breathing Hypersonic Vehicle Model written by Lisa Fiorentini and published by . This book was released on 2007 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: This thesis presents the design of two nonlinear robust controllers for an air-breathing hypersonic vehicle model. To overcome the analytical intractability of a dynamical model derived from first principles, a simplified control-oriented model is used for control design. The control-oriented model retains most of the features of the original model, including non-minimum phase characteristic of the flight-path angle dynamics and strong couplings between the engine and flight dynamics, whereas flexibility effects, included in the simulation model, are regarded as a dynamic perturbation. In adopting reduced-complexity models for controller design, the issue of robustness with respect to model uncertainty must be carefully addressed and included at the design level. Dynamic inversion-based design methods do not lend themselves easily to quantitative robustness analysis, due to the complexity of the inverse model of the plant. In this work, a nonlinear sequential loop-closure approach is adopted to design two different dynamic state-feedback controllers that provide stable tracking of velocity and altitude reference trajectories. The approach considered utilizes a combination of adaptive and robust design methods based on both classical and recently developed nonlinear design tools. Simulation results indicate that the proposed methodology may constitute a feasible approach towards the development of robust nonlinear controllers that satisfactorily address the issue of model uncertainty for this type of application.
Book Synopsis Nonlinear Adaptive Controller Design for Air-breathing Hypersonic Vehicles by : Lisa Fiorentini
Download or read book Nonlinear Adaptive Controller Design for Air-breathing Hypersonic Vehicles written by Lisa Fiorentini and published by . This book was released on 2010 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: This dissertation presents the design of two nonlinear robust controllers for an air-breathing hypersonic vehicle model capable of providing stable tracking of velocity and altitude (or flight-path angle) reference trajectories. To overcome the analytical intractability of a dynamical model derived from first principles, a simplified control-oriented model is used for control design. The control-oriented model retains the most important features of the model from which it was derived, including the non-minimum phase characteristic of the flight-path angle dynamics and strong couplings between the engine and flight dynamics. The first control design considers as control inputs the fuel equivalence ratio and the elevator and canard deflections. A combination of nonlinear sequential loop-closure and adaptive dynamic inversion has been adopted for the design of a dynamic state-feedback controller. An important contribution given by this work is the complete characterization of the internal dynamics of the model has been derived for Lyapunov-based stability analysis of the closed-loop system, which includes the structural dynamics. The results obtained address the issue of stability robustness with respect to both parametric model uncertainty, which naturally arises in adopting reduced-complexity models for control design, and dynamic perturbations due to the flexible dynamics. In the second control design a first step has been taken in extending those results in the case in which only two control inputs are available, namely the fuel equivalence ratio and the elevator deflection. The extension of these results to this new framework is not trivial since several issues arise. First of all, the vehicle dynamics are characterized by exponentially unstable zero-dynamics when longitudinal velocity and flight-path angle are selected as regulated output. This non-minimum phase behavior arises as a consequence of elevator-to-lift coupling. In the previous design the canard was strategically used to adaptively decouple lift from elevator command, thus rendering the system minimum phase. Moreover, the canard input was also employed to enforce the equilibrium at the desired trim condition and to provide a supplementary stabilizing action. As a result, when this control input is not assumed to be available, the fact that the system needs to be augmented with an integrator (to reconstruct the desired equilibrium) and the non-minimum phase behavior have a strong impact on the control design. In these preliminary results the flexible effects are not taken into account in the stability analysis but are considered as a perturbation and included in the simulation model. The approach considered utilizes a combination of adaptive and robust design methods based on both classical and recently developed nonlinear design tools. As a result, the issue of robustness with respect to parameter uncertainties is addressed also in this control design. Simulation results on the full nonlinear model show the effectiveness of both controllers.
Book Synopsis Modeling and Nonlinear Control of a 6-DOF Hypersonic Vehicle by : Mohammad Shakiba-Herfeh
Download or read book Modeling and Nonlinear Control of a 6-DOF Hypersonic Vehicle written by Mohammad Shakiba-Herfeh and published by . This book was released on 2015 with total page 137 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the past two decades, there has been a renewed and sustained effort devoted to modeling the dynamics of air-breathing hypersonic vehicles, for both simulation and control design purposes. The highly nonlinear characteristics of flight dynamics in hypersonic regimes and the consequent significance variability of the response with the operating conditions requires the development of innovative flight control solutions, hence the development of suitable model of the vehicle dynamics that are amenable to design, validation and rapid calibration of control algorithms. In this dissertation, a control-oriented and a simulation model of a generic hypersonic vehicle were derived to support the design and calibration of model-based flight controllers. A nonlinear robust adaptive controller was developed on the basis of the control-oriented model, that was shown to provide stable trajectory tracking in higher fidelity computer simulations. The first stage of this research was the development of a control design model (CDM) for the 6-degree-of-freedom dynamics of an air-breathing hypersonic aircraft based on an available high-fidelity first principle model. A method that incorporates the theory of compressible fluid dynamics and system identification methods, was proposed and implemented. The development of the CDM is based on curve fit approximation of the forces and moments acting on the vehicle, making the model suitable for control design. Kriging and Least Squares methods were used to find the most appropriate curve-fitted model of the aerodynamic forces for both the control design and the control simulation models. It was shown that the 6-DOF model can be both categorized as an under-actuated mechanical system, as well as an over-actuated system with respect to a chosen in- put/output pair of interest. An important contribution of this work is the development of a nonlinear adaptive controller for the 6-DOF control design model. The controller was endowed with a modular structure, comprised of an adaptive inner-loop attitude controller and a robust nonlinear outer-loop controller of fixed structure. The purpose of the outer- loop controller is to avoid the typical complexity of solutions derived from adaptive backstepping methods. A noticeable feature of the outer-loop controller is the presence of an internal model unit that generates the reference for the angle-of-attack, in spite of parametric model uncertainty. Airspeed, lateral velocity, vehicle's heading and altitude were considered as regulated outputs of the system. Simulation results on the control simulation model show the effectiveness of the developed controller in spite of significant variation in the flight parameters.
Book Synopsis Geometry Modeling and Adaptive Control of Air-breathing Hypersonic Vehicles by : Tyler J. Vick
Download or read book Geometry Modeling and Adaptive Control of Air-breathing Hypersonic Vehicles written by Tyler J. Vick and published by . This book was released on 2014 with total page 149 pages. Available in PDF, EPUB and Kindle. Book excerpt: Air-breathing hypersonic vehicles have the potential to provide global reach and affordable access to space. Recent technological advancements have made scramjet-powered flight achievable, as evidenced by the successes of the X-43A and X-51A flight test programs over the last decade. Air-breathing hypersonic vehicles present unique modeling and control challenges in large part due to the fact that scramjet propulsion systems are highly integrated into the airframe, resulting in strongly coupled and often unstable dynamics. Additionally, the extreme flight conditions and inability to test fully integrated vehicle systems larger than X-51 before flight leads to inherent uncertainty in hypersonic flight. This thesis presents a means to design vehicle geometries, simulate vehicle dynamics, and develop and analyze control systems for hypersonic vehicles. First, a software tool for generating three-dimensional watertight vehicle surface meshes from simple design parameters is developed. These surface meshes are compatible with existing vehicle analysis tools, with which databases of aerodynamic and propulsive forces and moments can be constructed. A six-degree-of-freedom nonlinear dynamics simulation model which incorporates this data is presented. Inner-loop longitudinal and lateral control systems are designed and analyzed utilizing the simulation model. The first is an output feedback proportional-integral linear controller designed using linear quadratic regulator techniques. The second is a model reference adaptive controller (MRAC) which augments this baseline linear controller with an adaptive element. The performance and robustness of each controller are analyzed through simulated time responses to angle-of-attack and bank angle commands, while various uncertainties are introduced. The MRAC architecture enables the controller to adapt in a nonlinear fashion to deviations from the desired response, allowing for improved tracking performance, stability, and robustness.
Book Synopsis Disturbance Observer-Based Control by : Shihua Li
Download or read book Disturbance Observer-Based Control written by Shihua Li and published by CRC Press. This book was released on 2016-04-19 with total page 342 pages. Available in PDF, EPUB and Kindle. Book excerpt: Due to its abilities to compensate disturbances and uncertainties, disturbance observer based control (DOBC) is regarded as one of the most promising approaches for disturbance-attenuation. One of the first books on DOBC, Disturbance Observer Based Control: Methods and Applications presents novel theory results as well as best practices for applica
Book Synopsis Adaptive Control of Nonminimum Phase Aerospace Vehicles by : Anusha Mannava
Download or read book Adaptive Control of Nonminimum Phase Aerospace Vehicles written by Anusha Mannava and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: In the second part, control design for HSV is attempted through a weaker coupling, i.e. by lift control. An internal model is used for redefining tracking errors and forming a loop interconnection with pitch angle and pitch-rate. This loop generates zero dynamics which must be stabilized. The pitch dynamics are steered towards a command input by selecting the input to the internal model. The internal model is stabilized by the selection of the command input to the pitch dynamics. This successive redefinition of the regulated outputs between the nested zero dynamics is the critical design element for overall system stability. The loop interconnection between the internal model and the pitch dynamics is stabilized by a small-gain analysis. In this design, coefficients of all three-lift,drag and moment coefficients are estimated by adaptive update laws. The main contribution of this dissertation is a demonstration of adaptive control design for nonlinear nonminimum phase systems using only thrust and elevator deflection as control inputs with the air-breathing hypersonic vehicle as a case study.
Book Synopsis L1 Adaptive Control Theory by : Naira Hovakimyan
Download or read book L1 Adaptive Control Theory written by Naira Hovakimyan and published by SIAM. This book was released on 2010-09-30 with total page 333 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contains results not yet published in technical journals and conference proceedings.
Book Synopsis Control Oriented Modelling and Nonlinear Control Design for an Air-breathing Hypersonic Vehicle by : Jason Terry Parker
Download or read book Control Oriented Modelling and Nonlinear Control Design for an Air-breathing Hypersonic Vehicle written by Jason Terry Parker and published by . This book was released on 2006 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: This thesis describes control oriented modelling, i.e. the development of a model which is amenable to control design, of an air-breathing hypersonic vehicle and nonlinear control design based on the constructed model. The full simulation model, or truth model, includes intricate couplings between the engine dynamics and the flight dynamics, along with complex interplay between the flexible and rigid modes of the vehicle. Furthermore, this model is found to be unstable and non-minimum phase with respect to the variables to be controlled. By replacing the complex force and moment functions with curve fitted approximations, neglecting certain weaker couplings, resorting to dynamic extension at the input side, and neglecting slower portions of the system dynamics, a control oriented model with full vector relative degree with respect to the regulated output is obtained. Standard dynamic inversion can then be applied to this model, resulting in approximate linearization of the input/output map of the truth model. A robust outer loop control is then designed using LQR with integral augmentation in a model reference scheme. Simulation results demonstrate that this technique achieves excellent tracking performance even in the presence of small plant parameter variations. The fidelity of the truth model is then increased by including additional flexible effects which render the original control design ineffective. A more elaborate control approach with an additional actuator is then employed to compensate for these new flexible effects, and simulation results which include mild plant parameter variations are presented.
Book Synopsis Proceedings of 3rd 2023 International Conference on Autonomous Unmanned Systems (3rd ICAUS 2023) by : Yi Qu
Download or read book Proceedings of 3rd 2023 International Conference on Autonomous Unmanned Systems (3rd ICAUS 2023) written by Yi Qu and published by Springer Nature. This book was released on with total page 679 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Adaptive Dynamic Programming: Single and Multiple Controllers by : Ruizhuo Song
Download or read book Adaptive Dynamic Programming: Single and Multiple Controllers written by Ruizhuo Song and published by Springer. This book was released on 2018-12-28 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents a class of novel optimal control methods and games schemes based on adaptive dynamic programming techniques. For systems with one control input, the ADP-based optimal control is designed for different objectives, while for systems with multi-players, the optimal control inputs are proposed based on games. In order to verify the effectiveness of the proposed methods, the book analyzes the properties of the adaptive dynamic programming methods, including convergence of the iterative value functions and the stability of the system under the iterative control laws. Further, to substantiate the mathematical analysis, it presents various application examples, which provide reference to real-world practices.
Book Synopsis Proceedings of the 6th China Aeronautical Science and Technology Conference by : Chinese Aeronautical Society
Download or read book Proceedings of the 6th China Aeronautical Science and Technology Conference written by Chinese Aeronautical Society and published by Springer Nature. This book was released on 2024-01-07 with total page 711 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book contains the original peer-reviewed research papers presented at the 6th China Aeronautical Science and Technology Conference held in Wuzhen, Zhejiang Province, China, in September 2023. Topics covered include but are not limited to Navigation/Guidance and Control Technology, Aircraft Design and Overall Optimisation of Key Technologies, Aviation Testing Technology, Airborne Systems/Electromechanical Technology, Structural Design, Aerodynamics and Flight Mechanics, Advanced Aviation Materials and Manufacturing Technology, Advanced Aviation Propulsion Technology, and Civil Aviation Transportation. The papers presented here share the latest findings in aviation science and technology, making the book a valuable resource for researchers, engineers and students in related fields.
Book Synopsis Robust Nonlinear Control System Design for Hypersonic Flight Vehicles by : Obaid Ur Rehman
Download or read book Robust Nonlinear Control System Design for Hypersonic Flight Vehicles written by Obaid Ur Rehman and published by . This book was released on 2011 with total page 442 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis develops a new nonlinear robust control design procedure which addresses some of the challenges associated with the control of uncertain nonlinear system and applies the proposed method to tracking control of an Air-breathing Hypersonic Flight Vehicle (AHFV). The AHFV is a highly nonlinear system and the combination of nonlinear dynamics, parameter uncertainty and complex constraints make the flight control design a challenging task for this type of vehicle. The main contribution of this thesis lies in the fact that it presents a robust feedback linerization based strategy which solves the control issue of a class of nonlinear systems subject to parametric uncertainty. The method is effectively applied to the tracking control of an AHFV. It is also demonstrated that the proposed approach can be used to design a single robust controller for a large flight envelope rather than using several gain scheduled controllers. This research, firstly presents three different approaches to develop linearized uncertainty models for a class of nonlinear systems using a robust feedback lnearization method. The feedback linearization approach to linearize the nonlinear dynamics has some advantages over the point linearization (Jacobian linearization) method. However, the feedback linearization method only linearizes the nominal model of a system and in the presence of uncertainty in the model the exact linearization is not possible. In this thesis, we present a robust approach to deal with the nonlinearities arising from the uncertainties in the system and use a nonlinear AHFV model to demonstrate the effectiveness of the method. Besides parametric uncertainty, due to the presence of body-integrated propulsion system, and the flexible modes, the nonlinear model of AHFV does not possess full relative degree. Any attempt to feedback linearize this nonlinear model will result into having input term in low order derivatives of the system output. In this research, we strategically remove the coupling and flexible effects from the nonlinear model and simplify the model in such a way that the full relative degree condition is satisfied. In the development of linearized uncertainty model for an AHFV the conventional feedback linearization approach is used to remove the known nonlinearities from the simplified system model and the nonlinearities arising from the uncertainties are treated in three different ways. In the first method, nonlinear uncertainties are linearized using Taylor expansion at an arbitrary point by considering a structured representation of uncertainties. This lienarization approach approximates the actual nonlinear uncertainty by considering only the first order terms and neglecting all the higher order terms. For the linearized model, a minimax Linear Quadratic Regulator (LQR) controller combined with feedback linearization law is proposed to fulfill the velocity and altitude tracking requirements of an AHFV. In the second method, an unstructured uncertainty representation is considered and a minimax Linear Quadratic Gaussian (LQG) controller combined with feedback linearization law is proposed for the same tracking requirements. In the third, method the nonlinear uncertainty terms are linearized at an arbitrary point using the generalized mean value theorem. The main advantages of using this approach are that upper bound on the uncertainties can be obtained by both structured and unstructured uncertainty representations and there is no need to ignore higher order uncertainty terms. The uncertain linearized models obtained from this method are followed by guaranteed cost and minimax LQR controllers combined with feedback linearization law. Rigorous simulations using actual nonlinear model for all the above methods are presented in the thesis to analyze the effectiveness of these controllers. These simulations have considered several cases of uncertainties for a step change in the reference commands. In order to see the robustness properties of the proposed robust scheme a Monte-Calro based simulation is also presented by considering the given bound on the uncertain parameters. Also, in order to demonstrate the effectiveness of the approach for a large flight envelope, several simulations are performed to observe the tracking response for the given reference trajectories in a large flight envelope.
Book Synopsis Proceedings of 2022 International Conference on Autonomous Unmanned Systems (ICAUS 2022) by : Wenxing Fu
Download or read book Proceedings of 2022 International Conference on Autonomous Unmanned Systems (ICAUS 2022) written by Wenxing Fu and published by Springer Nature. This book was released on 2023-03-10 with total page 3985 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book includes original, peer-reviewed research papers from the ICAUS 2022, which offers a unique and interesting platform for scientists, engineers and practitioners throughout the world to present and share their most recent research and innovative ideas. The aim of the ICAUS 2022 is to stimulate researchers active in the areas pertinent to intelligent unmanned systems. The topics covered include but are not limited to Unmanned Aerial/Ground/Surface/Underwater Systems, Robotic, Autonomous Control/Navigation and Positioning/ Architecture, Energy and Task Planning and Effectiveness Evaluation Technologies, Artificial Intelligence Algorithm/Bionic Technology and Its Application in Unmanned Systems. The papers showcased here share the latest findings on Unmanned Systems, Robotics, Automation, Intelligent Systems, Control Systems, Integrated Networks, Modeling and Simulation. It makes the book a valuable asset for researchers, engineers, and university students alike.
Book Synopsis Control Design for a Non-minimum Phase Hypersonic Vehicle Model by : Thomas McKenna
Download or read book Control Design for a Non-minimum Phase Hypersonic Vehicle Model written by Thomas McKenna and published by . This book was released on 2016 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Air-breathing hypersonic vehicles are emerging as a method for cost-efficient access to space. Great strides have recently been made in the field of hypersonic vehicles, however the unique dynamics of the vehicles present challenges for control design. In this thesis, a nonlinear controller for a hypersonic vehicle model is designed using the Indirect Manifold Construction approach. The high fidelity hypersonic vehicle model considered in this thesis includes many of the challenging effects of hypersonic flight. The main challenge to control design is the vehicle's unstable internal dynamics. This non-minimum phase behavior prevents the use of many standard forms of nonlinear control techniques. The nonlinear controller developed in this thesis following the Indirect Manifold Construction approach uses a hierarchical control design to force outputs to commanded values while ensuring the internal dynamics of the system remain stable. The nonlinear controller is shown to be effective in simulation. The closed loop system is also shown to be stable through a Lyapunov based stability analysis.
Book Synopsis Advances in Guidance, Navigation and Control by : Liang Yan
Download or read book Advances in Guidance, Navigation and Control written by Liang Yan and published by Springer Nature. This book was released on 2021-11-12 with total page 5416 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book features the latest theoretical results and techniques in the field of guidance, navigation, and control (GNC) of vehicles and aircraft. It covers a range of topics, including, but not limited to, intelligent computing communication and control; new methods of navigation, estimation, and tracking; control of multiple moving objects; manned and autonomous unmanned systems; guidance, navigation, and control of miniature aircraft; and sensor systems for guidance, navigation, and control. Presenting recent advances in the form of illustrations, tables, and text, it also provides detailed information of a number of the studies, to offer readers insights for their own research. In addition, the book addresses fundamental concepts and studies in the development of GNC, making it a valuable resource for both beginners and researchers wanting to further their understanding of guidance, navigation, and control.
Book Synopsis Proceedings of 2016 Chinese Intelligent Systems Conference by : Yingmin Jia
Download or read book Proceedings of 2016 Chinese Intelligent Systems Conference written by Yingmin Jia and published by Springer. This book was released on 2016-09-20 with total page 615 pages. Available in PDF, EPUB and Kindle. Book excerpt: These proceedings present selected research papers from CISC’16, held in Xiamen, China. The topics include Multi-agent system, Evolutionary Computation, Artificial Intelligence, Complex systems, Computation intelligence and soft computing, Intelligent control, Advanced control technology, Robotics and applications, Intelligent information processing, Iterative learning control, Machine Learning, and etc. Engineers and researchers from academia, industry, and government can get an insight view of the solutions combining ideas from multiple disciplines in the field of intelligent systems.
Book Synopsis Nonlinear Adaptive Dynamic Inversion Control for Hypersonic Vehicles by : Elizabeth Rollins
Download or read book Nonlinear Adaptive Dynamic Inversion Control for Hypersonic Vehicles written by Elizabeth Rollins and published by . This book was released on 2014 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Because of the widely varying flight conditions in which hypersonic vehicles operate and certain aspects unique to hypersonic flight, the development of control architectures for these vehicles presents a challenge. Previous work on control design for hypersonic vehicles often has involved linearized or simplified nonlinear dynamical models of the aircraft. This dissertation retains the nonlinear dynamics in the design of the controller for a generic hypersonic vehicle model and develops nonlinear adaptive dynamic inversion control architecture with a control allocation scheme. A robustness analysis is performed on the initial controller design, which shows that the controller is able to handle time delays, perturbations in stability derivatives, and reduced control surface effectiveness while maintaining tracking performance. One particular safety concern in hypersonic flight is inlet unstarts, which not only produce a significant decrease in the thrust but also can lead to loss of control and possibly the loss of the vehicle. This dissertation focuses on the prevention of inlet unstarts that are triggered by an altered flow that fails to pass through the throat of the engine because the aircraft has exceeded limits on angle-of-attack and sideslip angle. To prevent undesirable inlet unstart events, the nonlinear adaptive dynamic inversion control architecture is given the ability to enforce state constraints. Because several phenomena can cause inlet unstarts, the control architecture also is tested to determine if the controller is able to maintain reference trajectory tracking and to prevent the loss of the vehicle should an inlet unstart occur. Additionally, a fault-tolerant control capability is added to the control architecture so that the vehicle can handle the failure of one or more control surfaces. The tracking performance of the nonlinear adaptive dynamic inversion control architecture is analyzed for the cases of enforcement of state constraints, control surface failures, and inlet unstarts. In all three cases, the control architecture is able to track reference trajectories with minimal to no degradation in performance. Limitations were discovered in the case of the controller that enforces state constraints in terms of the trajectories that can be tracked when combined with fault-tolerant control. However, the results indicate that the nonlinear adaptive dynamic inversion controller is able to achieve tracking performance in the presence of the uncertainties and inlet unstarts conditions studied in this dissertation. The electronic version of this dissertation is accessible from http://hdl.handle.net/1969.1/151679
