This paper deals with the application of receding horizon methods to the simplified model of a flight control experiment developed at Cal Tech. The dynamics of the system are representative of a Vertical Landing and T...
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This paper deals with the application of receding horizon methods to the simplified model of a flight control experiment developed at Cal Tech. The dynamics of the system are representative of a Vertical Landing and Take off (VTOL) aircraft, such as a Harrier around hover. The adopted control methodology is a hybrid of receding horizon techniques and control Lyapunov Function (CLF) based ideas. First a CLF is found, and then, by using the CLF as the terminal cost in the receding horizon optimization, stability is guaranteed. It is shown that if the horizon length is long enough, a simple choice of CLF, i.e., the one obtained from Jacobian linearization of the dynamics at hover, will achieve a good performance. However, if due to computational costs, longer time horizons are not possible, stability can be guaranteed by applying the CLF obtained using Quasi-LPV methods, as a terminal costs. Several numerical simulations for different time horizons are presented to illustrate the effectiveness of the discussed methods.
In many industrial fields, there are still difficulties in adjusting parameters of nonlinear systems. In order to cope with the difficulties, this paper proposes that adjustment should be divided into choosing appropr...
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In many industrial fields, there are still difficulties in adjusting parameters of nonlinear systems. In order to cope with the difficulties, this paper proposes that adjustment should be divided into choosing appropriate parameters, calculating the amount of modification of the chosen parameters, and dealing with nonlinear phenomena. An adjustment rule which describes how to choose appropriate parameter in every situation is generated by using characteristics of influences of parameters. The calculation for the modification is carried out on trial just before the chosen parameter is really modified for adjustment. Nonlinear phenomena during adjustment can be categorized into vibration and inert-zone, and they should be evaded by extra treatments prepared beforehand. In addition, a sufficient condition for convergence to the desired state is explained in the case that the characteristics of the objected system are known. Finally, an example shows that the proposed method is applicable to unknown nonlinear static systems.
This article explores the application of non-linear tuning rules estimators to a known relay-oscillation tuner. Two approaches were tested. One uses non-linear functions to approximate the desirable controller paramet...
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This article explores the application of non-linear tuning rules estimators to a known relay-oscillation tuner. Two approaches were tested. One uses non-linear functions to approximate the desirable controller parameters. The other incorporates Neural Network for computing process model and controller parameters. As a basis for computation, the Ultimate Gain, Ultimate Period, and Process Dead Time are defined during the tuning experiment. Neural Network is trained in simulation using these process parameters as inputs and known process model parameters and desired PID controller tuning parameters as outputs. The PID tuning parameters are defined from the simulation process model using IMC or Lambda tuning rules. This concept was implemented in a scalable industrial controlsystem. Simulation test results show a vast improvement in model identification and control loop performance as compared to previous relay-oscillation based tuning approaches.
This paper describes a method for rapidly optimizing the uniformity of thin films deposited or grown on semiconductor wafers in batch thermal reactors. The method allows process recipes to be automatically optimized i...
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This paper describes a method for rapidly optimizing the uniformity of thin films deposited or grown on semiconductor wafers in batch thermal reactors. The method allows process recipes to be automatically optimized in as few as two process runs. Challenges associated with optimizing process recipes to yield uniform final film thickness on all wafers processed in each batch are presented, and the uniformity problem is formulated as a run-to-run control problem. A solution to this problem is presented that includes a run-to-run process model, an estimator, and a controller. This solution has been implemented in a software package that is used by engineers in the field to optimize process recipes. Measured results are presented from the optimization of two different process recipes.
This paper presents analysis of the effect of actuation on the combustor dynamics. Two different categories of actuators are studied: flow sources, e.g., acoustic speakers, and heat sources, e.g., fuel injectors. Thes...
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This paper presents analysis of the effect of actuation on the combustor dynamics. Two different categories of actuators are studied: flow sources, e.g., acoustic speakers, and heat sources, e.g., fuel injectors. These sources are modeled in the conservation equations and a finite dimensional model is obtained. Two methods of analysis are used to gain insight into the physics of actuation, and its stabilizing/destabilizing effect on the combustor through feedback control. The first is the energy method which is used here in a novel way to explain intricate work exchanges between the different dynamic components of the system: the acoustics, the flame, and the actuator. The energy analysis is used also to quantify the `useful' and `wasted' work generated by actuators. A more revealing method of analysis is the dynamic representation of the combustor as an oscillator, and is shown to be the basis of any optimal control analysis.
This paper approaches and solves a spectrum of problems in the motion control of highly-maneuverable aircraft. In particular, analysis and identification, as well as optimization and control of advanced aircraft are r...
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This paper approaches and solves a spectrum of problems in the motion control of highly-maneuverable aircraft. In particular, analysis and identification, as well as optimization and control of advanced aircraft are researched to attain the specified flying and handling qualities (agility and maneuverability, controllability and other pilotage quantities), guarantee survivability, damage adaptation and recovery, improve mission effectiveness, etc. This paper reports a new completely automated setup to perform real-time identification and control with failure accommodation. Innovative identification and design methods are applied. It is shown that the required aircraft performance through the specified operational envelope at various attitudes, including high-angle-of-attack regimes, can be achieved through real-time nonlinear analysis, identification, and control reconfiguration. An example is studied to demonstrate the practical use of the analytical and numerical results. In particular, the feasibility and viability of the identification and design methods developed, as well as the computational effectiveness and numerical stability of the algorithms, are illustrated. It is documented that the decision making process can be performed in real-time.
This paper deals with special-Purpose Devices Using Techniques of Discontinuous control and Setting Adjustment (DC&SA) in control Applications. DC&SA are result of a synthesis of two independent concepts of co...
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This paper deals with special-Purpose Devices Using Techniques of Discontinuous control and Setting Adjustment (DC&SA) in control Applications. DC&SA are result of a synthesis of two independent concepts of control: the Sliding Mode and Optimal Rating. This paper is aimed not only at stating and developing the results obtained in the sphere of discontinuous systemdesign, but also at presenting these results in close correlation with the basic concepts, problems and methods of theoretical aspects of present-day control theory. The discontinuity of control results in a discontinuity part of the differential equations describing the system motions. If such discontinuities are deliberately introduced on certain surfaces in the system state space, then motions in a sliding mode may occur in the system. To improve efficiency of practical implementation, long-period fiber Bragg Gratings, used as sensors, are regarded as electronic elements having a discontinuity-switching mode where the sliding modes are the basic motions. Implementation of this approach implies the knowledge of the conditions of the occurrence of sliding mode, for which purpose a sliding mode indicator has been developed. The state vector of the system is unknown. In this connection we designed spatial observer who uses measurements as basic data, and it will help to identificate the state vector of the system.
This paper presents an active noise control (ANC) algorithm using genetic algorithm with infinite impulse response (IIR) filter structure. Stochastic gradient algorithms such as least mean square (LMS) algorithm are c...
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This paper presents an active noise control (ANC) algorithm using genetic algorithm with infinite impulse response (IIR) filter structure. Stochastic gradient algorithms such as least mean square (LMS) algorithm are conventionally used for their simplicity and stability. But these algorithms have disadvantages of local minimum and large eigenvalue disparity of input signal's autocorrelation matrix. To solve those problems, several researches has been made to adaptive filtering schemes based on genetic algorithm. But their application is limited to the system that is able to know desired signal directly. In general active noise and vibration controlsystems are not be able to sense desired signal directly, so they have some difficulties or problems such that learning sample set is proportional to population size. Proposed active controller is composed of genetic controllers that can learn by one sample set per one generation. This structure can be properly applied to active controlsystem. computer simulations show that proposed genetic structured IIR active controller has more optimal result to feedforward active noise controlsystems.
Conceptually, Fuzzy Logic, which has drawn a great deal of attention recently, possesses the quality of simplicity. However, its early applications relied on trial and error in selecting either the fuzzy membership fu...
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Conceptually, Fuzzy Logic, which has drawn a great deal of attention recently, possesses the quality of simplicity. However, its early applications relied on trial and error in selecting either the fuzzy membership functions or the fuzzy rules. This made it depend rather too heavily on expert knowledge which may not always be available. Hence, a self-tuning or an adaptive Fuzzy Logic controller (FLC) such as Adaptive Neuro-Fuzzy Inference system (ANFIS) removes this stringent requirement. This paper demonstrates the application of ANFIS to a 160 Mw nonlinear Multi-Input Multi-Output (MIMO) steam boiler-turbine unit. The space of operating conditions of the plant is partitioned into five regions. For each of the regions an optimal controller is designed. The resulting five linear controllers are used to train the ANFIS. Simulation results showed that the fuzzy controller closely reproduced the optimal performance in each of the design points and surpassed any single linear controller in these operating regions. These results also revealed the robustness of the FLC to parameter variations.
This paper presents the application of a command shaping control method for suppressing payload swing caused by operator commanded maneuvers, in rotary, ship-based, boom cranes. The crane configuration investigated, c...
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This paper presents the application of a command shaping control method for suppressing payload swing caused by operator commanded maneuvers, in rotary, ship-based, boom cranes. The crane configuration investigated, consists of a payload mass that swings on the end of a spherical pendulum of varying lift-line length (hoisting). The lift-line is attached to a boom capable of elevation (luffing) and rotation about a vertical axis (slewing). Positioning of the payload is accomplished through luff, slew and hoist commands issued in real-time by an operator. Payload oscillation is excited by a nonlinear combination of the operator's inputs. It is shown that linear filters are sufficient under certain conditions. The command shaping strategy, consisting of a time-varying filter, reduces payload oscillation by 18 dB in experiments using the 1/16th scale Navy Crane Testbed at Sandia National Laboratories.
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