Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,最新文献

{"title":"Aircraft Model Comparison For Minimum Time-To-Climb Problem","authors":"S. Ong, B. Pierson, Ching-Fang Lin","doi":"10.1109/AEROCS.1993.720978","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720978","url":null,"abstract":"Five aircraft dynamic models for a minimum time-to-climb problem are solved. The five-state model features the usual point-mass equations of motion for flight in a vertical plane. Time is the independent variable, and speed, altitude, flight path angle, range, and mass are the dependent variables. Range is used to replace time as the independent variable for the remaining four models. The last of these is the well known energy-state approximation with specific energy as the only state variable and speed as the control variable. The objective is to compare the solutions for each of the five models with regard to accuracy and computational effort.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"80 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123343627","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Optimal Eigenvalue Placement Linear Quadratic Performance","authors":"H. Sehitoglu","doi":"10.1109/AEROCS.1993.721012","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721012","url":null,"abstract":"A new design algorithm is presented for clustering eigenvalues of a dynamic system within a sector in the left hand side of the complex s-plane while minimizing a LinearQuadratic (La) performance index. The development of the algorithm is based on a simple transformation of the system into a higher order associated dynamic system. The proposed algorithm explicitly deals with the relative damping and stability performance requirements. A numerical example is also given to illustrate and compare the design method. INTRODUCTION It is well-known that the time and frequency response of a linear system is directly influenced by the relative locations of the closed loop system eigenvalues. Hence, quite often, the main goal of the control system designer is not merely to stabilize a given plant, but to shape the dynamic response by placing the closed loop eigenvalues in some pre-specified region of the left hand s-plane. In practice, the following two important timedomain requirements are often included in the performance specifications: l-Response must be sufficiently fast and smooth. 2-Response must not exhibit excessive overshoot and oscillations. The first requirement places a bound on the settling time, whereas the second one gives rise to a bound on the damping ratio, C . By enforcing these bounds, a designer can achieve a uniform degree of damping and stability. For this reason, the shaded area of Fig.(l) has been widely accepted in the control systems community as a suitable design sector. Fig(1) Design sector with damping and stability specifications Because direct optimal pole placement in the shaded area is a very difficult problem to solve, a multitute of approximate regions have been proposed in the literature [1 ] [6 ] . Some of the approximations involve circular, elliptical, parabolic, and hyperbolic as well as horizontal and vertical strips. In order to contrast and compare the contributions of this paper, two of the most related root clustering methods will be briefly discussed below. The method developed in [ 5 ] is based on the preservation of the eigenvalues and eigenvectors of the quadratic and linear functions of a matrix. For example, if the system matrix A has I = x+yj as an eig nvalue, t en the corresponding eigenvalue of A’-(r21 implies that is The asymptotic stability of A2-a I 1 9 -a2. Re(A2-a2) < 0 or x2-y2 < a2 The above inequality defines a sector to the left of a hyperbola. Clearly, by making A2-a21 stable, it is possible to place all the eigenvalues of A in the shaded region of Fig. (1) . The design procedure of [ 51 involves an iterative technique to update the quadratic weights of the LQ performance index to move the eigenvalues into the desired region. The main disadvantage of this approach is that the asym totes of the hyperbola are fixed at e=45 g . A different class of root clustering algorithms can be developed by using the following theorem; The RELATIVE STABILITY THEOREM: eigenvalues of the matrix A lie within t","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125623839","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Stability, Aim Bias Compensation and Noise Sensitivity of Phalanx Ciws Control System","authors":"D. Serakos","doi":"10.1109/AEROCS.1993.720885","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720885","url":null,"abstract":"An aiming control system which is similar to that in the Block I PHALANX CIWS is considered in this report. An important feature of this control system is that it compensates for any gun aim bias. An aim bias may be caused by variations in the gun, ammunition or environmental conditions. Design issues considered are stability, aim bias compensation and sensitivity to feedback noise. These are disparate design goals. Design tradeoffs which quantify this disparity are presented.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"67 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126018811","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Robust H/spl infin/ Controller Design of Two-link Robots","authors":"A. Mohamed, I. Busch-Vishniac","doi":"10.1109/AEROCS.1993.720989","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720989","url":null,"abstract":"This paper utilizes the H/spl infin/ synthesis for the dynamic control of two link robots system. The nonlinear robot dynamic equations are described and linearized around an operating point. The system is formulated in state space form and stabilized with a control torque scheme in which the robot motion is controlled by controlling the torque of a DC motor drive at each joint of the robot arms. Performance objectives as well as modelling errors are incorporated in the framework of controller design through choice of appropriate weighting transfer functions in the H/spl infin/ synthesis procedure. Numerous simulation results are presented to evaluate the performance and robustness of the H/spl infin/ cent roller for the two-link robots system.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115949056","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Advanced Guidance Laws for Acceleration Constrained Missile, Randomly Maneuvering Target and Noisy Measurements","authors":"Ilan Rusnak","doi":"10.1109/AEROCS.1993.721003","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721003","url":null,"abstract":"An explicit, closed form formulae of advanced guidance laws for a linear, time-invariant, acceleration-constrained arbitrary-order missile, and a linear, time-invariant, arbitrary-order, randomly maneuvering target with noisy position measurements are derived. Two approaches are presented. The first approach derives the optimal guidance law for a quadratic objective. The solution is the guidance law for deterministic system with limiting on the commanded acceleration applied on the estimated state. The second approach is based on the idea of applying the average of the input that would have been applied to the plant if the noises were known. The formulas of the different guidance laws are given in terms of the transfer function of the missile and acceleration constraint, the shaping filter of the maneuver of the target, responses to initial conditions, error variance matrix of the estimated state and weights in the criterion. It is demonstrated by simulations that although the optimal guidance law has improved performance in terms of the miss distance, the suboptimal average input guidance law consumes less energy.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131986133","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Adaptive Tracking Control for a DC Motor","authors":"S. Hwang, Robert Carmichael","doi":"10.1109/AEROCS.1993.720932","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720932","url":null,"abstract":"The objective of this paper is to design an adaptive tracking controller for a DC motor. The adaptation gains of the controller are adapted based on the MIT rule. A desired sine wave is used as a reference trajectory. The DC motor traces the reference trajectory continuously. The voltage amplitude of a sine wave is corresponding to the angular position of the DC motor shaft. In order to investigate the tracking performance of this controller, one suitable performance index is introduced for the evaluation. The effect of the reference model is also studied.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"100 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132245275","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Genetic Design of Multivariable Flight-Control Systems Using Eigenstructure Assignment","authors":"B. Porter, S. Mohamed","doi":"10.1109/AEROCS.1993.720972","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720972","url":null,"abstract":"In the design of multivariable flight-control systems, performance specifications can frequently be met by assigning appropriate closed-loop eigenstructure by means of linear feedback control. However, although various powerful algorithms for the solution of this problem of eigenstructure assignment have been proposed, no universally applicable and computationally simple design methodology has yet emerged. The use of genetic algorithms to solve this fundamental problem of eigenstructure assignment is accordingly described, and illustrated by application to the design of multivariable fright-control systems for the AFTI/F-16 aircraft.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"190 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131892564","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Fuzzy Variable Structure Controller for Chattering Reduction","authors":"A. Meystel, Y. Nisenzon, R. Nawathe","doi":"10.1109/AEROCS.1993.720936","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720936","url":null,"abstract":"In this paper a method of chattering reduction is described using a fuzzy variable structure controller. A part of the state space around the sliding surface and the origin is represented using linguistic variables. A rule based controller which decides the contribution of equivalent control and attractivity control component in the total control input is designed. Their degrees of contribution are decided based on how far the present stale is from the sliding surface and the origin of the state spate. The performance of the proposed controller is demonstrated for a second order linear time invariant system which has parameter uncertainty. The simulation results show that there is a reduction in chattering and control energy.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127817776","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"ERA Identification for a Two-link Flexible Manipulator","authors":"Anren Hu","doi":"10.1109/AEROCS.1993.720958","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720958","url":null,"abstract":"Eigensystem Realization Algorithm has been successfully applied to a two-link flexible manipulator for system identification. As has been expected, the time responses of the identified models match perfectly with those of the original one when no noise was added to the measurement data, but the responses of the identified model deviate more significantly from those of the original model as the measurement noise intensity increases.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"69 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115340806","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Quadratic Lyapunov Functions for Orbitally-Stable Systems","authors":"M. Brooks","doi":"10.1109/AEROCS.1993.721013","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721013","url":null,"abstract":"Quadratic Lyapunov functions are constructed for orbitally-stable systems. The Lyapunov functions for higher-order systems (the N-body problem) are derived from functions that were created for lower-order oscillators.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115912630","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}