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

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On the Achievable Performance of a State Feedback Nonlinear H/sub /spl inifin// Control 状态反馈非线性H/sub /spl初始化控制的可实现性能研究
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.720985
M. Lai, J. Hauser, Chih-Yung Cheng
{"title":"On the Achievable Performance of a State Feedback Nonlinear H/sub /spl inifin// Control","authors":"M. Lai, J. Hauser, Chih-Yung Cheng","doi":"10.1109/AEROCS.1993.720985","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720985","url":null,"abstract":"Based on a recent result in nonlinear H/sub /spl inifin// control [9], we discuss several important system performance indices. We propose numerical algorithms to compute guaranteed performance and to find a state feedback such that better guaranteed performance can be improved.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"40 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":"125157003","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}
引用次数: 1
Stable State-Space System Identification from Frequency Domain Data 基于频域数据的稳定状态空间系统辨识
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.721041
Chung-Wen Chen, J. Juang, G. Lee
{"title":"Stable State-Space System Identification from Frequency Domain Data","authors":"Chung-Wen Chen, J. Juang, G. Lee","doi":"10.1109/AEROCS.1993.721041","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721041","url":null,"abstract":"Due to possible distortion contained in frequency-domain data, system identification methods based on data-matching alone do not guarantee stable models. This paper presents a method of identifying a stable state-space model of a linear system from its frequency response data. It is an improvement and extension of previous work. The method first identifies a matrix-fraction description of the transfer function matrix of the system from data. Then, through forming a multi-variable observable or controllable canonical form, the method separates and replaces the unstable sub-system by a stable sub-system having approximately the same frequency response. Finally, it calculates the Markov parameters of the resulting model and obtains a state-space model through the Eigensystem Realization Algorithm.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"1 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":"130221166","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}
引用次数: 6
Hierarchical Heuristic Control with Artificial Neural Network for Modelling and Compensation 基于人工神经网络的分层启发式控制建模与补偿
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.721020
Xiaoming Xu, Junjie Li, Zhongjun Zhang
{"title":"Hierarchical Heuristic Control with Artificial Neural Network for Modelling and Compensation","authors":"Xiaoming Xu, Junjie Li, Zhongjun Zhang","doi":"10.1109/AEROCS.1993.721020","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721020","url":null,"abstract":"Xiuoming Xu Junyi Li Zhongjun Zhang 3epahnent of Automatic Control Shanghai Jim Tong University Shanghai 200036 P.B.flhina 1. INTRCjlUCTION The recently-developed hierarchical heuristic control provides a powerful approach for complicated control Groblems. Kith the hierarchical architecture, the original comples structure is decompsed into different layers. In each layer, an individual tipgroach may be spcifically developed according to its respective characteristic. Also for each layer? by .using heuristic strategy, the origjnal complexity of every layer is decomposed into different steps. Vsing a heuristic evaluation function Kith moving-horizon implementation, the complexity in each la?-er should be less than the original one? and the correspondirg strategy should 'be easier to 'be obtained and simpler to be carried out. One of the author successfully applied_ the heaistic control method to robot manipulator control'̂ . This method is extended in this :paper to a hierarchical heuristic control method combined with artificial neural network technique. .& a general algorithn, +;here still remain several problems unsolved in the heuristic control method. . The first is modelling problem. In the heuristic control method, a simplified model is required in each step. In [ l ] , a predetermined trajectory is given so that a group of linearlized models €or .manipulator may be off-line set aiong the trajectory. In general situations, such adva3:tage can not be taken. The second problem is related to compensation. Since the hzuristic soluticn is obtained based on a simplified model, the solution may be rough. .Is a result, the plant resFnse with this rough control action is undesirable,. especially in the presence of model .uncertainty. T ' I","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"3 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":"128820921","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}
引用次数: 0
Adaptive Control of an Alignment System with Nonlinear Plant Characteristics 具有非线性对象特性的对准系统的自适应控制
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.720894
D. A. Hill, S. Chand
{"title":"Adaptive Control of an Alignment System with Nonlinear Plant Characteristics","authors":"D. A. Hill, S. Chand","doi":"10.1109/AEROCS.1993.720894","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720894","url":null,"abstract":"This paper presents Model Reference Adaptive Control (MRAC) of a precision angular alignment system (small gimbaled mass) with nonlinear friction characteristics. Open loop frequency response tests yield a family of curves for different amplitude sweep generator inputs as seen in Fig. 1 giving the ratio of alignment angle output to amplifier input over frequency. These results are directly traced to nonlinear bearing friction. The goal of the control design is to regulate alignment errors to within 2 arcseconds of a given reference angle in the presence of variable friction parameters and torque disturbances. The adaptive controller is derived by considering a linearized 2nd order Plant, of relative degree 2, with variable parameters. The MRAC design is tested with nonlinear simulation using Boeing Computer Services EASY5/sup TM/.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"53 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":"130023903","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}
引用次数: 0
Constrained Optimal Estimation: An Application to Target State Estimation in the Presence of Multipath Noise 约束最优估计:多径噪声条件下目标状态估计的应用
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.720891
E. P. Bailey, E. Price
{"title":"Constrained Optimal Estimation: An Application to Target State Estimation in the Presence of Multipath Noise","authors":"E. P. Bailey, E. Price","doi":"10.1109/AEROCS.1993.720891","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720891","url":null,"abstract":"Defending a ship under attack by an incoming cruise missile requires accurate estimates of the missile's dynamic state. However, obtaining accurate estimates from radar position measurements can be difficult if the missile is flying close to the earth's surface. This is because the radar measurements of low flying targets contain multipath noise. Multipath noise is a nonstationary highly correlated, large amplitude noise that can completely obscure the true measurements and make the target appear to be below the earth's surface. Faced with this type of measurement noise, unconstrained estimators can produce estimates with negative altitude and other physically meaningless characteristics. In this paper, we present an algorithm for a constrained optimal target state estimator that incorporates the physical limitations of the missile to obtain more accurate estimates of the missile's state in the presence of multipath noise.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"9 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":"127604137","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}
引用次数: 0
Performance Needs for Advanced Kinetic Energy Missiles' Inertial Measurement Units 先进动能导弹惯性测量装置的性能需求
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.721038
A. Killen, D. Tarrant
{"title":"Performance Needs for Advanced Kinetic Energy Missiles' Inertial Measurement Units","authors":"A. Killen, D. Tarrant","doi":"10.1109/AEROCS.1993.721038","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721038","url":null,"abstract":"A large number of commercial and military applications call for the use of inertial measurement units (IMUS). These applications vary vastly, however a new era is dawning where the need for and utilization of IMUS which can navigate through steady-state high acceleration environments are growing. These instruments will have to be very near or completely solid state because of the high acceleration loading. The performance of these instruments will be characterized by broader dynamic range, minimal nonlinear effects, higher noise rejection capability, but not necessarily low drift rate performance. These performance characteristics are driven by flight times on the order of a few seconds. These instruments must also exhibit small volume, low power, and low cost. An example of this type of IMU is the one needed for the Advanced Kinetic Energy Missile (ADKEM). ADKEM is a hypervelocity multi-role tactical missile which requires inertial grade navigation performance through a 1000-g environment.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"189 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":"117324362","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}
引用次数: 1
Adaptive Estimation of a Flexible Beam 柔性梁的自适应估计
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.721046
I.G. Resen, M. Demetriou
{"title":"Adaptive Estimation of a Flexible Beam","authors":"I.G. Resen, M. Demetriou","doi":"10.1109/AEROCS.1993.721046","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721046","url":null,"abstract":"An on-line or adaptive identification scheme for a flexible beam and, more generally, second order in time infinite dimensional or distributed parameter systems, is constructed. The estimator takes the form of an infinite dimensional initial value problem for a linear evolution system whose state consists of an estimate for the plant and an estimate for the parameters. A Lyapunov estimate is used to argue state convergence. Parameter convergence is argued via the extension of the finite dimensional notion of richness or persistence of excitation. A laboratory experiment involving an aluminum beam with piezoceramic actuation at the root and proximity displacement sensors mounted alongside the beam is discussed. The purpose of the experiment is to test the feasibility of the identification scheme.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"1 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":"114269433","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}
引用次数: 1
Line of Sight Differentiation via Kalman Filter 基于卡尔曼滤波的视线分化
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.720903
R. Jaffe
{"title":"Line of Sight Differentiation via Kalman Filter","authors":"R. Jaffe","doi":"10.1109/AEROCS.1993.720903","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720903","url":null,"abstract":"Modern guidance and location systems use a Kalman Filter for target position estimation. Terminal guidance systems for missile interceptors make use of Proportional Navigation (PN), which is a guidance law based upon differentiation of the Line Of Sight (LOS). The LOS rate is determined from the estimated states by a Kalman Filter (KF) which measures the LOS angle. In this paper I show that the KF based LOS estimate is entirely equivalent to LOS differentiation with finite low frequency gain and first order roll-off at high frequency. These two departures from ideal differentiation are shown to be inherent in the KF formulation, and to be in agreement with conventional LOS implementations.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"44 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":"122418593","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}
引用次数: 0
Design of Guidance Law for Homing Missile Via Feedback Linearization 基于反馈线性化的寻的制导律设计
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.721029
Scott Bezick, Ilan Rusnak, Steven Gray
{"title":"Design of Guidance Law for Homing Missile Via Feedback Linearization","authors":"Scott Bezick, Ilan Rusnak, Steven Gray","doi":"10.1109/AEROCS.1993.721029","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721029","url":null,"abstract":"This paper examines tlhe guidance problem of an acceleration constrained homing missile when the initial missile heading is far lfrom intercept course. A representation of the kinematics and dynamics is first presented in which the system is affine in the missile's acceleration. A guidance strategy is then synthesized for the control of the feedba,ck linearized system. The implementation of the feedback linearized guidance law is discussed, and simulation results are given comparing miss distance performance of the feedback linearized guidance law to Proportionall Navigation. The simulations reveal that the feedback linauized guidance law performs approximately equal to or better than Proportional Navigation for all initial launch regions.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"45 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":"115337902","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}
引用次数: 2
A method for fuzzy rules extraction directly from numerical data 一种直接从数值数据中提取模糊规则的方法
Proceedings. The First IEEE Regional Conference on Aerospace Control Systems, Pub Date : 1993-05-25 DOI: 10.1109/AEROCS.1993.720908
M. Lan, S. Abe
{"title":"A method for fuzzy rules extraction directly from numerical data","authors":"M. Lan, S. Abe","doi":"10.1109/AEROCS.1993.720908","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720908","url":null,"abstract":"This paper discusses new method for extracting fuzzy rules directly from numerical input-output data. The method was first developed for pattern classification and then was extended for function approximation. The fuzzy rules with variable fuzzy regions are defined by activation hyperboxes wich show the existence region of data for a class and inhibition hyperboxes which inhibit the existence of data for that class. These rules are extracted from numerical data by recursively resolving overlaps between two classes. For pattern classification, the method is applied to recognition of numerals of license plates and its performance is compare with neural networks. For function approximation, the approximation accuracy of the fuzzy system is compared with that of neural networks using an operation learning application of a water purification plant.","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":"126728748","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}
引用次数: 3
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