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

{"title":"Wavelets and operators in the Clifford algebra framework","authors":"B. Jawerth, M. Mitrea","doi":"10.1109/AEROCS.1993.720910","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720910","url":null,"abstract":"The main aim of this note is to present some applications of the discrete wavelet transform in the Clifford algebra framework to the study of some singular integral operators arising in connections with partial differential equations on non-smooth domains.","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":"125259161","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":"Simplicial Stability Analysis of an Unstable Plant with Adaptive Perturbation Control","authors":"R.D. Colgren","doi":"10.1109/AEROCS.1993.720968","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720968","url":null,"abstract":"This paper covers a new method for the stability analysis of a nonlinear system using simplicial algorithms. The system analyzed is a unstable first order plant, driven by a Bang-Bang actuator. A describing function model of the actuator is used in this analysis. This system is implemented on a digital computer, and in analog circuit form, to demonstrate the practicality of the method.","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":"131308970","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":"Modeling Analog Sun Sensor Current Output","authors":"C. Cosner, D. S. Barker","doi":"10.1109/AEROCS.1993.720915","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720915","url":null,"abstract":"This paper presents the derivation of a new sun sensor model and compares the predicted output to unit test data. The new model has been derived for a generalized rotation of the sensor with respect to the principal axes of the spacecraft. The modeling of the variation of the space output as a general function of the kinematics of the rotation of the sensor and an arbitrary sun location was initially solved using spherical geometry. However, the execution time required for this solution was unacceptable for the strict time constraints of real-time simulation. Therefore, a second method of modeling was derived in cartesian space, which proved to be a concise solution well suited to real-time simulation. This new analog sun sensor model generates predicted output for given sun elevation and azimuth, and sensor orientation angles based on a general analytical function. By varying the sensor sweep angle, the user can construct a current pulse that is accurate over the full range of the sensor.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"42 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":"131319539","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":"Disturbance Attenuation for Guidance and Control","authors":"J. L. Speyert","doi":"10.1109/AEROCS.1993.721001","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721001","url":null,"abstract":"The formulation of a disturbance attenuation problem provides a conceptual structure for the development of robust high performance guidance and control schemes in the presence of large uncertainties in the process and measurement disturbances. The disturbance attenuation problem is to find a feedback controller based upon the measurement output which guarantees that the disturbance attenuation function is bounded below some value for all admissible input disturbances. The disturbance attenuation function is an input-output relationship between a norm of a desired output, such as tracking error and/or control effort, to a norm associated with the input disturbance. This problem is usually solved by converting it to a zero-sum differential game between the controller, attempting to minimize a functional, and the disturbances acting as adversaries that maximize the performance index. By using a dynamic programming approach to differential game associated with the disturbance attenuation problem can be divided naturally into two problems. From the present time into the future and up to the terminal time, a game problem based upon perfect information naturally occurs since no actual measurements can be made, i.e., the system is causal. The solution to the dynamic programming problem is the optimal value function in terms of the state variables and time. This optimal value function is, in general, not easily generated, but in certain guidance problems it can be obtained approximately by using perturbation theory, producing solutions of high accuracy. The second half of the problem, from the initial time to the current time, is essentially viewed as a state estimation problem since the control sequence used in the past cannot be modified. The estimation problem can be viewed as dissipative with respect to a generalized energy function. An optimal accumulation function, which is the solution to the estimation dynamic programming problem, is a function of the current state and time. Some suggestions for determining suboptimal estimators are given. The final step is to maximize, with respect to the current state, the sum of the filter optimal accumulation function and the controller optimal value function. The resulting worst case state, which in the applications considered is a function of the state estimate and curvature, is used in the controller. Note that even though the worst case state is only a function of the measurement history and apriori values of the parameters, no certainty equivalence assumption is made.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"482 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":"131512315","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 Flexible Spacecraft Control System Design","authors":"F. Bauer, Ching-Fang Lin, Q. Liu, Qinghong Wang","doi":"10.1109/AEROCS.1993.720900","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720900","url":null,"abstract":"In this paper, varions robust control design methods are examined and their synergistic integration is investigated to meet the stringent performance and robustness requirements of flexible spacecraft. The robust control design methodologies are illustrated through the attitude control system design for the X-ray Timing Explorer satellite.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"217 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":"134130261","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":"Application of H-Infinity Technique","authors":"Q. Tham","doi":"10.1109/AEROCS.1993.720962","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.720962","url":null,"abstract":"A well-known example is studied. Physical interpretation is obtained. Software from the MATLAB's Robust-Control Toolbox is exercised to set the specifications on actuator gain, sensor gain and acceptable magnitude of resonance to guarantee system stability.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"574 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":"134268899","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":"Missile Autopilot Design Using a Generalized Hamiltonian Formulation","authors":"Ching-Fang Lin, J. Cloutier, J. Evers","doi":"10.1109/AEROCS.1993.721027","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721027","url":null,"abstract":"This paper presents the application of robust multivariable control to a missile autopilot design. A synergistic algorithm based on the generalized Hamiltonian formulation is applied to robust autopilot design for the HAVE DASH II missile system. The design endures significant kinematic and inertia couplings, aerodynamic parameter variations and high frequency flexible effects.","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":"132698297","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":"On global stability of quadratic state feedback controlled linear systems","authors":"Jing-Sin Liu, Shyh-Leh Chen","doi":"10.1109/AEROCS.1993.721011","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721011","url":null,"abstract":"In this article we analyze the global stability of a class of nonlinear system arising from asymptotically stable LTI single input plants controlled by quadratic state feedback. Some requirements on the quadratic feedback gain are given to reduce the possibly negative effect of the quadratic term on the internal stability for second order system. A quadratic state feedback design guideline is presented to improve the initial transient response of the original linear system.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"163 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":"133019966","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":"Low-order Controller Design of Linear Multivariable Systems Via a Classical Approach","authors":"G. Pang","doi":"10.1109/AEROCS.1993.721010","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721010","url":null,"abstract":"This paper presents a classical control system design approach, called Systematic Design Approach, for the design of multivariable feedback control systems in the frequency domain. The technique is based on singular value decomposition and handles stability, performance and robustness aspects of the design problem. The overall approach is systematic and intuitively appealing.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"21 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":"129248131","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":"Discrete Advanced Guidance for High Order Acceleration Constrained Missile and Maneuvering Target","authors":"Ilan Rusnak, L. Meir","doi":"10.1109/AEROCS.1993.721000","DOIUrl":"https://doi.org/10.1109/AEROCS.1993.721000","url":null,"abstract":"An explicit, closed form formula of discrete advanced guidance law for a linear, time-invariant, high-order and acceleration-constrained missile and a linear, time-invariant arbitrary-order, maneuvering target is derived. The formula is given in terms of the missile's transfer function and acceleration constraint, the shaping filter of the target and responses to initial conditions. Optimal full state feedback guidance law is synthesized and compared to a first order approximation for minimum and non-minimum phase missile. Simulation of a third order missile model shows the relative gain from using the full state guidance law for several values of the missile time response and acceleration constraint.","PeriodicalId":170527,"journal":{"name":"Proceedings. The First IEEE Regional Conference on Aerospace Control Systems,","volume":"123 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":"115465742","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}