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American control Conference

作者： Rata Suwantong Sylvain Bertrand Didier Dumur Dominique Beauvois Department of System Design and Performance Evaluation ONERA-The French Aerospace-lab F-91761 Palaiseau France Department of Automatic Control E3S SUPELEC 91192 Gif-sur-Yvette France

ISBN: (纸本)9781479932757

In this paper, a Moving Horizon Estimator with pre-estimation (MHE-PE) is proposed for discrete-time nonlinear systems under bounded noise. While the classical Moving Horizon Estimator (MHE) compensates for model errors by estimating the process noise sequence over the horizon via optimization, the MHE-PE does it using an auxiliary estimator. The MHE-PE is shown to require significantly less computation time compared to the MHE, while providing the same order of magnitude of estimation errors. The stability of the estimation errors of the MHE-PE is also proven and an upper bound on its estimation errors is derived. Performances of the MHE-PE is illustrated via a simulation example of pressure estimation in a gas-phase reversible reaction.

关键词： Horizon Moving computational time model error beyond visual range

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Limit-cycles prevention via multiple H∞ constraints with an application to anti-windup design

Limit-cycles prevention via multiple H∞ constraints with an...

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9th IFAC Symposium on Nonlinear control systems, NOLCOS 2013

作者： Biannic, Jean-Marc ONERA French Aerospace Lab. System Control Flight Dynamics Department F-31055 Toulouse Cedex France

ISBN: (纸本)9783902823472

Rate and magnitude control limitations are often responsible for the apparition of undesired limit-cycles in the resulting nonlinear closed-loop system. Based on the well- known describing function approach, it is shown in this paper that such limit cycles can be avoided as soon as H∞ constraints are simultaneously satisfied by appropriately chosen linear interconnections. This result is then used to design anti-windup compensators. © IFAC.

关键词： Nonlinear control systems

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Limit-cycles prevention via multiple H ∞ constraints with an application to anti-windup design

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IFAC Proceedings Volumes 2013年第23期46卷 640-645页

作者： Jean-Marc Biannic ONERA The French Aerospace Lab. System Control and Flight Dynamics Department BP 74025 F-31055 Toulouse Cedex France

Rate and magnitude control limitations are often responsible for the apparition of undesired limit-cycles in the resulting nonlinear closed-loop system. Based on the well-known describing function approach, it is shown in this paper that such limit cycles can be avoided as soon as H ∞ constraints are simultaneously satisfied by appropriately chosen linear interconnections. This result is then used to design anti-windup compensators.

关键词： Limit cycles anti-windup saturations H ∞ control

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IMMUNE project: An overview

IMMUNE project: An overview

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18th IFAC Symposium on Automatic control in aerospace, ACA 2010

作者： Döll, C. Hardier, G. Varga, A. Kappenberger, C. ONERA French Aerospace Lab. System Control and Flight Dynamics Department BP 74025 F-31055 Toulouse Cedex 4 France DLR German Aerospace Center Robotics and Mechatronics Department Münchner Str. 20 D-82234 Weßling Germany DLR German Aerospace Center Flight Systems Department Lilienthalplatz 7 D-38108 Braunschweig Germany

ISBN: (纸本)9783902661968

The IMMUNE project (Intelligent Monitoring and Managing of UNexpected Events) focuses on basic research regarding event monitoring and event tolerant control. Event detection methods and control law reconfiguration approaches have been investigated for their applicability in the context of developing advanced aircraft flight control systems. For promising methods, prototype software tools have been implemented in a desktop simulation environment to serve as basis for evaluation studies.

关键词： Fault detection

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IMMUNE project : An overview

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IFAC Proceedings Volumes 2010年第15期43卷 434-439页

作者： C. Döll G. Hardier A. Varga C. Kappenberger ONERA The French Aerospace Lab System Control and Flight Dynamics Department BP 74025 F-31055 Toulouse Cedex 4 France DLR German Aerospace Center Robotics and Mechatronics Department Münchner Str. 20 D-82234 Weßling Germany DLR German Aerospace Center Flight Systems Department Lilienthalplatz 7 D-38108 Braunschweig Germany

Abstract The IMMUNE project (Intelligent Monitoring and Managing of UNexpected Events) focuses on basic research regarding event monitoring and event tolerant control. Event detection methods and control law reconfiguration approaches have been investigated for their applicability in the context of developing advanced aircraft flight control systems. For promising methods, prototype software tools have been implemented in a desktop simulation environment to serve as basis for evaluation studies.

关键词： fault detection and isolation parameter identification control law reconfiguration adaptive control supervisor

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Modelling of the 3-Dof nonlinear aircraft behaviour via small standard forms

Modelling of the 3-Dof nonlinear aircraft behaviour via smal...

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26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008

作者： Döll, Carsten Berard, Caroline ONERA The French Aerospace Lab Department of System Control and Flight Dynamics 2 av Edouard Belin BP 4025 F-31055 Tolouse France The French Institute for Aeronautics Department of Control 10 av Edouard Belin BP 4032 F-31055 Tolouse France

ISBN: (纸本)9781605607153

The objective of this paper is to illustrate that the standard form or Linear Fractional Transformation LFT framework is a unique and powerful framework to treat with nonlinear aircraft behaviour during flight control law synthesis and analysis. Within this paper, a precise and as small as possible LFT for a nonlinear 3-DOF aircraft with time varying parameters is derived. This LFT is validated both in a linear and nonlinear framework 1.

关键词： Linear transformations

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Comparison of GPS tracking loop performance in high dynamic condition with nonlinear filtering techniques

Comparison of GPS tracking loop performance in high dynamic ...

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21st International Technical Meeting of the Satellite Division of the Institute of Navigation, ION GNSS 2008

作者： Im, Sung-Hyuck Song, Jong-Hwa Jee, Gyu-In Park, Chan-Gook Navigation and Control System Lab. Konkuk University Seoul 143-701 Korea Republic of Dept. of Electronics Engineering Konkuk University Seoul 143-701 Korea Republic of School of Mechanical and Aerospace Engineering Seoul National University Seoul 143-701 Korea Republic of

ISBN: (纸本)9781605606897

The conventional GPS tracking loop is optimal in Maximum likelihood Estimation (MLE), respectively. It well works in normal signal to noise ratio (SNR) and signal dynamics within the tracking loop bandwidth. But, when the receiver operates in high dynamic environment, discriminator linearity doesn't maintain and tracking loop error increase. In the previous rearch, several algorithms were proposed to overcome these problems such as EKF based tracking loop, grid method. In the previous paper [Gee, ENC 2005], LQG based GPS receiver tracking loop is developed using EKF and Linear Quadratic Regulator (LQR). The EKF estimate the range rate, code phase, carrier phase error and navigation bit from inphase and quadrature measurement. And LQR calculate the optimal DCO input using pre-calculated steady state feedback gain. It had good tracking performance than conventional tracking loop in normal condition because it is designed to consider correlation of code and carrier tracking loop. But there is problem about nonlinearity of measurement model as ever. In this paper, LQG based GPS tracking loop is implemented using nonlinear filtering techniques, i.e. Unscented Kalman Filter (UKF) and Particle Filter (PF). Also, the implemented algorithm performance is evaluated and compared. In the EKF, the measurement equations are linearized to the first order Taylor series in order to apply the Kalman filter, which is supposed to linear Gaussian systems. Instead of truncating the nonlinear measurement equation the UKF and PF approximate the distribution of the state deterministically and randomly, with a finite set of samples, and then propagate these points or particles through the original nonlinear functions, respectively. Because the nonlinear functions are used without approximation, it provides the better performance.

关键词： Maximum likelihood estimation

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LFT modelling of the 2-DOF longitudinal nonlinear aircraft behaviour

LFT modelling of the 2-DOF longitudinal nonlinear aircraft b...

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IEEE International Symposium on Computer Aided control system Design (CACSD)

作者： Carsten Doll Caroline Berard Andreas Knauf Jean-Marc Biannic Department of System Control and Flight Dynamics DCSD ONERA The French Aerospace Lab TOULOUSE France Common ONERA–ISAE Research Group CSDV for System Control and Flight Dynamics Department of System Control and Flight Dynamics DCSD ONERA French Aero Space Laboratory Toulouse France Department of Control 10 ISAE (former SUPAERO) The French Institute for Aeronautics TOULOUSE France

ISBN: (纸本)9781424422210

The objective of this paper is to illustrate that the standard form or Linear Fractional Transformation LFT framework is a unique and powerful framework to treat with nonlinear systems during control law synthesis and analysis. It is also shown that the expression linear in the acronym LFT is too restrictive as a nonlinear behaviour can be simulated by using the LFT framework. Within this paper, a precise and as small as possible LFT for a nonlinear 2-DOF aircraft with time varying parameters is derived. This LFT is validated both in a linear and nonlinear framework.

关键词： control systems USA Councils

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Design of an Image Motion Compensation (IMC) algorithm for the Communication, Ocean, Meteorological Satellite (COMS)

Design of an Image Motion Compensation (IMC) algorithm for t...

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AIAA/AAS Astrodynamics Specialist Conference, 2006

作者： Jung, Taek-Seo Lee, Un-Seob Park, Sang-Young Choi, Yoon-Hyuk Bang, Hyo-Choong Ju, Gwanghyeok Yang, Koon-Ho Yonsei University Seoul 120-749 Korea Republic of Korea Advanced Institute of Science and Technology Daejeon 305-701 Korea Republic of Korea Aerospace Research Institute Daejeon 305-333 Korea Republic of Astrodynamics and Control Lab. Dept. of Astronomy and Space Science Flight Dynamics and Control Lab. Dept. of Aerospace Engineering Communication Satellite System Department

ISBN: (纸本)1563478226

This paper presents an Image Motion Compensation (IMC) algorithm for Korea's Communication, Ocean, and Meteorological Satellite (COMS). An IMC algorithm is a priority component of the Image Navigation and Registration (INR) system to locate and register radiometric image data. To eliminate image distortions, depointing of the imager aiming direction must be adjusted. A compensation algorithm to correct depointing caused by satellite motion is designed, and the capability of the algorithm is compared with that of existing algorithm applied to the GOES's INR system. The algorithm developed in this paper improves pointing accuracy by efficiently compensating for depointing of the imager aiming direction. Copyright © 2006 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Motion compensation

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Communication, ocean, and meteorological satellite orbit determination analysis considering maneuver scheme

Communication, ocean, and meteorological satellite orbit det...

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AIAA/AAS Astrodynamics Specialist Conference, 2006

作者： Hwang, Yoola Lee, Byoung-Sun Kim, Hae-Yeon Kim, Jaehoon Kim, Haedong Shin, Hyo-Sang Electronics and Telecommunications Research Institute Daejeon 305-350 Korea Republic of Korea Aerospace Research Institute Daejeon 305-333 Korea Republic of Korea Advanced Institute of Science and Technology Daejeon 305-701 Korea Republic of Satellite Ground Control System Team Korea Republic of AIAA United States AAS Norway Korea Aerospace Research Institute Korea Republic of Flight Dynamics and Control Lab. Aerospace Engineering Korea Republic of

ISBN: (纸本)1563478226

Orbit determination (OD) analysis for geostationary Communications, Ocean, and Meteorological Satellite (COMS) is presented. Since the orbital longitude of COMS is close to that of satellite tracking site, geometric singularity affects observability. For OD, we fix velocity increment by the wheel off-loading maneuver, and the azimuth angle tracking bias is not estimated because of observability problem. Final epoch of the propagated OD based on different data arc length is used for two-day orbit prediction. The difference between truth and 48-hour predicted orbit that contains the OD error shows 4-18 km Root-Sum-Squares (RSS) in 3-D sense (one sigma) in spite of the singularity problem. Thus an operational Orbit Determination and prediction (ODP) system for COMS fulfills the requirement for 18 km RSS (one sigma) predicted positioning knowledge. Copyright © 2006 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Space research

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