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Novel Two-Stage Observer for Line-of-Sight Rate Estimation

JOURNAL OF GUIDANCE control AND DYNAMICS 2016年第11期39卷 2582-+页

作者： Tamhane, Bhagyashri Kurode, Shailaja Parkhi, Prasad Coll Engn Dept Elect Engn Pune 411005 Maharashtra India ARDE PGM TECH GNC Pune 411021 Maharashtra India

A two-observer scheme has been proposed using higher-order sliding mode algorithms for a general second-order system with a time-varying, uncertain, unknown parameter. The first observer was used for the varying parameter estimation and using knowledge of this estimated parameter, and the state estimation by second observer was found to be exact. Supertwisting algorithms provide robust, noise-free, finite-time convergent state estimations. The proposed scheme was found to yield accurate and fast converging estimates of the line-of-sight (LOS) rates of the missile system. LOS rate estimates are robust against coupled acceleration disturbance terms. The proposed method for fixed-time parameter estimation and robust state estimation can be used for a class of second-order systems and can be extended to any uncertain plant.

关键词： adaptive control algorithm Yaw Mathematical Models Kalman Filter Missile Dynamics Guidance System White Noise Terminal Guidance Missile Body control System Design

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adaptive IDENTIFICATION OF A FLEXIBLE STRUCTURE BY LATTICE FILTERS

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JOURNAL OF GUIDANCE control AND DYNAMICS 1989年第4期12卷 548-554页

作者： JABBARI, F GIBSON, JS UNIV CALIF LOS ANGELES DEPT MECH AEROSP & NUCL ENGNLOS ANGELESCA 90024

This paper presents adaptive parameter identification results for a complex flexible structure with many closely packed natural frequencies. Least-squares lattice filters, which are recursive in both time and order, are used to estimate the number of excited modes, natural frequencies, and damping ratios from input/output data. One-step-ahead output prediction also is generated by the lattice filters. The paper compares results from several experiments on the same structure, including one experiment during which the mass of the structure changes. © 1980 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Flexible Structures Forced Vibrations Finite Element Modeling White Noise NASA Langley Research Center adaptive control algorithm Single Input Single Output Autoregressive Model Prediction algorithms Convergence Analysis

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Synthesis of nonlinear adaptive controller for a batch distillation

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ISA TRANSACTIONS 2007年第1期46卷 49-57页

作者： Jana, Amiya K. Birla Inst Technol & Sci Dept Chem Engn Pilani 333031 Rajasthan India

A nonlinear adaptive control strategy is proposed for a binary batch distillation column. The hybrid control algorithm comprises a generic model controller (GMC) and a nonlinear adaptive state estimator (ASE). The adaptive observation scheme mainly estimates the imprecisely known parameters based on the available tray temperature measurements. The sensitivity of the proposed estimator is investigated with respect to the effect of initialization error, unmeasured disturbance and uncertainty. Then, a comparative study is carried out between the derived nonlinear GMC-ASE controller and a traditional proportional integral law in terms of set point tracking and disturbance rejection performance. The study also includes the effect of measurement noise and parametric uncertainty on the closed-loop performance. The proposed adaptive control algorithm is shown to be quite promising due to the exponential error convergence capability of the ASE estimator in addition to the high-quality control action provided by the GMC controller. (c) 2006, ISA. Published by Elsevier Ltd. All rights reserved.

关键词： generic model controller adaptive state estimator adaptive control algorithm batch distillation

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adaptive Reaction less Motion and Parameter Identification in Postcapture of Space Debris

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JOURNAL OF GUIDANCE control AND DYNAMICS 2013年第2期36卷 404-414页

作者： Thai Chau Nguyen-Huynh Sharf, Inna McGill Univ Dept Mech Engn Montreal PQ H3A 2K6 Canada

This paper presents a new control scheme for the problem of a space manipulator after capturing an unknown target, such as space debris. The changes in the dynamics parameters of the system, as a result of capturing an unknown target, must be accommodated because they may lead to poor performance of the trajectory control and attitude stabilization system. To address this issue in the postcapture scenario, the adaptive reactionless control algorithm to produce the arm motions with minimum disturbance to the base is proposed in this study. In addition, the online momentum-based estimation method is developed for inertia-parameter identification after the space manipulator grasps an unknown tumbling target with unknown angular momentum. This control scheme is intended for use in the transition phase from the instant of capture until the unknown parameters are identified and/or the available stabilization methods can be applied properly. To verify the validity and feasibility of the proposed concept, *** simulation platform is employed to implement a planar base manipulator target model and the three-dimensional model of the Engineering Test Satellite VII system. The numerical results show that the space manipulator is able to perform reactionless motion while the inertial parameters converge to their real values.

关键词： Orbital Debris Serial Link Manipulators Space Manipulator Attitude control System Satellites control algorithm adaptive control algorithm Three Degrees of Freedom Reaction Wheels Robots

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Robust adaptive Coordination controller for a Spacecraft Equipped with a Robotic Manipulator

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JOURNAL OF GUIDANCE control AND DYNAMICS 2016年第12期39卷 2699-2711页

作者： Jayakody, Hiranya S. Shi, Lingling Katupitiya, Jay Kinkaid, Nathan Univ New South Wales Sch Mech & Mfg Engn Mechatron Grp Sydney NSW 2052 Australia Univ New South Wales Sch Mech & Mfg Engn Australian Ctr Space Engn Res Sydney NSW 2052 Australia

Free-flying robotic spacecraft play a significant role in the space industry today. Unlike ground-based robots, the manipulator motion in a space robot can cause undesirable disturbances to the spacecraft platform, causing its attitude to change, potentially disrupting communication and solar energy collection processes as a result. Thus, coordinated control of both the spacecraft attitude and the manipulator motion become essential for successful space operations. Though past research has developed dynamic models for spacecraft manipulators, the contribution of reaction wheels to the angular momentum of the entire system needs further consideration. This paper reformulates the dynamic equations of a free-flying space robot by taking the aspect of reaction wheels into account. A diagonalization method is introduced to decouple the highly nonlinear multi-input/ multi-output system model. A novel adaptive variable structure control method is then applied to implement a robust coordination controller for the space robot subjected to system uncertainties. Simulations are carried out on a spacecraft model with a 3-degree-of-freedom manipulator mounted on it to demonstrate the robustness of the proposed approach. Comparisons with sliding mode control show that the new controller results in faster settling times, which leads to maintaining uninterrupted communication links and efficient solar energy harvesting.

关键词： Spacecraft Models Special Purpose Dexterous Manipulator adaptive control algorithm Free Flying Space Robot Spacecraft Attitude Variable Structure control Robots Solar Energy Space Operations Energy Harvesting

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Single-Input/Single-Output adaptive Flutter Suppression of a Three-Dimensional Aeroelastic System

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JOURNAL OF GUIDANCE control AND DYNAMICS 2012年第2期35卷 659-665页

作者： Huang, Rui Hu, Haiyan Zhao, Yonghui Nanjing Univ Aeronaut & Astronaut Inst Vibrat Engn Res State Key Lab Mech & Control Mech Syst Nanjing 210016 Peoples R China

AEROELASTIC effects induced by the interaction of unsteady aerodynamics and structural dynamics are an extremely important concern in aircraft design. Among the aeroelastic effects, flutters and limit-cycle oscillations (LCO) are the critical constraints on the performance of an aircraft. Although a possible flutter or LCO can be suppressed via many conventional controls, such as classical single-input/single-output (SISO) feedback controls [1] and linear quadratic Gaussian (LQG) control [2], it is not easy to synthesize an efficient control scheme to suppress an aeroelastic instability because of parameter uncertainties caused by inaccurate computation of the aerodynamics and/or structural modes, as well as varying configurations. Therefore, it is necessary to develop an adaptive control to suppress the instability of an aeroelastic system with parameter uncertainties.

关键词： Aeroelastic Models Single Input Single Output adaptive control algorithm Linear Quadratic Gaussian Low Speed Wind Tunnel Finite Element Modeling adaptive Output Feedback control Aerodynamic Configurations Conjugate Gradient algorithm control Surfaces

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Neural Network Based Modified State Observer for Orbit Uncertainty Estimation

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JOURNAL OF GUIDANCE control AND DYNAMICS 2013年第4期36卷 1194-1209页

作者： Harl, Nathan Rajagopal, Karthikeyan Balakrishnan, S. N. IST Rolla Rolla MO 65401 USA IST Rolla Dept Mech & Aerosp Engn Rolla MO 65401 USA

A novel technique for estimating uncertainties caused by gravitational perturbations is presented. The approach, called the modified state observer, allows for the estimation of uncertainties in nonlinear dynamics and, in addition, providing estimates of the system states. The observer structure contains neural networks whose outputs are the uncertainties in the system. A useful and important application of this observer is the problem of determining uncertain gravitational perturbations that a satellite may experience when orbiting a body. With future space missions involving other bodies, such as asteroids that produce gravitational perturbations which are highly uncertain and are subjected to unknown physical influences, the modified state observer can be used not only to estimate the states of the satellites, but it can also be used to estimate the uncertainties that could be analyzed further with understanding the physical phenomena. To demonstrate the utility of the modified state observer for this class of problem the technique is applied for two cases: estimating the uncertainty caused by the J(2) perturbation for an Earth orbiter and estimating the uncertainty in an asteroid's gravitational field. Simulations are presented, which indicate that the observer can accurately estimate both the periodic nature of these perturbations, as well as the magnitudes.

关键词： Radial Basis Function Network Asteroids Earth Satellites Nonlinear Dynamics Asteroid Missions Orbiting Body Extended Kalman Filter adaptive control algorithm Monte Carlo Simulation

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Tiltrotor whirl flutter alleviation using actively controlled wing flaperons

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AIAA JOURNAL 2006年第11期44卷 2524-2534页

作者： Hathaway, Eric L. Gandhi, Farhan Boeing Co Philadelphia PA 19142 USA Penn State Univ Rotorcraft Ctr Excellence Dept Aerosp Engn University Pk PA 16802 USA

The present study is an evaluation of the effectiveness of wing flaperon active control for alleviation of filtrotor whirl flutter. control systems that increase whirl flutter speed and wing mode subcritical damping are designed while at the same time observing realistic limits on flaperon deflection. Both stiff- and soft in-plane filtrotor configurations are examined, to develop an understanding of the influence of vehicle configuration on flaperon effectiveness. The importance of considering unsteady aerodynamic effects in stability analyses and in controller design is also discussed. controller designs considered include gain-scheduled full-state feedback optimal control, constant-gain full-state controllers derived from the optimal controllers, and single-state feedback systems. The dominant feedback parameters in the optimal control systems are identified and examined to gain insight into the most important feedback paths that could be exploited by simpler reduced-order controllers. Feedback of wing vertical and chordwise bending modes are identified as the most powerful parameters, with wing vertical bending rate feedback being particularly beneficial, as it substantially increases wing vertical bending mode damping.

关键词： Tiltrotor Aircraft Aircraft control adaptive control algorithm Algebraic Riccati Equation Feedback control System adaptive control Systems Freestream Mach Number Airspeed Stability Augmentation Unsteady Aerodynamic Analysis

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Forced Flame Response of Turbulent Liquid-Fueled Lean-Direct-Injection Combustion to Fuel Modulations

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JOURNAL OF PROPULSION AND POWER 2009年第6期25卷 1259-1271页

作者： Yi, Tongxun Santavicca, Domenic A. Penn State Univ Dept Mech & Nucl Engn University Pk PA 16802 USA

Reported are the forced flame responses of a turbulent, liquid-fueled, swirl-stabilized, lean-direct-injection combustor to fuel modulations. Fuel modulations are achieved using a motor-driven, high-frequency, rotary fuel valve specially designed for this experiment. This valve is capable of fuel modulations up to 1 kHz. The instantaneous fuel How rate out of a fuel injector is accurately determined from pressure measurements at one or two locations upstream of the fuel nozzle. Linear flame responses are obtained with small-amplitude fuel modulations, typically below 2.0% of the mean fuel How rate, about 60 Hz below the acoustic resonant frequencies. The invariance in the flame transfer functions to the fuel modulation amplitude suggests that the derived flame transfer functions are linear and that the induced heat release rate oscillations mainly respond to variations in the instantaneous fuel flow rate rather than in the droplet size and distribution. Flame transfer functions at different air flow rates, equivalence ratios, and preheat temperature are examined. With fuel modulations around the acoustic resonant frequencies, forcing-induced acoustic feedback on heat release responses cannot be ignored, and the measured flame transfer functions are no longer open-loop and linear. The nonlinearity in the forced flame responses is significantly affected by acoustic damping. Extinction and entrainment of self-excited combustion oscillations by fuel modulations at the approach of the acoustic resonant frequencies are observed. Self-excited combustion oscillations can be diminished by increasing the amount of fuel modulations. Applications of the flame transfer functions to modeling and control of combustion instability and lean blowout for both liquid-fueled and gas-fueled combustion are discussed.

关键词： Liquid Fuels Fuels Lean Premixed Combustion Planar Laser Induced Fluorescence Resonant Frequencies Swirl Stabilized Combustor Combustion Chambers Fuel Injector adaptive control algorithm Fuel Valve

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Computationally Efficient Collision-Free Trajectory Planning of Satellite Swarms Under Unmodeled Orbital Perturbations

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JOURNAL OF GUIDANCE control AND DYNAMICS 2023年第8期46卷 1548-1563页

作者： Basu, Himadri Pedari, Yasaman Almassalkhi, Mads Ossareh, Hamid R. Univ Grenoble Alpes Grenoble Images Parole Signal Automat Lab CNRS F-38000 Grenoble France Univ Vermont Dept Elect & Biomed Engn Burlington VT 05405 USA

This paper studies the problem of collision-free trajectory planning for a satellite swarm reconfiguration under perturbations and modeling uncertainties in a low Earth orbit (LEO). Determining exact trajectory planning solutions is computationally heavy as they require solving a mixed-integer nonlinear program owing to i) nonlinear relative dynamic models of satellites, ii) fuel-optimal assignment of satellites on the final formation, and iii) nonconvex collision avoidance constraints. To address these, first, a suitable linear model for trajectory planning is identified by quantifying modeling accuracy associated with various models capturing LEO perturbations. The effects of any residual modeling errors in the path prediction are mitigated by shrinking-horizon model-predictive feedback control, which updates the control command based on the latest satellite measurements. Secondly, an optimal swarm configuration is efficiently computed by decoupling the target-assignment algorithm from the trajectory optimization problem. Based on the estimated fuel expenditure for each satellite-target pairing, the target-assignment algorithm selects a configuration with minimal fuel consumption. Lastly, to determine collision-free, fuel-optimal maneuvers, two novel trajectory planning approaches, namely, distributed and decentralized trajectory optimization, are presented. While the former iteratively searches for collision-free feasible paths to optimal terminal configuration, the latter computes a near-optimal configuration with collision-free paths.

关键词： Satellite Formation Flying Pontryagin's Maximum Principle Mixed Integer Linear Programming Energy Economics Feedback control adaptive control algorithm Aircraft Operations Planets Sun Synchronous Orbit Computational Fluid Dynamics

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