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Dynamic Response to Canard control and Gravity for a Dual-Spin Projectile

JOURNAL OF SPACECRAFT AND ROCKETS 2016年第3期53卷 558-566页

作者： Chang, Sijiang Nanjing Univ Sci & Technol Sch Energy & Power Engn 200 Xiaolingwei Nanjing 210094 Jiangsu Peoples R China

Existing literature has shown that spin-stabilized projectiles respond out-of-phase to control force that is applied at the nose of projectile. However, this conclusion was made according to some assumptions or specific conditions. Taking a dual-spin-stabilized projectile with canards as the object of study, this paper seeks to explore a deeper understanding of dynamic response to control input in another particular situation by considering the coupled effect of canard control and gravity. By establishing a linear model of the pitching and yawing motion based on a simplified seven-degree-of-freedom dynamic model for this projectile, approximate expressions that could predict the angle of attack after canard actuation were obtained. These effective formulas are used to indicate that, depending on the effect of gravity on trajectory, the swerve response due to identical canard control could be fundamentally different, especially with large amplitude of gravity-induced yaw of repose. The phase shift may vary substantially with different deflection angles of canards during the process of guidance and control. Moreover, a simple formula for estimating the critical equivalent deflection angle of canards was given. The results of this research are expected to be supplementary to those concerning flight dynamics of spin-stabilized projectiles concluded in current literature.

关键词： Dynamic Response Spin Stabilized Projectiles Canard Angle of Attack Yaw Flight Path Angle Aerodynamic Coefficients Magnus Moment Coefficient Numerical Integration control algorithm

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Time and frequency domain convergence properties in iterative learning control

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INTERNATIONAL JOURNAL OF control 2002年第14期75卷 1114-1126页

作者： Norrlöf, M Gunnarsson, S Linkoping Univ Dept Elect Engn SE-58183 Linkoping Sweden

The convergence properties of iterative learning control (ILC) algorithms are considered. The analysis is carried out in a framework using linear iterative systems, which enables several results from the theory of linear systems to be applied. This makes it possible to analyse both first-order and high-order ILC algorithms in both the time and frequency domains. The time and frequency domain results can also be tied together in a clear way. Results are also given for the iteration-variant case, i.e. when the dynamics of the system to be controlled or the ILC algorithm itself changes from iteration to iteration.

关键词： Repetitive control control algorithm Manipulators Converge International Labour Conference Iterative learning control learning control Manipulators iterative methods Computer algorithms Linear system

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POINTING control, WITH TETHERS AS ACTUATORS, OF A SPACE STATION SUPPORTED PLATFORM

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JOURNAL OF GUIDANCE control AND DYNAMICS 1993年第2期16卷 396-399页

作者： BANERJEE, AK KANE, TR STANFORD UNIV DEPT MECH ENGNSTANFORDCA 94304

We consider the problem of Earth-pointing control of a space platform B connected by means of tethers to an orbiting space station A that is independently controlled so as to remain Earth pointing. The intuitive idea that is explored is that of achieving pointing control by pulling on the tethers. The concept presented in this Note for pointing control in a plant with two tethers has the potential of extension to three-dimensional attitude control with three tethers. We present nonlinear and linearized equations of motion of the system, and a control law design based on feedforward control plus full state feedback with an actuator prefilter, followed by simulation results.

关键词： Space Stations Actuators Linear Quadratic Regulator Full State Feedback Earth Attitude control Three Degrees of Freedom control algorithm

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Passive nutation control of spinning spacecraft through the use of multiple booms

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第5期23卷 906-908页

作者： Eke, FO Harvey, A Eke, EM Univ Calif Davis Dept Mech & Aeronaut Engn Davis CA 95616 USA Toyo Tanso USA Inc Dept Engn Dev Sect Troutdale OR 97060 USA Calif State Univ Sacramento Dept Mech Engn Sacramento CA 95819 USA

SEVERAL of the spacecraft in use today are spin-stabilized and are thus equipped with some form of nutation control system. Spacecraft nutation control devices can be active or passive. Passive nutation damping systems limit spacecraft nutation through onboard energy dissipation, and the design of such systems is based, for the most part, on well-established attitude stability criteria for spinning bodies. When disturbed slightly from its position of stable spin, a spacecraft with internal energy dissipation will, in general, regain its original orientation faster than one without energy dissipation. This fact has led to the design of several passive devices that are triggered into dissipating energy onboard of a spacecraft anytime,that the spacecraft attitude motion is disturbed. Such devices have included simple mass-spring-dashpot systems, damped physical pendulum, viscous fluid in ring-shaped tubes, *** systems often include several rod like appendages or booms attached to the main spacecraft bus, which serve various purposes during the vehicle's mission. In this study it is proposed to use two such booms on a given spacecraft for nutation control purposes. The idea is to replace the usual rigid attachment of such booms to the bus, with a one-degtee-of-freedom hinge, together with a torsional spring and damper system. This effectively converts each boom into a pendulous damper for the spacecraft. Such arrangement differs markedly from the usual design of pendulous dampers in that the mass center of each boom would be outboard of the pivot point and the length would substantially exceed that of traditional pendulum dampers.

关键词： Spinning Spacecraft Nutation Damping Propellant Galileo Spacecraft Spacecraft Mission Spacecraft Attitude Spacecraft System control algorithm Magnetometers

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MCSR and SCSR control algorithms for Providing Power Quality in Electrical Grids

MCSR and SCSR Control Algorithms for Providing Power Quality...

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Mediterranean Electrotechnical Conference

作者： Boris Oleksyuk Rinat Karymov Victor Cioban National Research University "MPEI" SKRM FARAMAX

ISBN: (纸本)9781509000593

The development of power engineering leads to the growing need for flexible systems allowing control of electrical grid modes, transients and increase the efficiency of power systems. In the last decade the most rapidly developing group of controlled devices, which use magnetization characteristic of electrotechnical steel for power control, are magnetically controlled shunt reactors and sources of reactive power based on controlled reactors. Due to the control principle used in these devices, as well as in other types of FACTS, they produce current harmonics. The paper presents two developed reactor control algorithms that reduce its negative impact on the voltage waveform distortion in the nodes of electrical grid.

关键词： magnetically controlled shunt reactor SCSR power quality control algorithm current and voltage harmonics automatic control system

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Predictive Functional control-Based Missile Autopilot Design

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JOURNAL OF GUIDANCE control AND DYNAMICS 2012年第5期35卷 1450-1455页

作者： Tang, Wei-Qiang Cai, Yuan-Li Xi An Jiao Tong Univ Inst Control Engn Xian 710049 Shaanxi Peoples R China

Predictive functional control is applied to design a missile autopilot considering control constraints. The missile nonlinear dynamics are first transformed into a linear structure with state-dependent coefficient matrices. At each sampling instant, the internal state-space model for prediction is obtained through a normal discretization procedure. Based upon this model, a predictive functional controller for the nonlinear missile autopilot is proposed. Compared with the conventional predictive control algorithms, which usually involve an online quadratic programming in the practical implementation, the new controller demands less online computation resources. Simulation results validate the effectiveness and robustness of the proposed algorithm.

关键词： Autopilot Missiles control algorithm Quadratic Programming Nonlinear Dynamics State Dependent Riccati Equation Linear Time Invariant System Stability Derivatives Nonlinear Systems Attitude control System

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Forcefree control with independent compensation for industrial articulated robot arms

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control ENGINEERING PRACTICE 2007年第6期15卷 627-638页

作者： Goto, Satoru Usui, Tatsumi Kyura, Nobuhiro Nakamura, Masatoshi Saga Univ Dept Adv Syst Control Engn Honjomachi Saga 8408502 Japan Kinki Univ Sch Human Oriented Sci & Engn Dept Elect & Commun Engn Iizuka Fukuoka 8208555 Japan

Forcefree control of robot manipulators so far has been the passive motion of the arm due to the influence of external force under ideal conditions of zero gravity and zero friction, whereas this paper demonstrates forcefree control under assigned friction, gravity and inertia. The effectiveness of the proposed forcefree control with independent compensation is confirmed by comparing the experimental results with simulation results. Comparisons of the forcefree control with independent compensation to the other force control methods are also presented. (c) 2006 Elsevier Ltd. All rights reserved.

关键词： industrial robots robotic manipulators force control passive motion control algorithm

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FEEDBACK-control LOGIC FOR SPACECRAFT EIGENAXIS ROTATIONS UNDER SLEW RATE AND control CONSTRAINTS

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JOURNAL OF GUIDANCE control AND DYNAMICS 1995年第6期18卷 1372-1379页

作者： WIE, B LU, JB Arizona State Univ. Tempe

The problem of reorienting a rigid spacecraft as fast as possible within the physical limits of actuators and sensors is investigated. In particular, a nonlinear feedback control logic that accommodates the actuator and sensor saturation limits is introduced. The near-minimum-time eigenaxis reorientation problem of the X-Ray Timing Explorer spacecraft under slew rate and control torque constraints is used as an example to demonstrate the effectiveness and simplicity of the proposed nonlinear feedback control logic.

关键词： Nonlinear Feedback Clementine Spacecraft Actuators Sensors Closed Loop System Reaction Wheels Quaternions control algorithm Attitude Dynamics Gyroscopic Couple

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Adaptive control of a zero-stiffness suspension system

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JOURNAL OF GUIDANCE control AND DYNAMICS 1996年第4期19卷 794-800页

作者： Yang, LF Tzeng, RC Kuo, CP National Cheng Kung Univ. Tainan Taiwan

A zero-stiffness suspension system featuring a noncircular disk is used as an application in counteracting gravity loads in ground-based structural testing. The dynamic behavior of this mechanism is analyzed in closed form, in which this mechanism is shown to be very sensitive to inertial properties of a noncircular disk, which can introduce inertial forces to trigger nonlinear dynamic behavior in the system, thereby degrading testing performance under such inertial loading. An adaptive feedforward control law is developed for eliminating these inertial effects on the suspension system during dynamic testing. Under this control manipulation, the output signals of disk mechanism are regulated and tracked along the desired trajectories so that the error signals can be vastly reduced. Stability of the control system is investigated, and simulated time histories of test articles under an active band-drive suspension system also are presented to show the effectiveness of the approach.

关键词： Closed Loop System Stiffness control Systems Feedback control System Stiffness Matrices Space Structures control Moment Gyroscope D'Alembert's Principle control algorithm Zero Gravity

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Adaptive control of a Tendon-Driven Manipulator for Capturing Non-Cooperative Space Targets

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JOURNAL OF SPACECRAFT AND ROCKETS 2022年第1期59卷 111-128页

作者： Kernot, Justin E. Ulrich, Steve Carleton Univ Dept Mech & Aerosp Engn 1125 Colonel By Drive Ottawa ON K1S 5B6 Canada

Orbital debris in Earth orbit poses a threat to the future of spaceflight. To combat this issue, this paper proposes a novel robotic mechanism for non-cooperative capture and active servicing missions on non-cooperative targets;specifically, a tendon-driven manipulator is assumed for this work. The capture mechanism is a prototype symmetric two-link gripper driven by an open-ended cable-sheath transmission mechanism. Because the cable-sheath transmission mechanism is a nonlinear time-varying hysteretic system, two separate adaptive control strategies were compared against the uncontrolled and proportional-integral-derivative controlled performance of the closedloop gripper. Specifically, an indirect control method and a direct L-1 controller were employed. Experimental results demonstrate that the adaptive controllers show better tracking performance of a joint trajectory over the proportional-integral-derivative controlled and uncontrolled cases, whereas the L-1 controller performs best under dynamic conditions, and the indirect controller performs best in steady state.

关键词： Special Purpose Dexterous Manipulator Proportional Integral Derivative control Orbital Debris Earth Hysteresis Loops control algorithm Inverse Kinematics Front End Robotics Enabling Near Term Demonstration Servomotors Japan Aerospace Exploration Agency

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