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REDUCED-ORDER PULSE-MOTOR IGNITION control LOGIC

JOURNAL OF GUIDANCE control AND DYNAMICS 1987年第4期10卷 343-350页

作者： CHENG, VHL MENON, PKA GUPTA, NK BRIGGS, MM GEORGIA INST TECHNOL ATLANTAGA 30332 INTEGRATED SYST DIV MISSILESANTA CLARACA

The higher total impulse and energy management potential available in a pulse motor can be exploited with optimal guidance and propulsion control methods to improve missile performance. Under the assumptions of same propellant formulation and similar grain configuration of the pulses, a pulse motor can generally deliver higher specific impulse than its boost-sustain counterpart, leading to higher total impulse with the same launch weight despite a weight penalty on the pulse motor due to barrier insulation and an additional igniter; moreover, the pulse motor also allows arbitrary pulse delays between pulses. To fully exploit such energy management capabilities requires a real-time on-board pulse ignition controller. This paper studies the pulse ignition problem for a generic medium-range air-to-air missile from an optimal control viewpoint, using a minimum fight-time performance index.

关键词： Midcourse Guidance Transversality Condition Singular Perturbation Solid Propellants Air to Air Missiles Energy Management Propulsion control Microprocessors control algorithm Guidance Laws

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Coordinated control of multisatellite systems

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JOURNAL OF GUIDANCE control AND DYNAMICS 2001年第2期24卷 360-368页

作者： Kang, W Sparks, A Banda, S USN Postgrad Sch Dept Math Monterey CA 93943 USA USAF Res Lab Control Sci Div Wright Patterson AFB OH 45433 USA

The problem of formation and reconfiguration of multiple microsatellite systems is addressed. A control scheme called the perceptive frame is adopted that integrates the decentralized feedback of each satellite with online sensor information to achieve the goal of formation keeping and intersatellite coordination. The proposed design algorithm has the advantage of relative position keeping and easy formation reconfiguration.

关键词： Satellite Formation Sensors Feedback Linearization Elliptical Orbit Linear Quadratic Regulator Earth Moving Target Indication Satellite control control algorithm Nonlinear Systems

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Real-Time Nonlinear Attitude control System for Nanosatellite Applications

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JOURNAL OF GUIDANCE control AND DYNAMICS 2013年第6期36卷 1661-1671页

作者： Li, Junquan Post, Mark Lee, Regina York Univ Toronto ON M3J 1P3 Canada

This paper develops a fault-tolerant attitude controller for next-generation nanosatellites. The proposed fault-tolerant attitude control algorithms in this study are based on first-order and high-order sliding-mode control theories as well as fuzzy logic systems to achieve low cost and real-time autonomy. A locally asymptotically stable adaptive fuzzy first-order sliding-mode controller is chosen as the best solution to the local attitude control tracking problem. This novel fault-tolerant controller is validated by simulation results with reaction wheel Coulomb friction, saturation, noise, dead zones, bias faults, and external disturbances. Simulation and testing results presented in the paper demonstrate that the attitude control system can provide successful pointing and tracking in the presence of system uncertainties for a specified class of reaction wheel failures.

关键词： Attitude control System Small Satellites Proportional Integral Derivative Spacecraft Attitude Fuzzy control control algorithm Quaternions Fault Tolerance Variable Structure control Attitude Tracking

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Combined Longitudinal and Lateral control of Car-Like Vehicle Platooning With Extended Look-Ahead

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IEEE TRANSACTIONS ON control SYSTEMS TECHNOLOGY 2020年第3期28卷 790-803页

作者： Bayuwindra, Anggera Ploeg, Jeroen Lefebere, Erjen Nijmeijere, Henk Eindhoven Univ Technol Dept Mech Engn NL-5600 MB Eindhoven Netherlands 2getthere NL-3543 AE Utrecht Netherlands

In this paper, we present a novel look-ahead concept for combined longitudinal and lateral vehicle following control for a car-like platoon. A nonlinear controller structure, which is based on Cooperative Adaptive Cruise control, is designed for the lateral and longitudinal direction. For practical implementation and cost efficiency, a preceding vehicle look-ahead approach is considered since it utilizes the already available information (such as preceding vehicle position, orientation, and velocity) from radar and vehicle-to-vehicle communication. However, due to the position control in the look-ahead approach, the follower vehicle may cut corners. To overcome this problem, the look-ahead is extended to a point perpendicular to the direction of the preceding vehicle, which can be viewed as a virtual preceding vehicle tracking objective. To demonstrate the effectiveness of the designed controller with the extended look-ahead approach, simulations are performed and further validated with experiments on a mobile robot platform. The results prove the effectiveness of the extended look-ahead approach.

关键词： Magnetic resonance imaging Vehicular ad hoc networks Radar tracking Acceleration Vehicle dynamics control systems control algorithm Cooperative Adaptive Cruise control (CACC) intelligent vehicle nonlinear systems vehicle platooning

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Design of yarn tension self-adaptive control system on warp knitting machine

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JOURNAL OF THE TEXTILE INSTITUTE 2024年第2期115卷 173-187页

作者： Zheng, Baoping Jiang, Gaoming Jiangnan Univ Engn Res Ctr Knitting Technol Minist Educ Wuxi Peoples R China

In order to realize the control of yarn dynamic tension, the warp knitting machine should be able to control the variation of tension values in different angles in one course during the knitting process. In view of the defects of controlling the let-off of warp beam, such as large yarn tension fluctuating and can't accurately control the yarn tension at different angles within a course and so on, a specific kind of yarn tension self-adaptive control system on warp knitting machine has been developed. By analyzing the fluctuation of yarn tension combined with the looping mechanism motion law and process parameters of a warp knitting machine, the hardware and software platform of the system are designed;the velocity control strategy of the system is optimized;the quintic polynomial interpolation curve is calculated, and the double FIFO(first input first output) dynamic interpolation motion method is planned. Meanwhile, the self-adaptive control algorithm is designed to realize the self-adaptive control of yarn tension. From the analysis of the feedback yarn dynamic tension value curve and in comparison with the traditional let-off control system, the self-adaptive control system can reduce the yarn tension peak by at least 55.2% and the yarn tension fluctuation range by at least 51.6%. It is verified that the self-adaptive control system has an efficient performance of yarn dynamic tension regulation.

关键词： Warp knitting machine yarn tension self-adaptive control interpolation motion control algorithm

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Reusable Launchers: Development of a Coupled Flight Mechanics, Guidance, and control Benchmark

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JOURNAL OF SPACECRAFT AND ROCKETS 2020年第1期57卷 74-89页

作者： Simplicio, Pedro Marcos, Andres Bennani, Samir Univ Bristol Dept Aerosp Engn Univ Walk Bristol BS8 1TR Avon England European Space Agcy European Space Res & Technol Ctr GNC Sect Keplerlaan 1 NL-2201 AZ Noordwijk Netherlands AIAA Reston VA USA

This paper studies the mechanics of reusable retropropelled flight of slender low lift-to-drag bodies via integrated guidance and control simulations. To do this, a simulation benchmark focused on the coupling between flight mechanics, guidance, and control must be developed, as opposed to mission-optimization-oriented ones that simplify (or directly ignore) these couplings. The developed simulator covers vertical takeoff and landing of a first-stage booster for return to launch site and downrange landing missions. To steer it toward a controlled entry, followed by descent and precision landing, the vehicle is configured with a deep throttling thrust vector control system, fins, and cold gas thrusters. Comparative performance results are derived in terms of aerodynamic loads and heat fluxes for both recovery scenarios, as well as through a detailed closed-loop controllability analysis. The latter demonstrates that the configuration has sufficient authority and resolution to perform stable flight and adequate wind gust rejection. The developed benchmark (because of the coupled flight mechanics, guidance, and control) allows to provide a first assessment of operational limits, as well as mission and GNC specifications. This in turn paves the way for the synthesis and assessment of more sophisticated reusable launcher guidance and control algorithms.

关键词： Flight Mechanics Thrust Vector control Aerodynamic Characteristics Closed Loop Transfer Function Cold Gas Thruster Vertical Landing control algorithm Heat Flux Propellant Slosh Aerodynamic Angle

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MICROcontrolLER-BASED STRATEGY FOR REACTIVE POWER-control AND DISTORTION COMPENSATION

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IEE PROCEEDINGS-B ELECTRIC POWER APPLICATIONS 1990年第6期137卷 364-372页

作者： DOULAI, P LEDWICH, G Department of Electrical Engineering University of Queensland Brisbane Australia

Compensation of the fundamental displacement and harmonic distortion currents drawn by nonlinear loads can be achieved by using a three-phase voltage-source inverter to generate an appropriate correction voltage. The real time feedback control scheme of the inverter presented in the paper is a full three-phase switching strategy based on a ‘periodic integral’ version of the error sawtooth pulse-width modulation technique. The switching commands for the transistors within the inverter are generated by a 16-bit single-chip microcontroller. This device has sufficient computational power to implement all aspects of the controller tasks as well as handling the man/machine interface. The output waveform of the compensator is precisely determined by theoretically perfect tracking of the periodic reference signal to cancel the harmonic components up to the synthetised switching frequency (2.7 kHZ). The value of the proposed algorithm is experimentally verified on a 5.5 kVA inverter circuit and is found to give very fast and precise compensation characteristics. Details are given for operation of the experimental system as well as the control algorithm implementation. Harmonic analysis of the voltage on the test system demonstrates the effectiveness of the developed control strategy for the compensator.

关键词： PWM fundamental displacement Power convertors and power supplies to apparatus feedback control 2.7 kHz three-phase switching strategy distortion compensation reactive power control 16-bit single-chip microcontroller feedback 5.5 kVA control of electric power systems Power and energy control error sawtooth pulse-width modulation technique harmonic distortion currents three-phase voltage-source inverter invertors electric distortion power control compensation reactive power control algorithm

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Aircraft pitch control via second-order sliding technique

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第4期23卷 586-594页

作者： Levant, A Pridor, A Gitizadeh, R Yaesh, I Ben-Asher, JZ Inst Ind Math IL-84311 Beer Sheva Israel Israel Mil Ind Ltd Control Dept Adv Syst Div IMI IL-47100 Ramat Hasharon Israel Technion Israel Inst Technol Dept Aerosp Engn IL-32000 Haifa Israel

control of high-performance low-cost uncrewed air vehicles involves the problems of incomplete measurements, external disturbances, and modeling uncertainties. Sliding mode control combines high precision with robustness to the aforementioned factors. The idea behind this approach is the choice of a particular constraint that, when maintained, will provide the process with the required features and remove, therefore, the plant's uncertainty. However, standard sliding modes are characterized by a high-frequency switching of control, which causes problems in practical applications (so-called chattering effect). The implemented second order sliding controller features bounded continuously time-dependent control and provides higher accuracy than the standard sliding mode, while preserving precise constraint fulfillment within a finite time. It possesses, also, significant adaptive properties. The general approach is demonstrated by solving a real-life pitch control problem. Results of a computer simulation and flight tests are presented.

关键词： Aircraft Pitch control Sliding Mode control Air Vehicle Variable Structure System Dynamic Pressure Flight Testing Six Degree of Freedom Feedback Linearization control algorithm Wind Tunnels

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Generalizing Movements with Information-Theoretic Stochastic Optimal control

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JOURNAL OF AEROSPACE INFORMATION SYSTEMS 2014年第9期11卷 579-595页

作者： Lioutikov, Rudolf Paraschos, Alexandros Peters, Jan Neumann, Gerhard Tech Univ Darmstadt Intelligent Autonomous Syst Grp D-64283 Darmstadt Germany Max Planck Inst Intelligent Syst Dept Empir Inference D-72076 Tubingen Germany

Stochastic optimal control is typically used to plan a movement for a specific situation. Although most stochastic optimal control methods fail to generalize this movement plan to a new situation without replanning, a stochastic optimal control method is presented that allows reuse of the obtained policy in a new situation, as the policy is more robust to slight deviations from the initial movement plan. To improve the robustness of the policy, we employ information-theoretic policy updates that explicitly operate on trajectory distributions instead of single trajectories. To ensure a stable and smooth policy update, the "distance" is limited between the trajectory distributions of the old and the new control policies. The introduced bound offers a closed-form solution for the resulting policy and extends results from recent developments in stochastic optimal control. In contrast to many standard stochastic optimal control algorithms, the current approach can directly infer the system dynamics from data points, and hence can also be used for model-based reinforcement learning. This paper represents an extension of the paper by Lioutikov et al. ("Sample-Based Information-Theoretic Stochastic Optimal control," Proceedings of 2014 IEEE International Conference on Robotics and Automation (ICRA), IEEE, Piscataway, NJ, 2014, pp. 3896-3902). In addition to revisiting the content, an extensive theoretical comparison is presented of the approach with related work, additional aspects of the implementation are discussed, and further evaluations are introduced.

关键词： Theoretic Stochastic Optimal control Reinforcement Learning Robotics Linear Quadratic Gaussian Robots Markov Decision Process Kullback Leibler Divergence Search algorithm Optimization algorithm control algorithm

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MISSION-FUNCTION control FOR SLEW MANEUVER OF A FLEXIBLE SPACE STRUCTURE

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JOURNAL OF GUIDANCE control AND DYNAMICS 1989年第6期12卷 858-865页

作者： FUJII, H ISHIJIMA, S TOKYO METROPOLITAN INST TECHNOL DEPT ELECTR SYST ENGNTOKYOJAPAN

A new control algorithm, named the mission-function control method, is introduced and applied to slew maneuver of a spacecraft with a flexible appendage. The control algorithm is based upon the Lyapunov method applied to a mechanical system combined with a control system and employs the concept of generalized energy functions. The flexible appendage is modeled in terms of the partial differential equations that are believed to describe the distributed systems most precisely. Implementation of the control algorithm naturally results with physical meaning, and it is shown that sensing of the bending moment and shearing force at the root of the flexible appendage is essential. Results of numerical simulation show an excellent controlled behavior for the slew maneuver. © 1989 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Large Space Structures control algorithm Bernoulli Euler Beams Numerical Simulation control Systems Linear Quadratic Gaussian Damping Coefficient Flexible Structures Canadian Aeronautics and Space Institute National Aerospace Laboratories

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