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  • 1
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    Automatic assembly of space stations (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A problem in the automatic assembly of space stations is the determination of guidance laws for the terminal rendezvous and docking of two structural components or modules. The problem involves the feedback control of both the relative attitude and translational motion of the modules. A suitable mathematical model based on rigid body dynamics was used. The basic requirements, physical constraints and difficulties associated with the control problem are discussed. An approach which bypasses some of the difficulties is proposed. A nonlinear guidance law satisfying the basic requirements is derived. The implementation requirements is discussed. The performance of the resulting feedback control system with rigid and flexible structural components is studied by computer simulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 67-101
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  • 2
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    Control of reflector vibrations in large spaceborne antennas by means of movable dampers (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A simple approach to the design of feedback controls for damping the vibrations in large spaceborne antennas with flexible dish reflectors is proposed. The feedback controls consist of movable velocity-feedback dampers whose positions are determined by minimizing the rate of change of total vibrational energy at any time. The performance of the proposed feedback controls is studied via computer simulations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME, Transactions, Journal of Applied Mechanics (ISSN 0021-8936); 50; Sept
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  • 3
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    Control of large spaceborne antenna systems with flexible booms by mechanical decoupling (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A simple practical method for designing antenna-feed attitude control systems for large deployable spaceborne antenna systems with long flexible booms is proposed. The basic idea is to mechanically decouple the antenna-feed from the boom so that the feed-attitude control system can be designed without taking the boom dynamics into consideration, thus avoiding a complex control problem involving an infinite-dimensional distributed parameter system. The validity of the proposed method is substantiated by analytical and numerical studies using a mathematical model for the flexible boom which could undergo both bending and torsional vibrations. This approach leads to simple antenna-feed attitude control systems which are amenable to physical implementation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Franklin Institute, Journal (ISSN 0016-0032); 315; May-June
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  • 4
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    A decoupling approach to the control of large spaceborne antenna systems (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A simple practical method for designing antenna-feed positioning control systems for large deployable spaceborne antenna systems with flexible booms is proposed. The approach is based on the mechanical decoupling of the antenna-feed from the boom so that the positioning control system can be designed without taking boom dynamics into consideration, thus avoiding a complex infinite dimensional control problem. The basic idea is illustrated by a simple angular positional control system attached to a flexible boom restricted to torsional motion only. The application of this approach to more complex situations is discussed briefly.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 5
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    A robust nonlinear attitude control law for space stations with flexible structural components (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: In this paper, a nonlinear attitude control law for space stations with flexible structural components is derived using a rigid-body model. This control law, depending on the Cayley-Rodriguez parameters, globally stabilizes the equilibrium of the rigid-body model. The effect of elastic deformations of the flexible structural components on the resulting feedback system dynamics is analyzed. It is found that the system's stability property is highly robust with respect to structural vibrations and inertial variations. The time-domain behavior of the feedback system is studied numerically using a model of a typical space station with flexible solar panels.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 6
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    Disturbance and vibration isolation in space stations by means of mechanical decoupling (1987)
    In:  Other Sources
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    Publication Date: 2019-07-12
    Description: A decoupling approach to disturbance and vibration isolation in large space stations composed of modules interconnected by flexible members is proposed. A simplified mathematical model for the motion of the space station core and a laboratory module with both torsional vibration and translational motion decouplers is used in this study. The dynamic behavior of the model in the presence of decoupler friction is analyzed. Estimates for the maximum excursions of the laboratory module induced by various types of external disturbance are derived. The paper concludes with a simulation study involving the hard-docking of a space shuttle with a space station.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Journal of Control (ISSN 0020-7179); 46; 1061-108
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