Analysis of the rigid solar array, SA-3, design showed that the pointing control system stability margin requirements would be violated because of the modal characteristics of the SA-3 fundamental bending modes. A damping of 1.5% of critical of the SA-3 fundamental bending modes, at the HST system level, is needed to meet the stability margin requirements. A damper, consisting of a titanium flexure and viscoelastic damping material, has been designed, built, and tested, and is an integral part of the SA-3 mast. The viscoelastic material properties are temperature-sensitive, and direct complex stiffness testing was performed to characterize the frequency- and temperature-dependent behavior of the damper. Fixed-base modal testing showed that the optimized damper is expected to provide modal damping of at least 2.25% of critical (fixed base and extrapolated to zero excitation force levels) over the temperature range of 0/spl deg/C to 25/spl deg/C.


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    Title :

    Hubble Space Telescope solar array damper for improving control system stability


    Contributors:
    Anandakrishnan, S.M. (author) / Connor, C.T. (author) / Lee, S. (author) / Shade, E. (author) / Sills, J. (author) / Maly, J.R. (author) / Pendleton, S.C. (author)


    Publication date :

    2000-01-01


    Size :

    1220966 byte





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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