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  • 1
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    Performance characterization of the Hubble Space Telescope Rate Gyro Assembly (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An account is given of the design features and performance characteristics of the Rate Gyro Assembly employed by the Hubble Space Telescope's Pointing Control System to effect accurate spacecraft maneuvers and support fine pointing telescope operation, in conjunction with the fine guidance sensors. The rate sensor attitude quantization is 0.00025 arcsec. Fine-pointing stability is the driver for gyro noise performance, while spacecraft-pointing accuracy requirements at the end of maneuvers has driven the gyro scale factor and mechanical alignment stability performance.
    Keywords: SPACECRAFT INSTRUMENTATION
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Line-of-sight performance improvement with reaction-wheel isolation (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Design techniques used to isolate and damp vibrations from the reaction control wheels assembly (RCA) from the structural dynamics of the Hubble Space Telescope are described. The four RCAs can generate sufficient torque for large maneuvers and precision control during fine pointing. The RCAs are to operate continuously during observations and thereby pose the potential of inducing jitter. The image stability must be constrained to less than 0.007 arcsec rms per 24 hr and pointing accuracy must be 0.01 arcsec for 100 hr. Vibration-producing characteristics of the RCAs are identified, and test results are provided from measurements of the magnitudes of the associated disturbances. Design features and test results for the vibration isolators employed with the RCAs to effect viscous damping of RCA axial perturbations are presented. The dampers are expected to reduce jitter effects of RCA operation by a half.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 86-005
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Noise characterization and minimization of a precision gyroscopic rate sensor (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A program has been conducted to evaluate the noise signature of Space Telescope gyros. The Space Telescope gyros provide a three-axis attitude reference using six single-degree-of-freedom gyroscopes operated with pulse rebalance electronics; the rate sensor attitude quantization is 0.00025 arcsec. The results of the noise evaluation program, including error source characterization and identification of candidate design modifications, are summarized together with the results of prototype hardware testing. It is shown that the proposed design modifications can significantly improve the rate sensor noise performance.
    Keywords: SPACECRAFT INSTRUMENTATION
    Type: Automatic control in space 1982; Jul 05, 1982 - Jul 09, 1982; Noordwijkerhout; Netherlands
    Format: text
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    NASA TECHNICAL REPORTS
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