Ms. Morgan M. Van Arsdall Profile

Morgan M. Van Arsdall

Systems Engineer at Lockheed Martin Corp

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Proceedings Article | 30 June 2006 Paper

The Hubble Space Telescope attitude observer anomaly

Morgan Van Arsdall, Patrick Ramsey, Scott Swain

Proceedings Volume 6270, 62701K (2006) https://doi.org/10.1117/12.672457

KEYWORDS: Gyroscopes, Thermal effects, Stars, Current controlled current source, Hubble Space Telescope, Control systems, Space telescopes, Telescopes, Space operations, Mirrors

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In mid-2004, the Hubble Space Telescope (HST) began experiencing occasional losses of lock during Fine Guidance Sensor (FGS) guide star acquisitions, threatening a potential loss of science. These failures were associated with an increasing disparity between the FGS-derived estimates of gyro bias calculated in orbit day and those calculated in orbit night. Early efforts to mitigate the operational effects of this Attitude Observer Anomaly (AOA) succeeded; however, the magnitude of the anomaly continued to increase at a linear rate and operational problems resumed in mid-2005. Continued analysis led to an additional on-orbit mitigation strategy that succeeded in reducing the AOA signature. Before the investigation could be completed, HST began operations under the life-extending Two Gyro Science mode. This eliminated both the operational effects of and the visibility into the AOA phenomenon. Possible causes of the anomaly at the vehicle system level included component hardware failures, flight software errors in control law processing, distortion of the telescope optical path, and deformation of vehicle structure. Although the mechanism of the AOA was not definitively identified, the Anomaly Review Board (ARB) chartered to investigate the anomaly concluded that the most likely root cause lies within one of HST's 6 rate-integrating gyroscopes. This paper provides a summary of the initial paths of investigation, the analysis and testing performed to attempt to isolate the source, and a review of the findings of the ARB. The possibility of future operational impacts and available methods of on-orbit mitigation are also addressed.

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