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In-orbit evaluation of the control system/structural mode interactions of the OSO-8 spacecraftThe Orbiting Solar Observatory-8 experienced severe structural mode/control loop interaction problems during the spacecraft development. Extensive analytical studies, using the hybrid coordinate modeling approach, and comprehensive ground testing were carried out in order to achieve the system's precision pointing performance requirements. A recent series of flight tests were conducted with the spacecraft in which a wide bandwidth, high resolution telemetry system was utilized to evaluate the on-orbit flexible dynamics characteristics of the vehicle along with the control system performance. The paper describes the results of these tests, reviewing the basic design problem, analytical approach taken, ground test philosophy, and on-orbit testing. Data from the tests was used to determine the primary mode frequency, damping, and servo coupling dynamics for the on-orbit condition. Additionally, the test results have verified analytically predicted differences between the on-orbit and ground test environments, and have led to a validation of both the analytical modeling and servo design techniques used during the development of the control system.
Document ID
19800047494
Document Type
Conference Proceedings
Authors
Slafer, L. I. (Hughes Aircraft Co. El Segundo, Calif., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1979
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Meeting Information
Dynamics and control of large flexible spacecraft(Blacksburg, VA)
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other