NASA NTRS · 19820002203
Spacecraft attitude pointing performance during orbit adjust as a function of compensator order
Abstract
A steady state compensator of specified order is proposed to estimate the required duty cycle needed to balance the distribution torque. The compensator was increased gradually to demonstrate the improvement in pointing accuracy. The basic mathematical model of the flexible spacecraft and sensor used to characterize the performance of the compensator are described.
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Basuthakur, S., Duelfer, R., Peckjian, A., Stick, T.. 1981-10-01. Spacecraft attitude pointing performance during orbit adjust as a function of compensator order. https://ntrs.nasa.gov/citations/19820002203
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