Accession Number:

AD0263282

Title:

STUDY OF A SATELLITE ATTITUDE CONTROL SYSTEM USING INTEGRATING GYROS AS TORQUE SOURCES

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-09-01

Pagination or Media Count:

1.0

Abstract:

Some general design criteria are derived and applied to a specific example. The results of the analytical design are compared with those of an analog computer study and also with experimental results from a low-friction platform. The results show the steady-state and transient behavior of the system using single-degree-of-freedom integrating gyros was reasonably good. A major advantage of using gyros for torque sources is that the gyros also act to stabilize the vehicle directly, even in the absence of an external reference, so that when the target is occulted, an alternate reference is not required. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE