Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1976-03-15
1979-01-30
Engle, Samuel W.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
244165, F41G 900, F42B 1502, F42B 1500
Patent
active
041368444
ABSTRACT:
An inertial guidance system including a true space stable platform is provided while retaining a simple two-degree-of-freedom gimbal system. An added third degree of freedom is provided by motions of the support itself which maintains desired platform orientation. The output of a third axis instrument is used to maneuver the frame itself about the axis of the frame which most nearly will null any rotation about the platform roll or longitudinal axis. A rotational rate gyroscope is positioned on the space stable platform, and actuates the movement of the frame about the longitudinal or roll axis directly from the reading of the rotational movement along the roll axis of the platform.
REFERENCES:
patent: 3263944 (1966-08-01), Watson
patent: 3365148 (1968-01-01), Preston et al.
patent: 3412239 (1968-11-01), Seliger et al.
patent: 3491228 (1970-01-01), Selvin
patent: 3746281 (1973-07-01), Stripling
Bissell Henry M.
Engle Samuel W.
General Dynamics Corporation
Johnson Edward B.
Webb Thomas H.
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