Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1976-08-02
1978-08-22
Pendegrass, Verlin R.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
244 316, 244 319, F42B 1510
Patent
active
041084004
ABSTRACT:
A dual mode missile guidance system employing a passive anti-radiation ser for midcourse guidance and an alternate sensor for terminal guidance. A broadband, body mounted conformal antenna comprises the midcourse sensor, and the alternate sensor is mounted on a stabilized platform within the missile radome. Detected video guidance signals from the midcourse sensor are video processed and utilized to adjust the system phase shifters for null tracking as well as for driving the stabilized platform to keep the alternate sensor directed at the target. Upon the occurrence of a predetermined condition, a handover switch connects the detected video guidance signals provided by the alternate guidance sensor processor for video processing and for control of the stabilized platform. Auto pilot signals are derived from the rate gyros mounted on the stabilized platform.
REFERENCES:
patent: 3064924 (1962-11-01), Fairbanks
patent: 3165749 (1965-01-01), Cushner
patent: 3743215 (1973-07-01), Harris
patent: 3844506 (1974-10-01), Stavis et al.
Borunda Gabriel S.
Groutage Frederick D.
Fendelman H.
Pendegrass Verlin R.
Rubens G. J.
Sciascia R. S.
The United States of America as represented by the Secretary of
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