Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1983-08-22
1993-01-05
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F41G 722
Patent
active
051763370
ABSTRACT:
An electronic activation circuit (1) for automatically transitioning a guided missile from a non-tracking mode to a tracking mode. When the missile's tracking means comprises a gyroscope, the non-tracking mode corresponds to the gyroscope being caged. A parameter indicating target signal quality is extracted (2) from a missile carrier signal (3) generated by means, which may be on board the missile or associated with the device launching the missile, for measuring target signal quality. This signal (3) is compared (6) against a preselected reference threshold voltage (4) to determine whether the tracking mode is to be initiated. Temporary indications to recage during a preselected time delay latch period T are suppressed (8, 10). The quality threshold comparison (6) is hysteresis conditioned (46, 48, 50, 52) to attenuate the effects of noise on the input signal (3). A switch (16) allows the operator to preinitialize the tracking activation circuit (1) prior to the time when the target signal (3) is of sufficient quality to permit tracking, i.e., prior to combat. When the missile leaves its launch rail, an umbilical electrical connection (13, 15) between the missile and rail is severed, preventing the gyroscope from being recaged, by the operator or otherwise, subsequent to missile launch.
REFERENCES:
patent: 3333789 (1967-08-01), Schreiner, Jr.
patent: 3798420 (1974-03-01), Kaaz
Jordan Charles T.
Loral Aerospace Corp.
Radlo Edward J.
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