Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1989-01-23
1990-02-13
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
74 56A, 244 316, F41G 722, G01C 1928
Patent
active
048999555
ABSTRACT:
An angle encoder for determining the pitch (or yaw) angle of a gyroscopic mass with respect to the pitch (or yaw) axis of a missile in flight is shown to be the combination of: (a) an optical encoder pattern disposed on the periphery of the gyroscopic mass, such pattern preferably being divided into a substantially equal reflective portion and a nonreflective portion; (b) an optical sensor arrangement having a limited field of view, such arrangement being mounted on the body of the missile to provide a first signal whose level is indicative of the reflective or nonreflective portion in the limited field of view; and (c) circuitry for converting the first signal into a signal indicative of the pitch (or yaw) angle of the missile.
REFERENCES:
patent: 3328595 (1967-06-01), Todd, Jr.
patent: 3886361 (1975-05-01), Wester
patent: 3915019 (1975-10-01), Zoltan
patent: 4123134 (1978-10-01), Meyers
patent: 4600166 (1986-07-01), Califano et al.
Dugas David J.
Fattal Jean A.
Tella Louis L.
Jordan Charles T.
McFarland Philip J.
Raytheon Company
Sharkansky Richard M.
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