Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1982-09-16
1984-06-26
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F41G 700, F42B 1502
Patent
active
044562020
ABSTRACT:
A method of increasing the predictable effectiveness of a ballistic reentry ody having a predicted nominal reentry trajectory. Beginning at reentry or another predetermined location, the distance travelled by said reentry body is calculated based on measured longitudinal acceleration and preset predicted trajectory parameters. When the reentry body reaches a predetermined altitude as measured by an onboard radar, the calculated distance travelled to the altitude is compared with the predicted nominal distance travelled to the altitude to determine the actual trajectory of the reentry body. Based on this actual trajectory, the actual distance travelled from reentry to a preferred fuzing location is determined. When the calculated distance travelled equals the distance required to reach the preferred fuzing location, the fuze signal is sent to the fire set and then to the warhead.
REFERENCES:
patent: 3784800 (1974-01-01), Willoteaux
patent: 3990657 (1976-11-01), Schott
Louis, III Charles A.
Price, Jr. Donald A.
Beers R. F.
Curry C. D. B.
Daubenspeck W. C.
Jordan Charles T.
The United States of America as represented by the Secretary of
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