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US 6,578,791 B1Granted
Variable gravity bias control system for a guided missile
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorsEverett K. Jenne, H. Lowell Smith
Life of this patent
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Abstract
A missile flight control initiating device for optimizing flight control time and a variable gravity bias device that corrects guidance signals from the missile's guidance computer during the optimized flight control time. These devices function to correct for the droop in trajectory caused by gravity so that the missile passes above the target.
Claims6
A control circuit for an air launched missile comprising:
- a flight control initiating device which includes,
- pressure measuring means for sensing atmospheric pressure, said means having a pressure output signal which is continuous and linear,
- differentiating means connected to said pressure measuring means for determining the rate of change of said pressure output signal and outputting a rate of change pressure signal,
- means for comparing output signals of said pressure measuring means and differentiating means to predetermined values, outputting pulse signals when said output signals equal or exceed predetermined values, and
- gating means for implementing an algorithm to initiate missile flight control, connected to receive pulse signals from said comparing means;
- and
- a variable gravity bias device connected to said flight control initiating device that corrects guidance signals from a missile guidance computer after flight control is initiated.
4 more elements
Dependencies are inferred from the claim text.