Guidance systems

Details Guidance systems Guidance systems

1968-09-11

1982-03-09

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

F41G 726

Patent

active

043185150

ABSTRACT:
In an aerial or space missile guidance system, the direction of the resultant applied force vector relative to the line of sight from the missile to the target is controlled by measuring the rate of turn of the line of sight and turning the missile frame appropriately until the resultant force vector points in a direction to reduce any error in the missile flight path. A signal representing rate of turn of the line of sight is derived, amplified by a predetermined multiplication factor, and then algebraically summed with a second signal representing the angle between the resultant force vector and the longitudinal axis of the missile. The result of this first summation is then algebraically summed with a third signal representing the angle between the missile longitudinal axis and the target line of sight to obtain an error signal for application to the missile control actuation system.

REFERENCES:
patent: 2826380 (1958-03-01), Ketchledge

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