CONTROL SYSTEMS FOR MISSILES AND OTHER MOVING BODIES

摘要

Disclosed is a control circuit for use in missiles having a nose portion rotatably mounted in bearings on the forward end of a cylindrical main body portion of the missile for rotation about the longitudinal axis of the missile and is provided with aileron and elevator control surfaces. By remote control the nose portion can be brought to a preselected roll attitude. The control circuit ensures that the nose portion takes the shorter path to arrive at a required roll attitude. The control circuit comprises a difference unit to which first and second input signals are in operation applied to produce a signal representative of the difference between the two input signals. A logic circuit receives a signal from the difference unit to produce in response to signals applied thereto exceeding a predetermined value in respect to a datum an output of a constant value equal to twice the predetermined value and on the other side of the datum. An adding unit receives the signal from the logic circuit and the signal from the difference unit to produce an output signal representative of the algebraic sum of the two signals applied to the adding unit. A switching arrangement switches to a first condition in response to signals from the adding unit having values to one side of the datum and to a second condition in response to signals from the adding unit having values to the other side of the datum.