Abstract: Daughter missiles 11 are catapulted forward from a mother missile 10 when a rocket motor 12 of the mother no longer accelerates the missiles. A catapult force generated at a piston head 43 by the pressure of gas from the rocket motor on rearward facing surfaces 26 of the daughters is large enough to shear pins 34 holding the daughters to the mother, but only when the forces of reaction of the daughters 11 on the piston 43, due to acceleration, have fallen off. Preferably the daughters are thrown outwardly at release, most preferably by axial spinning of the structure of the mother to which they are mounted.

Abstract: A missile or other moving body comprising a rotatable portion arranged for rotation relative to another portion of the missile or body and control means for rotating said rotatable portion to bring it to any one of a plurality of preselected positions in relation to a datum and for exerting a thrust thereon having a lateral component with respect to the axis of rotation of said rotatable portion to produce a steering effect on the missile or body, said control means including a variable-incidence control surface mounted on the rotatable portion for rotation about a rotary axis transverse to the rotary axis of the rotatable portion, and actuator means responsive to control signals applied thereto for turning said control surface about its rotary axis to a first disposition in which it produces a component thrust causing rotation of said rotatable portion, and a second disposition in which it produces a lateral steering force on the missile.

Abstract: A control circuit having a difference unit to which first and second input signals are in operation applied to produce a signal representative of the differences between the two input signals, a logic circuit connected to receive 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 said predetermined value and on the other side of the datum, an adding unit connected to receive 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, said switch means adapted to switch to a first condition in response to signals from the adding unit having values to one side of the datum and to switch to a second condition in response to signals from the adding unit having values to the other side of the datum.

Abstract: A missile comprising a first rotatable portion arranged for rotation relative to a second rotatable portion of the missile, the first rotatable portion being adapted to be subjected to a thrust causing it to rotate in one sense during the flight of the body and in the absense of any restraining or opposing forces, and said second rotatable portion being adapted to be subjected to a thrust causing it to rotate in the opposite sense during the flight of the body, steering means on said first rotatable portion for exerting a thrust thereon away from the axis of rotation thereof to produce a steering effect on the missile or body, a free gyroscope mounted in the first rotatable portion and arranged to generate an electrical signal representative of the roll deviation of the first rotatable portion from a predetermined roll attitude in space and electromagnetic braking means responsive to said electrical signal to brake the first rotatable portion against the second rotatable portion to bring said first rotatable

Abstract: Disclosed herein is a missile having a rotatable portion arranged for rotation relative to another portion of the missile which contains spacedly mounted electromagnetic coils for respectively operating first and second control member actuator mechanisms for controlling the missile.