Release mechanism for spin-stabilized self-propelled missiles

Abstract

A release mechanism for facilitating launching a spin-stabilized self-propelled missile, which includes a rotary missile support and a launching support for supporting the rotary missile support for rotation about a spin axis and for movement axially of the spin axis. A nozzle assembly extends between the rotary missile support and the missile coaxial with the spin axis. A separable portion of the nozzle assembly moves axially in an aft direction under the influence of exhaust gases expelled by the missile. The separable portion strikes an abutment on the rotary missile support to effect rapid movement of the rotary missle support axially away from the missile on separation of the separable portion of the nozzle assembly. A low friction bearing is provided for engagement by the rotary missile support at its aft limit position of travel away from the missile to reduce spin momentum induced forces caused by the rotary missile support. Another low friction bearing surrounds the rotary missile support between the support and the launching support to further reduce spin momentum induced forces. A time release mechanism is provided for preventing aft movement of the rotary missile support during a given number of initial revolutions and for releasing the rotary missile support to allow aft movement thereof after the given number of initial revolutions. A prescribed clearance is provided between the missile and the launching support to prevent post-separation collisions between the missile and the lauching support.