Rocket catapult

DETAILED DESCRIPTION I claim: 1.
In a rocket catapult ejection system for a seat-occupant mass of an aircraft having a catapult tube secured to said aircraft and rocket motor means having a head member at one end attached to an aircraft seat structure, a guide tube secured at one end to said head member, slidably mounted on said catapult tube, and having a spherical pintle at its other end, a booster cartridge seated in said head member and extending into said catapult tube, releasable locking pin means initially securing said guide tube and catapult tube against relative longitudinal motion, a control piston in said catapult tube and responsive to ignition of said booster cartridge for releasing said locking pin means, a rocket tube secured at one end to said head member, surrounding and concentrically spaced from said guide tube, and housing a main rocket propellant grain, a nozzle housing having a reduced portion slidably mounted in said rocket tube and an inclined throat member surrounding a portion of said spherical pintle to define an annular nozzle effective throat therebetween for providing a thrust vector of generated rocket gases at a predetermined angle inclination to the longitudinal axis of said guide tube and in alignment with a predetermined seat occupant mass center of gravity, means biasing said nozzle housing away from said rocket tube, and means for adjustably camming said nozzle housing to a desired position along the longitudinal axis of said guide tube in opposition to said biasing means, so constructed and arranged that said rocket thrust vector can be adjusted for deviations in said seat occupant mass center of gravity.
2.
The structure in accordance with claim 1 wherein said camming means includes a split cylindrical bushing rotatably mounted in said rocket tube and having at one end thereof camming surface means, and said nozzle housing having cam follower means in contact with said camming surface means.
3.
The structure of claim 2 wherein said split bushing has a pair of longitudinally spaced, outwardly extending annular ribs, and said rocket tube having an internal surface containing a laterally extending annular groove, one of said annular ribs extending into said annular groove and the other annular rib extending outwardly between said rocket tube and said biasing means