Extendible nozzle exit cone

An extendible nozzle exit cone for a rocket motor comprising,

• a plurality of concentric nozzle segments including an inner segment and two outer segments, the inner segment being attachable to a rocket motor case, each of the outer segments being movable from a nested position to an extended fully deployed position, each of said inner and outer segments having a divergent conic inner surface, which surfaces form a single substantially conic surface when each of said outer segments are in their fully deployed positions,
• folding linkage means for deploying said outer segments from the nested position to the extended, fully deployed position, said folding linkage means comprising a lever having a cam follower at one end, a slotted cam in which said cam follower is disposed in cooperative relation, and a first link,
• said first link having one end pivotally attached to the inner one of said outer segments and the other end attached to the other end of said lever,
• said folding linkage means further including a second link, said second link having one end pivotally attached to the outer one of said outer segments and the other end attached to the said other end of said lever,
• the angle between said second link and the outer one of said outer segments on the side facing away from said exit cone being at least 180.degree.,
• the angle between said second link and the inner one of said outer segments on the side facing away from said exit cone being less than 180.degree.,
• said folding linkage means being adjusted into an over center configuration in the fully deployed and extended positions of said outer segments whereby said folding linkage means locks said outer segments against thrust forces of the nozzle, and
• actuatable translating means having a first end and a second end the distance between which is extended upon actuation thereof,
• said translating means having a pivotal connection at said first end to said inner segment, and being intermediately pivoted at said second end to said lever.

An extendible nozzle exit cone for a rocket motor comprising,

• A plurality of concentric nozzle segments including an inner segment and two outer segments, the inner segment being attachable to a rocket motor case, each of the outer segments being movable from a nested position to an extended fully deployed position, each of said inner and outer segments having a divergent conic inner surface, which surfaces form a single substantially conic surface when each of said outer segments are in their extended fully deployed positions,
• folding linkage means for deploying each of said outer segments from the nested position to the extended fully deployed position, said folding linkage means comprising a lever having a cam follower at one end, a slotted cam in which said cam follower is disposed in cooperative relation, and a first link,
• said first link having one end pivotally attached to the inner one of said outer segments and the other end attached to the other end of said lever,
• said folding linkage means further including a second link, said second link having one end pivotally attached to the outer one of said outer segments and the other end attached to the said other end of said lever,
• the angle between said second link and the outer one of said outer segments on the side facing away from said exit cone being at least 180.degree.,
• the angle between said second link and the inner one of said outer segments on the side facing away from said exit cone being less than 180.degree.,
• said inner and outer nozzle segments being provided at their ends with locking shoulders,
• said inner nozzle segment including at the end thereof an annular shoulder and an adjoining recess,
• each of said outer nozzle segments including a shoulder and an adjoining ridge at the end thereof that is attached to a link, and including at the other end thereof a shoulder and an adjoining recess,
• said shoulder and ridge of the intermediate segment cooperating in locking manner with the shoulder and recess of said inner segment, and
• said shoulder and ridge of the outer segment cooperating in locking manner with the shoulder and recess of the intermediate segment, and
• actuatable translating means having a first end and a second end the distance between which is extended upon actuation thereof,
• said actuatable translating means having a pivotal connection at said first end to said inner segment, and being intermediately pivoted at said second end to said lever,
• said actuatable translating means comprising a pneumatic cylinder containing a gas generant charge and having a body and a movable rod extending from said body, and
• further including a bracket attached to the exterior surface of said inner segment,
• said body of said pneumatic cylinder being attached to said bracket,
• the end of said rod remote from said body of said pneumatic cylinder being intermediately pivoted to said lever, and
• the pivotal attachment of the end of said lever and said first and second links moving into an over center position when said segments are fully deployed in their extended positions whereby to lock said exit cone against thrust forces of the nozzle.