Extendible nozzle exit cone

Claim 2

An extendible nozzle exit cone for a rocket motor comprising, a plurality of concentric nozzle segments, the inner one of said segments being attachable to a rocket motor case, at least one outer segment being movable from a nested position to an extended fully deployed position, each of said segments having a divergent conic inner surface, which surfaces form a single substantially conic surface when said outer segment is in its fully deployed position, folding linkage means for deploying said outer segment 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 said outer segment and the other end attached to the other end of said lever, 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.

Claim 3

An extendible nozzle exit cone for a rocket motor as specified in claim 1 wherein said actuatable translating means comprises a pneumatic cylinder containing a gas generant charge.

Claim 4

An extendible nozzle exit cone for a rocket motor as specified in claim 2 further including a bracket attached to the exterior surface of said inner segment, and wherein said pneumatic cylinder includes a body that is attached to said bracket and a movable rod extending from said body, the end of said rod remote from said body being intermediately pivoted to said lever.

Claim 5

An extendible nozzle exit cone for a rocket motor as specified in claim 1 wherein said plurality of concentric nozzle segments includes two outer segments, wherein said folding linkage means further includes 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, wherein the angle between said second link and the outer one of said outer segments on the side facing away from said exit cone is at least 180°, and wherein the angle between said second link and the inner one of said outer segments on the side facing away from said exit cone is less than 180°.

Claim 6

An extendible nozzle exit cone for a rocket motor as specified in claim 4 wherein said actuatable translating means comprises 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, and the end of said rod remote from said body of said pneumatic cylinder being intermediately pivoted to said lever.

Claim 7

An extendible nozzle exit cone for a rocket motor as specified in claim 4 wherein said inner and outer nozzle segments are provided at their ends with locking shoulders, said locking shoulders including an annular exterior shoulder and adjoining annular recess on the aft end of an upstream segment and an annular interior shoulder and adjoining annular ridge on the forward end of an adjacent downstream segment, said annular shoulders engaging with said annular ridge fitting into said annular recess to lock said adjacent segments together.

Claim 8

An extendible nozzle exit cone for a rocket motor as specified in claim 6 wherein at least one of each pair of shoulders is provided with an elastomeric seal whereby gas tight seals are provided between said segments when said segments are fully deployed in their extended positions.

Claim 9

An extendible nozzle exit cone for a rocket motor as specified in claim 6 wherein said inner nozzle segment includes at the end thereof an annular shoulder and an adjoining recess, wherein each of said outer nozzle segments includes a shoulder and an adjoining ridge at the end thereof that is attached to a link, and includes 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.

Claim 10

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°, 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°, 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.

Claim 11

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°, 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°, 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.

Claim 12

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°, 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°, 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.

Claim 13

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°, 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°, 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.

Claim 14

An extendible nozzle exit cone for a rocket motor as specified in claim 10 wherein said slotted cam extends longitudinally of said extendible nozzle exit cone and includes an inwardly facing curved sutface at its downstream end, and wherein the said cam follower at said one end of said lever and the pivotal connection thereto of the end of said pneumatic cylinder rod are positioned transversely of the length of said lever, whereby upon completion of the stroke of said pneumatic cylinder said cam follower moves into said inwardly facing cam curved surface and said lever is given a rotative movement about said cam follower as a pivot to move the pivotal attachment of the lever and said first and second links to an over center position.