Integrated weatherseal/igniter for solid rocket motor

Claim 2

A rocket motor including a nozzle having a throat, a first conical surface converging toward said throat and a second conical surface diverging away from the throat toward the rear or exit end of the motor, and an igniter comprising a tube having a closed end, the tube located in the nozzle throat with said closed end facing toward the exit end, an electrically activated igniter squib located in said tube at the closed end thereof, an ignition charge in the tube and means associated with the opposing end of said tube to hold the charge in place, first retaining means secured to said tube at a location spaced from said closed end and extending outwardly therefrom and engaging said first conical surface of the nozzle, second retaining means including means defining an annular groove on said tube adjacent said closed end and a resilient annular gasket located in said annular groove and projecting outwardly therefrom and firmly and sealingly engaging said second conical surface of the nozzle such that said gasket is under radial compression to provide the sealing effect, and said engagement with said second conical surface creating force components in the axial direction of the nozzle which bring said first retaining means into close abutting relation to said first conical surface thereby to securely position and retain the igniter in the nozzle throat.

Claim 3

The rocket motor according to claim 1 wherein said annular gasket is an O-ring of elastomeric material.

Claim 4

The rocket motor accoridng to claim 1 wherein said first retaining means includes a plurality of segments extending outwardly from the tube from said location at an angle corresponding to the angle of convergence of the first surface, said closed end of the tube including a section of reduced size and said igniter squib being located in such reduced size section.

Claim 5

The rocket motor according to claim 1 wherein said first retaining means includes a plurality of segments extending outwardly from the tube from said location at an angle corresponding to the angle of convergence of the first surface, said closed end of the tube including a section of reduced size and said igniter squib being located in such reduced size section, the segments being of such a flexibility and such a strength that during detonation of the squib the igniter is first held in place and is thereafter allowed to move thus bending the segments inwardly to break the tube and initiate collapse and ejection of the igniter from the rocket in pieces.

Claim 6

The rocket motor according to claim 1 wherein said type is cylindrical.

Claim 7

A rocket motor including a nozzle having a throat, a first conical surface converging toward said throat and a second conical surface diverging away from the throat toward the rear end of the motor, and an igniter comprising a tube having a closed end, the tube located in the nozzle throat with said closed end facing toward the rocket rear end, an igniter and an ignition charge in the tube and means associted with the tube to hold the charge in place, first retaining means secured to said tube at a location spaced from said closed end and extending outwardly therefrom and engaging said first conical surface of the nozzle, second retaining means including means defining an annular groove on said tube adjacent said closed end and a resilient annular gasket located in said annular groove and projecting outwardly therefrom and firmly and sealingly engaging said second conical surface of the nozzle, said annular gasket being compressed by virtue of its contact with said conical surface with such compression giving rise to firm sealing engagement between the second conical surface and the annular gasket and between the latter and the annular groove of the igniter, said compression of said annular gasket against said second conical surface also giving rise to axially directed force components which tend to hold the first retaining means in close engagement with the first conical surface of the nozzle thereby to position and secure the igniter in the nozzle throat.

Claim 8

A rocket motor including a nozzle having a throat, a first conical surface converging toward said throat and a second conical surface diverging away from the throat toward the rear end of the motor, and an igniter comprising a tube having a closed end, the tube located in the nozzle throat with said closed end facing toward the rocket rear end, an igniter and an ignition charge in the tube and means associted with the tube to hold the charge in place, first retaining means secured to said tube at a location spaced from said closed end and extending outwardly therefrom and engaging said first conical surface of the nozzle, second retaining means including means defining an annular groove on said tube adjacent said closed end and a resilient annular gasket located in said annular groove and projecting outwardly therefrom and firmly and sealingly engaging said second conical surface of the nozzle, said annular gasket being compressed by virtue of its contact with said conical surface with such compression giving rise to firm sealing engagement between the second conical surface and the annular gasket and between the latter and the annular groove of the igniter, said compression of said annular gasket against said second conical surface also giving rise to axially directed force components which tend to hold the first retaining means in close engagement with the first conical surface of the nozzle thereby to position and secure the igniter in the nozzle throat.

Claim 9

The motor of claim 6 wherein said gasket comprises an O-ring.