Abstract: A pneumatic actuator for deploying flexible bodies and the like is disclosed. The actuator is a plurality of telescoping tubes made of high temperature resistant graphite material which are extended by the pressure of gases produced internally by a gas generator contained within the innermost tube. The extended tubes are locked in position automatically and venting of the gases from the tube interior is provided for simultaneously with full and locked extension of the tubes.

Abstract: A braided preform fabrication for annular refractory articles such as an integral monolithic throat section and exit cone of a rocket motor nozzle is formed on a mandrel and includes closely spaced radially oriented carbon rods that extend to a uniform length from the mandrel surface and carbon fibers braided on the surface of the mandrel around the carbon rods in a triaxial braid whereby the fabrication has a 4-D fiber architecture. The density of the fabrication is increased by a process that is repeated four times and involves the steps of vacuum impregnation thereof with pitch, subjecting the impregnated preform to high pressure at a temperature that is gradually increased to about 700.degree. C. to convert the pitch to coke and to form the braided preform and mandrel into a billet, and producing graphitization of the braided preform by subjecting the billet to an argon atmosphere in a vacuum furnace at a temperature that is gradually increased to 2,500.degree. C.

Abstract: A normally collapsed but extendible nozzle exit cone for the second or upper stage of a missile having a first or lower stage includes three concentrically disposed linear segments each of which is a hollow, truncated cone larger than the adjacent upstream segment. The mechanism for translating the segments from their collapsed or stowed state to their deployed state includes a plurality of pneumatic cylinders, each of which contains a gas generant charge, and a set of folding linkages associated with each pneumatic cylinder that are attached to the movable segments of the exit cone. The segments of the exit cone are provided at their ends with locking shoulders and one shoulder of each pair includes an elastomeric seal so that gas tight seals are provided between the segments, as they are aligned. An over-center action of each of the folding linkages locks the extended exit cone adjacent thrust forces of the nozzle.

Abstract: A non-radiating cloth exit cone for a rocket nozzle includes a flared woven refractory cloth structure having the shape of the frustum of a cone with a refractory felt sewn to the exterior surface of the cloth structure for thermal insulation of the cloth structure and a sacrificial ablative material comprising tufts of refractory material incorporated in the interior surface of the cloth structure, the cloth structure providing the primary supporting structure for transmitting the rocket motor thrust forces to the rocket nozzle.

Abstract: A convergent-divergent rocket nozzle is made to be extendible by moving successively larger, conic annuli into a tandem arrangement therewith, so that they collectively form a single exit cone. In a stowed position, the movable, conic annuli concentrically surround the primary nozzle. Each of these movable segments of the nozzle is moved relative to its adjacent upstream segment by being attached to rotary means that engage elongated positive traction surfaces on a set of guide members that are spaced circumferentially about and fixed at each end to the upstream segment, parallel to the axis of the nozzle. The rotary means are actuated, by means of a flexible shaft, by a small, electric motor that is mounted to each movable segment. When in fully deployed position, each movable segment is locked in place by tang latches, fixed to the adjcent, upstream segment, that engage an internal flange or shoulder on the movable segment.

Abstract: A rocket motor expansion cone extension skirt of the combustion gas deployable type is purposely delayed in its deployment by an erodable barrier in the motor's expansion cone upstream of the extension and which diverts combustion gas away from the skirt to prevent its deployment. The barrier is eroded away by the gases after a brief predetermined period of time long enough to permit the rocket motor to clear other structures in a situation such as may occur during vehicle stage separation, after which time deployment of the skirt occurs.