Solid propellant rocket motor

TL;DR: In this paper, a thin membrane of high strength but ductile material is placed over a perforated structural support, thus allowing high pressure on the membrane side of the support to separate one chamber from another.

TL;DR: A passive chamber wall fragmenter adapted to be mounted on or in connection with a portion of a chamber wall which is mounted to be dislodged by a pressure differential across the wall portion, wherein the fragmenter is adapted to become active upon displacement of the wall part to cause the displaced wall portion to fragment or break up into small pieces so as to minimize damage that might result from larger pieces striking sensitive structure making up the chamber as mentioned in this paper.

TL;DR: In this article, the authors propose a partition arrangement for rocket motors with at least two mutually independent thrust stages and nozzle and nose sides, where a partition member separates a combustion chamber on the nozzle side from another combustion chamber in the nose side with the partition member being provided with a flow aperture therein.

TL;DR: In this paper, a solid propellant grain for a gas generator such as a missile canister erection actuator is presented, where a gap is provided between the plug and the wall of the cavity to provide effective propellant burnign surface area along the cavity wall for the boost phase.

TL;DR: In this article, the authors used a RUPTURBLE MEMBRANE SEAL ASSEMBLY to separate the zones of a gas generator from a solid propulsion wheel.

TL;DR: In this article, the authors present an experiment with an opposition system between the COMBUSTION CHAMBER of a GAS GENERATOR and a SRS MOTOR.