Abstract: A flexible bearing assembly includes at least one metal end ring, a flexible bearing core having a plurality of layers of a resilient material between layers of a reinforcement material, and a phenolic composite material between and bonded to each of the at least one metal end ring and the flexible bearing core. A rocket motor assembly includes a chamber configured to contain a propellant and a movable thrust nozzle coupled to the chamber. The movable thrust nozzle includes a phenolic composite material between and bonded to each of a metal end ring and a flexible bearing core. Methods of forming a flexible bearing assembly include bonding a phenolic composite material to at least one metal end ring and bonding a flexible bearing core to the phenolic composite material. The flexible bearing core includes a plurality of layers of a resilient material between layers of a reinforcement material.

Abstract: A grommet for installation in an opening of a panel comprises an elastically deformable material having a longitudinal axis extending from a proximal end to a distal end of a grommet body. The grommet body comprises an aperture extending longitudinally through the grommet body between the proximal end and the distal end. A wall-engaging segment defines a longitudinal segment of the aperture and is located to be enclosed by a wall of the opening when the grommet is installed in the panel. A clamping element occludes the aperture in the wall-engaging segment and comprises at least one longitudinally extending through-hole sized and configured to receive an elongated element. The clamping element is located to apply a compressive force on the elongated element to retain the elongated element in the through-hole of the grommet body responsive to disposition of the wall-engaging segment in the opening of the panel.

Abstract: A grommet for installation in an opening of a panel comprises an elastically deformable material having a longitudinal axis extending from a proximal end to a distal end of a grommet body. The grommet body comprises an aperture extending longitudinally through the grommet body between the proximal end and the distal end. A wall-engaging segment defines a longitudinal segment of the aperture and is located to be enclosed by a wall of the opening when the grommet is installed in the panel. A clamping element occludes the aperture in the wall-engaging segment and comprises at least one longitudinally extending through-hole sized and configured to receive an elongated element. The clamping element is located to apply a compressive force on the elongated element to retain the elongated element in the through-hole of the grommet body responsive to disposition of the wall-engaging segment in the opening of the panel.

Abstract: A flexible bearing assembly includes at least one metal end ring, a flexible bearing core having a plurality of layers of a resilient material between layers of a reinforcement material, and a phenolic composite material between and bonded to each of the at least one metal end ring and the flexible bearing core. A rocket motor assembly includes a chamber configured to contain a propellant and a movable thrust nozzle coupled to the chamber. The movable thrust nozzle includes a phenolic composite material between and bonded to each of a metal end ring and a flexible bearing core. Methods of forming a flexible bearing assembly include bonding a phenolic composite material to at least one metal end ring and bonding a flexible bearing core to the phenolic composite material. The flexible bearing core includes a plurality of layers of a resilient material between layers of a reinforcement material.

Abstract: Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Abstract: Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Abstract: Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Abstract: Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Abstract: A thermal protection system and a method of manufacturing are disclosed. The thermal protection system may be configured to protect a movable joint, for example, a flexible bearing of a rocket motor nozzle. The thermal protection system includes a series of annular shims separated by a plurality of discrete spacers. Each shim of the series of annular shims may have a larger diameter than the previous shim, and the shims may nest. The shims may comprise a thermally stable material, and the discrete spacers may comprise an elastomer. Optionally, an annular bearing protector may separate the annular shims from the flexible bearing.

Abstract: A thermal protection system and a method of manufacturing are disclosed. The thermal protection system may be configured to protect a moveable joint, for example, a flexible bearing of a rocket motor nozzle. The thermal protection system includes a series of annular shims separated by a plurality of discrete spacers. Each shim of the series of annular shims may have a larger diameter than the previous shim, and the shims may nest. The shims may comprise a thermally stable material, and the discrete spacers may comprise an elastomer. Optionally. an annular bearing protector may separate the annular shims from the flexible bearing.