Abstract: A fiber optic module for installation within patch panel, the fiber optic module comprising a first outer wall with a first rail profile on its outside surface, a second outer wall with a second rail profile on its outside surface, and at least one optical connector. The first outer wall and the second outer wall run parallel to each other. The at least one optical connector is arranged between the first outer wall and the second outer wall. The first rail profile and the second rail profile are complementary to each other such that the fiber optic module may be coupled to an adjacent fiber optic module, wherein the first rail profile of the fiber optic module may be coupled to the second rail profile of the adjacent fiber optic module.

Abstract: A fiber optic module for installation within patch panel, the fiber optic module comprising a first outer wall with a first rail profile on its outside surface, a second outer wall with a second rail profile on its outside surface, and at least one optical connector. The first outer wall and the second outer wall run parallel to each other. The at least one optical connector is arranged between the first outer wall and the second outer wall. The first rail profile and the second rail profile are complementary to each other such that the fiber optic module may be coupled to an adjacent fiber optic module, wherein the first rail profile of the fiber optic module may be coupled to the second rail profile of the adjacent fiber optic module.

Abstract: A plurality of pan-shaped beams and supports of graphite/epoxy laminate mrial are mounted on a circular graphite/epoxy aft panel to form a symmetrical structure which is attached to the missile shell. Four main stiffening beams intersect at right angles to form a central square structure with the intersecting walls extending outward beyond the central square to the missile shell. Four diagonal stiffening beams are disposed across the corners within the central square to form a central hexagonal structure. Additional stiffness is provided by strut support beams oriented parallel to the main support beams and support ribs oriented perpendicular to the main support beams.

Abstract: An engine mount to position a rocket engine within a missile stage and to lease the engine upon burn-out. A separation ring comprising a bracket portion and a shroud portion encircles the engine. The bracket is located approximately mid-length of the engine and wound thereon to engage the engine-circling sheath having a grooved and unsymmetrically weakened cross-section. The shroud is joined to the interior of an on-flying missile stage. A small rocket and fail-safe abutment ensure that the motor will be released in a direction opposite to the continuing flight path of the parent stage.