Abstract: A launch vehicle dispenser attach structure is disclosed. The launch vehicle dispenser attach structure includes a launch vehicle adapter, and a polygonal extruded cylinder comprising tapered side and an essentially closed end. The polygonal extruded cylinder connects to the launch vehicle adapter. The tapered sides and the closed end of the polygonal extruded cylinder provide mounting interfaces for connecting satellite dispensers. A mounting interface of the mounting interfaces includes a separation ring for transforming the launch vehicle dispenser attach structure into a free flying satellite. The launch vehicle dispenser attach structure is particularly useful for attaching multiple payload separation systems to launch vehicle.

Abstract: A method and apparatus for deploying satellites is disclosed a satellite deployment mechanism includes an enclosure having at least one door, a lift table implemented therein, and a spring arranged to apply force to the lift table. A mounting system is arranged to allow for the satellite deployment mechanism to be mounted to a portion of a spacecraft. Responsive to opening the at least one door, the spring may cause the lift table to eject one or more satellites from the enclosure.

Abstract: A launch vehicle dispenser attach structure is disclosed. The launch vehicle dispenser attach structure includes a launch vehicle adapter, and a polygonal extruded cylinder comprising tapered side and an essentially closed end. The polygonal extruded cylinder connects to the launch vehicle adapter. The tapered sides and the closed end of the polygonal extruded cylinder provide mounting interfaces for connecting satellite dispensers. A mounting interface of the mounting interfaces includes a separation ring for transforming the launch vehicle dispenser attach structure into a free flying satellite. The launch vehicle dispenser attach structure is particularly useful for attaching multiple payload separation systems to launch vehicle.

Abstract: A method and apparatus for deploying satellites is disclosed a satellite deployment mechanism includes an enclosure having at least one door, a lift table implemented therein, and a spring arranged to apply force to the lift table. A mounting system is arranged to allow for the satellite deployment mechanism to be mounted to a portion of a spacecraft. Responsive to opening the at least one door, the spring may cause the lift table to eject one or more satellites from the enclosure.

Abstract: This disclosure relates generally to a Multiple Payload Expendable Device consisting of a set of cylindrical multiple payload casings, each payload casing exhibiting circular symmetry fluid passages in relation to firing squibs and voltage coded squib actuating circuit that converts existing single payload expendable device systems to multiple payload expendable device systems.

Abstract: A satellite deployer spring mechanism includes a satellite deployer enclosure for containing an associated column of hinged spring element sets. A pair of identically-sized leaf springs each including a sheet of curved metal formed into an approximately rhomboidal shape with opposing acute angles trimmed to form opposing parallel sides. The identically-sized leaf springs are pivotally hinged at the opposing parallel sides to form a compressible and opposing pair of leaf springs as a compressible elliptical leaf spring pair. Each of the identically-sized leaf springs further includes an alignment aperture at the center of the approximately rhomboidal shape for receiving a retention screw, such that the compressible elliptical leaf spring pair may receive a retention screw, thereby forming the hinged leaf spring assembly in a compressed state prior to deployment.

Abstract: This disclosure relates generally to a Multiple Payload Expendable Device consisting of a set of cylindrical multiple payload casings, each payload casing exhibiting circular symmetry fluid passages in relation to firing squibs and voltage coded squib actuating circuit that converts existing single payload expendable device systems to multiple payload expendable device systems.

Abstract: A satellite deployer spring mechanism includes a satellite deployer enclosure for containing an associated column of hinged spring element sets. A pair of identically-sized leaf springs each including a sheet of curved metal formed into an approximately rhomboidal shape with opposing acute angles trimmed to form opposing parallel sides. The identically-sized leaf springs are pivotally hinged at the opposing parallel sides to form a compressible and opposing pair of leaf springs as a compressible elliptical leaf spring pair. Each of the identically-sized leaf springs further includes an alignment aperture at the center of the approximately rhomboidal shape for receiving a retention screw, such that the compressible elliptical leaf spring pair may receive a retention screw, thereby forming the hinged leaf spring assembly in a compressed state prior to deployment.