Abstract: A threaded insert with a replaceable nut element allows a user to replace only the nut element of the threaded insert rather than the entire threaded insert. The threaded insert includes an insertable housing, a replaceable nut, a retaining mechanism, and an attachment mechanism. The insertable housing allows the threaded insert to be engaged within a wall structure and is used to contain the replaceable nut. The replaceable nut allows the threaded insert to be engaged by a fastener such as a screw or bolt. The attachment mechanism allows the replaceable nut to be attached within and detached from the insertable housing. The retaining mechanism further secures the replaceable nut within the insertable housing and also prevents the replaceable nut from rotating within the insertable housing.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: A threaded insert with a replaceable nut element allows a user to replace only the nut element of the threaded insert rather than the entire threaded insert. The threaded insert includes an insertable housing, a replaceable nut, a retaining mechanism, and an attachment mechanism. The insertable housing allows the threaded insert to be engaged within a wall structure and is used to contain the replaceable nut. The replaceable nut allows the threaded insert to be engaged by a fastener such as a screw or bolt. The attachment mechanism allows the replaceable nut to be attached within and detached from the insertable housing. The retaining mechanism further secures the replaceable nut within the insertable housing and also prevents the replaceable nut from rotating within the insertable housing.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: A grapple-fixture deployment device allows for an easy, quick, and safe disposal of an unnecessary payload from a space station. The grapple-fixture deployment device includes a space station remote manipulator system (SSRMS)-securing module, a separation system, a payload-securing module, a first attachment mechanism, and a second attachment mechanism. The SSRMS-securing module allows the grapple-fixture deployment device to be attached to the robotic arm apparatus of a mobile servicing system (MSS). The separation system is a spacecraft deployment system that is used to eject the payload-securing mechanism from the rest of the grapple-fixture deployment device. The payload-securing module allows the grapple-fixture deployment device to be attached to a payload. The first attachment mechanism is used to attach the SSRMS-securing module to the robotic arm apparatus of a MSS. The second attachment mechanism is used to attach the payload-securing module to the payload.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Abstract: A model rocket motor retainer apparatus for model rockets comprised of two components, a cylindrical retainer body (1) and an aft closure ring (2); wherein the retainer body is attached to a rocket motor tube (3), and the aft closure ring attaches into the aft end of the retainer body (3). Installation and tightening of the aft closure ring traps the rocket motor (4) between the aft closure ring and the rocket motor tube, thereby positively retaining the motor.