Spacecraft systems airlock for international space station access and interface and methods of operation
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.
1. A spacecraft airlock, comprising:
a module defining an interior with an open end, and including:
a closed end opposite the open end of the interior;
a passive common berthing mechanism positioned around the open end, such that the interior is configured to receive pressurized air from an active common berthing mechanism in a berthed configuration with the passive common berthing mechanism;
an exterior surface having at least one attachment mechanism configured to releasably attach one or more vacuum exposed payloads to the exterior surface, wherein the exterior surface is a longitudinal surface between the open end and the closed end; and
an Electrical Power System (EPS) that includes a dual feed power supply configured to interface with a power supply output of the active common berthing mechanism in the berthed configuration, and that is configured to provide one or more of power control, isolation, circuit protection, or regulation to any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
2. The spacecraft airlock of claim 1 , further comprising:
a Command and Data Handling System (CDHS) configured to command and control any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
3. The spacecraft airlock of claim 2 , wherein the CDHS further includes a data storage for the spacecraft airlock.
4. The spacecraft airlock of claim 2 , further comprising:
a data interface between the CDHS and a data port of the active common berthing mechanism; and
a data connection between the CDHS and the at least one attachment mechanism on the exterior surface, such that the CDHS is configured to act as a primary command and data path for any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
5. The spacecraft airlock of claim 1 , further comprising:
an active cooling interface configured to engage with a low temperature cooling loop via the active common berthing mechanism; and
a cooling device engaged with the active cooling interface, and configured to provide active cooling to any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
6. The spacecraft airlock of claim 1 , wherein the EPS is positioned in the interior.
7. The spacecraft airlock of claim 6 , further comprising:
payload avionics positioned within the interior and configured to interface with one or more payload sensors releasably attached to the at least one attachment mechanism of the exterior surface.
8. The spacecraft airlock of claim 1 , further comprising:
a seat track positioned within the interior.
9. The spacecraft airlock of claim 1 , wherein the exterior surface includes at least one grapple point that is configured to be engaged by a robotic arm, the grapple point positioned on the exterior surface such that the robotic arm is operable to transition the spacecraft airlock between the berthed configuration and a deployed configuration.
10. The spacecraft airlock of claim 1 , further comprising:
airlock mechanism core system avionics positioned within the interior.
11. A method of operating a spacecraft airlock, comprising:
operating an engagement between (i) a passive common berthing mechanism positioned around an open end of an interior defined by a module of the spacecraft airlock, and (ii) an active common berthing mechanism, wherein:
the module further includes a closed end opposite the open end of the interior;
the interior is configured to receive pressurized air from the active common berthing mechanism in a berthed configuration with the passive common berthing mechanism;
the module includes an exterior surface having at least one attachment mechanism configured to releasably attach one or more vacuum exposed payloads to the exterior surface; and
the exterior surface is a longitudinal surface between the open end and the closed end; and
operating an engagement between a duel feed power supply of an Electrical Power System (EPS) of the spacecraft airlock and a power supply output of the active common berthing mechanism, the EPS configured to provide one or more of power control, isolation, circuit protection, or regulation to any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
12. The method of claim 11 , further comprising:
operating a data interface between a Command and Data Handling System (CDHS) of the module and a data connection of the active common berthing mechanism, the CDHS configured to command and control any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
13. The method of claim 12 , wherein:
the CDHS provides a data connection from the active common berthing mechanism and the at least one attachment mechanism on the exterior surface, such that the CDHS is configured to act as a primary command and data path for any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
14. The method of claim 11 , further comprising:
operating an engagement between a low temperature cooling loop of the active common berthing mechanism and an active cooling device of the spacecraft airlock that is configured to provide active cooling to any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface.
15. The method of claim 11 , wherein the EPS is positioned in an interior of the module.
16. The method of claim 15 , wherein:
payload avionics of the spacecraft airlock are positioned within the interior and configured to interface with one or more payload sensors releasably attached to the at least one attachment mechanism of the exterior surface.
17. The method of claim 15 , wherein airlock mechanism core system avionics are positioned within the interior.
18. The method of claim 11 , wherein the exterior surface includes at least one grapple point that is configured to be engaged by a robotic arm, the grapple point positioned on the exterior surface such that the robotic arm is operable to transition the spacecraft airlock between the berthed configuration and a deployed configuration.
19. A spacecraft airlock, comprising:
a module defining an interior with an open end, and including:
a passive common berthing mechanism positioned around the open end, such that the interior is configured to receive pressurized air from an active common berthing mechanism in a berthed configuration with the passive common berthing mechanism;
an exterior surface having at least one attachment mechanism configured to releasably attach one or more vacuum exposed payloads to the exterior surface;
an Electrical Power System (EPS) that includes a dual feed power supply configured to interface with a power supply output of the active common berthing mechanism in the berthed configuration, and that is configured to provide one or more of power control, isolation, circuit protection, or regulation to any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface;
a Command and Data Handling System (CDHS) configured to command and control any vacuum exposed payloads releasably attached to the at least one attachment mechanism of the exterior surface;
payload avionics positioned within the interior and configured to interface with one or more payload sensors releasably attached to the at least one attachment mechanism of the exterior surface; and
airlock mechanism core system avionics positioned within the interior.
20. The spacecraft airlock of claim 19 , wherein the exterior surface includes at least one grapple point that is configured to be engaged by a robotic arm, the grapple point positioned on the exterior surface such that the robotic arm is operable to transition the spacecraft airlock between the berthed configuration and a deployed configuration.