Self-assembling persistent space platform
A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
1. A spacecraft comprising:
a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration, wherein:
in the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement;
in the on-orbit configuration, the deployable module elements are disposed in a second arrangement;
the spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration; and
in the launch configuration, adjacent ones of the deployable module elements are releasably coupled with a first releasable coupling;
in the on-orbit configuration, the adjacent ones of the deployable module elements are releasably coupled with a second releasable coupling, different from the first releasable coupling
in the transition configuration, both the first releasable coupling and the second releasable coupling are released.
2. The spacecraft of claim 1 , wherein:
in the launch configuration, the deployable module elements are in a stacked arrangement; and
in the on-orbit configuration, the deployable module elements are in a side-by-side arrangement.
3. The spacecraft of claim 1 , wherein at least one of the deployable module elements is a persistent bus services module.
4. The spacecraft of claim 1 , wherein at least one of the deployable module elements is a propulsion module.
5. The spacecraft of claim 1 , wherein at least two of the deployable module elements are replaceable payload modules.
6. A method comprising:
self-assembling an orbiting spacecraft from a launch configuration to an on-orbit configuration; and
operating the orbiting spacecraft in the on-orbit configuration, wherein:
in the launch configuration, a plurality of deployable module elements are disposed in a launch vehicle in a stacked arrangement;
in the on-orbit configuration, the deployable module elements are disposed in a side-by-side arrangement;
at least one of the deployable module elements includes a robotic manipulator operable to reconfigure the orbiting spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration;
in the stacked arrangement, adjacent ones of the deployable module elements are releasably coupled with a first releasable coupling;
in the side-by-side arrangement, the adjacent ones of the deployable module elements are releasably coupled with a second releasable coupling; and
in the transition configuration, both the first releasable coupling and the second releasable coupling are released.
7. The method of claim 6 , wherein self-assembling the orbiting spacecraft includes using the robotic manipulator to reconfigure the spacecraft from the launch configuration, through the transition configuration, to the on-orbit configuration.
8. A system comprising:
a payload for a launch vehicle, the payload including a robotic manipulator and a payload stack including one or more deployable module elements and a plurality of spacecraft including at least a first spacecraft and a second spacecraft, wherein,
at least a first portion of the second spacecraft is disposed, in a launch configuration, forward of the first spacecraft;
at least one of the deployable module elements is disposed, in the launch configuration, in an upper portion of the payload stack, forward of the first portion of the second spacecraft;
the robotic manipulator is operable to reconfigure the payload from the launch configuration, through a transition configuration, to an on-orbit configuration;
in the on-orbit configuration, the at least one deployable module is coupled with the first spacecraft;
in the launch configuration, a first arrangement mechanically couples a first one of the deployable module elements to one or both of the first spacecraft and a second one of the deployable module elements;
in an on-orbit configuration, a second arrangement mechanically couples the first one of the deployable module elements with the second spacecraft; and
in a transition configuration, intermediate to the launch configuration and the on-orbit configuration, each of the first arrangement and the second arrangement is detached from the first one of the deployable module elements.
9. The system of claim 8 , wherein:
at least one of the first spacecraft and the second spacecraft has a first characteristic width transverse to a longitudinal axis of the launch vehicle;
the at least one deployable module elements has a second characteristic width transverse to the longitudinal axis of the launch vehicle; and
the first characteristic width is substantially larger than the second characteristic width.
10. The system of claim 8 , wherein:
at least one of the first spacecraft and the second spacecraft include a plurality of deployable module elements;
in the launch configuration, the plurality of deployable module elements is disposed in a launch vehicle in a stacked configuration such that a third arrangement mechanically couples adjacent ones of the plurality of module elements; and
in the on-orbit configuration, the plurality of deployable module elements is disposed in a side-by-side configuration such that a fourth arrangement mechanically couples adjacent module elements.
11. The system of claim 8 , wherein:
a lower portion of the payload stack includes a first plurality and a second plurality of deployable module elements, the first plurality being associated with the first spacecraft, the second plurality being associated with the second spacecraft; and
an upper portion of the payload stack includes a third plurality and a fourth plurality of deployable module elements, the third plurality being associated with the first spacecraft, the fourth plurality being associated with the second spacecraft.
12. The system of claim 11 , wherein:
the lower portion of the payload stack has a first characteristic width transverse to a longitudinal axis of the launch vehicle;
the upper portion of the payload stack has a second characteristic width transverse to the longitudinal axis of the launch vehicle;
and the first characteristic width is substantially larger than the second characteristic width.
13. The system of claim 11 , wherein the first plurality of the deployable module elements is disposed in an aft region of the lower portion of the payload stack and the second plurality of the deployable module elements is disposed in a forward region of the lower portion of the payload stack.
14. The system of claim 11 , wherein at least one of the first plurality of the deployable module elements is disposed forward of a first subset of the second plurality of deployable module elements and aft of a second subset of the second plurality of deployable module.