On-orbit assembly of communication satellites

1. A method comprising:

reconfiguring a spacecraft from a launch configuration to an on-orbit configuration, wherein

the spacecraft includes a main body structure, a manipulator and at least a first deployable element;

in the launch configuration, the spacecraft is disposed within a launch vehicle fairing and the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement;

in the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement;

in a transition configuration, intermediate to the launch configuration and the on-orbit configuration, both the first arrangement and the second arrangement are detached from the first deployable element;

reconfiguring includes:

detaching the first deployable element from the first arrangement;

moving the first deployable element with respect to the spacecraft main body structure; and

attaching the first deployable element to the second arrangement; and

the manipulator is configured to grasp the first deployable element;

move the first deployable element from a first position proximate to the first arrangement to a second position proximate to the second arrangement; and

release the first deployable element.

2. The method of claim 1 , wherein:

the spacecraft further includes:

a structural interface adapter for mating to a launch vehicle;

an aft surface disposed proximate to the structural interface adapter;

a forward surface disposed opposite to the aft surface;

a main body structure disposed between the aft surface and the forward surface; and,

in the launch configuration, the first deployable element is disposed forward of the forward surface and, in the on-orbit configuration, is disposed, deployed, so as to be substantially outboard of the main body structure.

3. The method of claim 2 , wherein:

the first deployable element is an antenna reflector having an aperture plane, and, in the launch configuration, the antenna reflector is disposed with the aperture plane substantially parallel to the forward surface.

4. The method of claim 3 , wherein, in the launch configuration, a centroid of the aperture plane is substantially aligned with launch vehicle longitudinal axis.

5. The method of claim 2 , wherein the first arrangement is a launch holddown device and the second arrangement includes one or more of a spacecraft structural element, a hinged joint, an actuator, a two axis positioning mechanism, and a three axis positioning mechanism.

6. The method of claim 1 wherein, in the transition configuration, the first deployable element is coupled with the spacecraft only by way of a mechanical linkage, the mechanical linkage including the manipulator.

7. The method of claim 6 , wherein the manipulator is further configured to attach the deployable element to the second arrangement.

8. The method of claim 6 , wherein:

the spacecraft further includes at least a second deployable element; and

the manipulator is configured to:

grasp the second deployable element;

move the second deployable element; and

release the second deployable element.

9. The method of claim 6 , wherein the manipulator is a self relocatable robotic arm, the robotic arm including at least two end effectors, and a plurality of articulable joints disposed between the at least two end effectors.