On-orbit assembly of communication satellites

Patent metadata

Field	Value
Publication number	US-2016264264-A1
Application number	US-201514642486-A
Country	US
Kind code	A1
Filing date	Mar 9, 2015
Priority date	Mar 9, 2015
Publication date	Sep 15, 2016
Grant date	—

Abstract

A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, 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. Reconfiguring the spacecraft 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.

First claim

What is claimed is:

1 . A spacecraft, comprising:
a main body structure; and at least a first deployable element, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration, wherein:
in the launch configuration, 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; and
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.

2 . The spacecraft of claim 1 , further comprising:
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; and a main body structure disposed between the aft surface and the forward surface; wherein:
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 spacecraft 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 spacecraft of claim 3 , wherein, in the launch configuration, a centroid of the aperture plane is substantially aligned with a launch vehicle longitudinal axis

5 . The spacecraft 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 spacecraft 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 a manipulator.

7 . The spacecraft of claim 6 , wherein 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.

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

9 . The spacecraft of claim 6 , further comprising at least a second deployable element, wherein the manipulator is configured to:
grasp the second deployable element; move the second deployable element; and release the second deployable element.

10 . The spacecraft 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.

11 . A method comprising:
reconfiguring a spacecraft from a launch configuration to an on-orbit configuration, wherein
the spacecraft includes a main body structure and at least a first deployable element;
in the launch configuration, 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; and
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.

12 . The method of claim 11 , 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.

13 . The method of claim 12 , 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.

14 . The method of claim 13 , wherein, in the launch configuration, a centroid of the aperture plane is substantially aligned with launch vehicle longitudinal axis

15 . The method of claim 12 , 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.

16 . The method of claim 11 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 a manipulator.

17 . The method of claim 16 , wherein 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.

18 . The method of claim 17 , wherein the manipulator is further configured to attach the deployable element to the second arrangement.

19 . 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.

20 . The spacecraft of claim 16 , 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.

Assignees

• Space Systems/Loral LLC

Inventors

• Helmer Robert Edward
• Lymer John Douglas

Classifications

• B64G1/66 Primary

  Arrangements or adaptations of apparatus or instruments, not otherwise provided for · CPC title

• B64G2004/005

  Robotic manipulator systems for use in space · CPC title

• B64G4/00

  Tools specially adapted for use in space · CPC title

• B64G1/2228

  characterised by the hold-down or release mechanisms · CPC title

• B64G1/641

  Interstage or payload connectors (docking systems B64G1/646) · CPC title