Extendable antenna reflector deployment techniques

1. A spacecraft, the spacecraft being reconfigurable between a launch configuration and an on-orbit configuration, the spacecraft comprising:

a forward surface;

an aft surface;

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

a first rigid antenna reflector, wherein the first rigid antenna reflector is:

(i) disposed, in the launch configuration, in a first position forward of the forward surface, and

(ii) disposed, in the on-orbit configuration, a first distance outboard of the main body and a second distance forward of the first position, the first distance and the second distance being substantially orthogonal to one another;

a first antenna feed associated with the first rigid antenna reflector;

a mechanism configured to move the first rigid antenna reflector between the launch configuration and the on-orbit configuration, wherein the mechanism comprises:

an elevator tower disposed with a first end proximate to the forward surface and a second end substantially forward of the main body; and

an elevator truck, wherein the elevator truck is configured to translate a first pivot along the elevator tower from a first position at the first end of the elevator tower to a second position at the second end of the elevator tower, wherein translation of the elevator truck along the elevator tower causes the first rigid antenna reflector to move between the launch configuration and the on-orbit configuration

a first reflector boom having a first proximal end and a first distal end located along a longitudinal axis, the first proximal end coupled with the elevator truck via the first pivot and the first distal end coupled with the first rigid antenna reflector, wherein,

in the on-orbit configuration, the elevator truck is in the second position, the first reflector boom is extended away from the elevator tower and rotated about the first pivot, and the first rigid antenna reflector is illuminated by the first antenna feed.

2. The spacecraft of claim 1 , wherein, in the launch configuration, the aperture plane of the first rigid antenna reflector is substantially normal to the rotational axis of the first pivot.

3. The spacecraft of claim 1 , further comprising a drive mechanism configured to move the elevator truck between the first position and the second position.

4. The spacecraft of claim 1 , further comprising an elevator track, wherein:

the elevator track spans between the first position and the second position, and

the elevator track is configured to guide the elevator truck during translation of the elevator truck between the first position and the second position.

5. The spacecraft of claim 1 , wherein:

the elevator tower includes a first fixed pivot point, the first fixed pivot point being engaged with the first reflector boom so as to permit rotation of the boom about the first fixed pivot point and to permit translation of the first reflector boom with respect to the first fixed pivot point along the longitudinal axis of the first reflector boom, and

the mechanism is configured such that translation of the elevator truck simultaneously rotates the first reflector boom about the first pivot and the first fixed pivot point and translates the first reflector boom, with respect to the first fixed pivot point, along the longitudinal axis.

6. The spacecraft of claim 3 , wherein the drive mechanism is coupled with a motor and selected from the group consisting of a ball or lead screw, a cable and drum, or a rack and pinion.

7. The spacecraft of claim 1 , further comprising at least one latch movable between a first latch position and a second latch position, wherein:

the at least one latch prevents the elevator truck from moving from the second position when the elevator truck is in the second position and the at least one latch is in the first latch position, and

the at least one latch does not prevent the elevator truck from moving from or to the second position when the at least one latch is in the second latch position.

8. The spacecraft of claim 1 , wherein the first antenna feed is located approximately midway between the forward surface and the aft surface.

9. The spacecraft of claim 1 , wherein the first reflector boom deploys to the east side of the spacecraft with respect to the orientation of the spacecraft when in normal operational orbit.

10. The spacecraft of claim 1 , wherein the first reflector boom deploys to the north side of the spacecraft with respect to the orientation of the spacecraft when in normal operational orbit.

11. The spacecraft of claim 1 , wherein the mechanism further comprises:

a first positioning mechanism coupled with the first rigid antenna reflector, wherein:

the first distal end of the first reflector boom is coupled with the first rigid antenna reflector via the first positioning mechanism; and

in the launch configuration, the elevator truck is in the first position, the first reflector boom is drawn into a stowed position, the aperture plane of the first rigid antenna reflector is substantially parallel to the spacecraft yaw axis, and a substantial portion of the first rigid antenna reflector is forward of the forward surface and inboard of the main body.

12. The spacecraft of claim 11 , wherein the first positioning mechanism is configured to provide dual-axis rotation.

13. The spacecraft of claim 11 , further comprising:

a second rigid antenna reflector, wherein the second rigid antenna reflector is:

(i) disposed, in the launch configuration, in a second position forward of the forward surface, and

(ii) disposed, in the on-orbit configuration, a third distance outboard of the main body and a fourth distance forward of the second position, the third distance and the fourth distance being substantially orthogonal to one another; and

a second antenna feed associated with the second rigid antenna reflector; and wherein the mechanism further comprises:

a second positioning mechanism coupled with the second rigid antenna reflector;

a second reflector boom having a second proximal end and a second distal end, the second proximal end coupled with the elevator truck via a second pivot, wherein the second pivot translates with the elevator truck, and the second distal end coupled with the second rigid antenna reflector via the second positioning mechanism, wherein:

in the launch configuration, the second reflector boom is drawn into the stowed position, the aperture plane of the second rigid antenna reflector is substantially parallel to the spacecraft yaw axis, and a substantial portion of the second rigid antenna reflector is forward of the forward surface and inboard of the main body, and

in the on-orbit configuration, the second reflector boom is extended away from the elevator tower and rotated about the second pivot, and the first rigid antenna reflector is illuminated by the second antenna feed.

14. The spacecraft of claim 13 , wherein:

the first reflector boom is coupled with the second reflector boom with a bi-fold strut,

the bi-fold strut is coupled with the first reflector boom between the first proximal end and the first distal end, and

the bi-fold strut is coupled with the second reflector boom between the second proximal end and the second distal end.

15. The spacecraft of claim 13 , further comprising:

a third rigid antenna reflector, wherein the third rigid antenna reflector is:

(i) disposed, in the launch configuration, in a third position forward of the forward surface, and

(ii) disposed, in the on-orbit configuration, a fifth distance outboard of the main body and a sixth distance forward of the third position, the fifth distance and the sixth distance being substantially orthogonal to one another;

a third antenna feed associated with the third rigid antenna reflector;

a fourth rigid antenna reflector, wherein the fourth rigid antenna reflector is:

(i) disposed, in the launch configuration, in a fourth position forward of the forward surface, and

(ii) disposed, in the on-orbit configuration, a seventh distance outboard of the main body and an eighth distance forward of the fourth position, the seventh distance and the eighth distance being substantially orthogonal to one another;

a fourth antenna feed associated with the fourth rigid antenna reflector; and wherein the mechanism further comprises:

a third positioning mechanism coupled with the third rigid antenna reflector and to the first distal end; and

a fourth positioning mechanism coupled with the fourth rigid antenna reflector and the second distal end, wherein:

in the launch configuration, the aperture planes of the third rigid antenna reflector and the fourth rigid antenna reflector are substantially parallel to the spacecraft yaw axis, and the third rigid antenna reflector and the fourth rigid antenna reflector are forward of the forward surface and inboard of the main body, and

in the on-orbit configuration, the third rigid antenna reflector and the fourth rigid antenna reflector are illuminated by the third antenna feed and fourth antenna feed, respectively.

16. The spacecraft of claim 15 , further comprising:

a first crossboom, the first crossboom coupled with the first positioning mechanism at a first end of the first crossboom, the first crossboom coupled with the third positioning mechanism at a second end of the first crossboom, and the first crossboom coupled with the first distal end between the first end and the second end of the first crossboom, wherein the first rigid antenna reflector and the third rigid antenna reflector are coupled with the first reflector boom via the first crossboom; and

a second crossboom, the second crossboom coupled with the second positioning mechanism at a first end of the second crossboom, the second crossboom coupled with the fourth positioning mechanism at a second end of the second crossboom, and the second crossboom coupled with the second distal end between the first end and the second end of the second crossboom, wherein the second rigid antenna reflector and the fourth rigid antenna reflector are coupled with the second reflector boom via the second crossboom.

17. An antenna reflector deployment mechanism for a spacecraft, the antenna reflector deployment mechanism being reconfigurable between a launch configuration and an on-orbit configuration, configured to be mounted to a forward surface of a main body of the spacecraft, and comprising:

an elevator tower, wherein the elevator tower is configured to be disposed with a first end proximate to the forward surface and a second end further away from the forward surface of the spacecraft;

an elevator truck, wherein the elevator truck is configured to translate a first pivot along the elevator tower from a first position at the first end of the elevator tower to a second position at the second end of the elevator tower;

a first rigid antenna reflector;

a first reflector boom having a first proximal end and a first distal end, the first proximal end coupled with the elevator truck via the first pivot and the first distal end coupled with the first rigid antenna reflector,

wherein, in the on-orbit configuration, the elevator truck is in the second position, the first reflector boom is extended away from the second end of the elevator tower at a substantial angle with respect to the elevator tower, and the aperture plane of the first rigid antenna reflector is substantially parallel to the rotational axis of the first pivot, and

wherein the first rigid antenna reflector is:

disposed, in the launch configuration, in a first position forward of the forward surface, and

disposed, in the on-orbit configuration, a first distance outboard of the main body and a second distance forward of the first position, the first distance and the second distance being substantially orthogonal to one another, and

translation of the elevator truck along the elevator tower causes the first rigid antenna reflector to move between the launch configuration and the on-orbit configuration.

18. The antenna reflector deployment mechanism of claim 17 , wherein the first rigid antenna reflector is characterized by a focal length, the focal length being no less than the axial length of the main body along the yaw axis.

19. The antenna reflector deployment mechanism of claim 17 , further comprising:

a first positioning mechanism configured to be coupled with the first rigid antenna reflector, wherein:

the first rigid antenna reflector is coupled with the first distal end via the first positioning mechanism;

in the launch configuration, the elevator truck is in the first position, the first reflector boom is drawn into a stowed position, the aperture plane of the first rigid antenna reflector is substantially parallel to the elevator tower, and a substantial portion of the first rigid antenna reflector is between the first end and the second end of the elevator tower; and

in the on-orbit configuration, the aperture plane of the first rigid antenna reflector is substantially parallel to the rotational axis of the first pivot, and the first rigid antenna reflector is illuminated by the first antenna feed.

20. The antenna reflector deployment mechanism of claim 19 , wherein, in the launch configuration, the aperture plane of the first rigid antenna reflector is substantially normal to the rotational axis of the first pivot.

21. The antenna reflector deployment mechanism of claim 19 , wherein:

the elevator tower includes a first fixed pivot point, the first fixed pivot point being engaged with the first reflector boom so as to permit rotation of the boom about the first fixed pivot point and to permit translation of the boom with respect to the first fixed pivot point along the longitudinal axis of the boom;

the mechanism is configured such that translation of the elevator truck simultaneously rotates the first reflector boom about the first pivot and the first fixed pivot and translates the first reflector boom, with respect to the first fixed pivot point, along the longitudinal axis.

22. The antenna reflector deployment mechanism of claim 19 , wherein the first positioning mechanism is configured to provide dual-axis rotation.

23. The antenna reflector deployment mechanism of claim 19 , further comprising:

a second rigid antenna reflector;

a second positioning mechanism configured to be coupled with the second rigid antenna reflector; and

a second reflector boom having a second proximal end and a second distal end, the second proximal end coupled with the elevator truck via a second pivot and the second distal end coupled with the second rigid antenna reflector via the second positioning mechanism, wherein:

in the launch configuration, the second reflector boom is drawn into a stowed position, the aperture plane of the second rigid antenna reflector is substantially parallel to the elevator tower, and a substantial portion of the second rigid antenna reflector is between the first end and the second end of the elevator tower,

in the on-orbit configuration, the second reflector boom is extended away from the second end of the elevator tower at a substantial angle with respect to the elevator tower, and the aperture lane of the second rigid antenna reflector is substantially parallel to the rotational axis of the first pivot, and

the second rigid antenna reflector is:

disposed, in the launch configuration, in a second position forward of the forward surface, and

disposed, in the on-orbit configuration, a third distance outboard of the main body and a fourth distance forward of the second position, the third distance and the fourth distance being substantially orthogonal to one another.

24. The antenna reflector deployment mechanism of claim 17 , further comprising a drive mechanism configured to move the elevator truck between the first position and the second position.

25. The antenna reflector deployment mechanism of claim 17 , further comprising an elevator track, wherein:

the elevator track spans between the first position and the second position, and

the elevator track is configured to guide the elevator truck during translation of the elevator truck between the first position and the second position.

26. The antenna reflector deployment mechanism of claim 24 , wherein the drive mechanism is coupled with a motor and selected from the group consisting of a ball or lead screw, a cable and drum, or a rack and pinion.

27. The antenna reflector deployment mechanism of claim 17 , further comprising at least one latch movable between a first latch position and a second latch position, wherein:

the at least one latch prevents the elevator truck from moving from the second position when the elevator truck is in the second position and the at least one latch is in the first latch position, and

the at least one latch does not prevent the elevator truck from moving from or to the second position when the at least one latch is in the second latch position.

28. The antenna reflector deployment mechanism of claim 23 , wherein:

the first reflector boom is coupled with the second reflector boom with a bi-fold strut,

the bi-fold strut is coupled with the first reflector boom between the first proximal end and the first distal end, and

the bi-fold strut is coupled with the second reflector boom between the second proximal end and the second distal end, wherein the bi-fold strut is configured to:

unfold as the antenna reflector deployment mechanism is reconfigured from the launch configuration to the on-orbit configuration, and

stiffen the first reflector boom and the second reflector boom when the antenna reflector deployment mechanism is in the on-orbit configuration.

29. The antenna reflector deployment mechanism of claim 23 , further comprising:

a third rigid antenna reflector;

a fourth rigid antenna reflector;

a third positioning mechanism configured to be coupled with the third rigid antenna reflector and to the first distal end; and

a fourth positioning mechanism configured to be coupled with the fourth rigid antenna reflector and the second distal end, wherein:

in the launch configuration, the aperture planes of the third rigid antenna reflector and the fourth rigid antenna reflector are substantially parallel to the elevator tower, and a substantial portion of the third rigid antenna reflector and a substantial portion of the fourth rigid antenna reflector are between the first end and the second end of the elevator tower,

in the on-orbit configuration, the aperture planes of the third rigid antenna reflector and the fourth rigid antenna reflector are substantially parallel to the rotation axis of the first pivot rotational axis and the second pivot rotational axis, respectively,

the third rigid antenna reflector is:

disposed, in the launch configuration, in a third position forward of the forward surface, and

disposed, in the on-orbit configuration, a fifth distance outboard of the main body and a sixth distance forward of the third position, the fifth distance and the sixth distance being substantially orthogonal to one another, and

the fourth rigid antenna reflector is:

disposed, in the launch configuration, in a fourth position forward of the forward surface, and

disposed, in the on-orbit configuration, a seventh distance outboard of the main body and an eighth distance forward of the fourth position, the seventh distance and the eighth distance being substantially orthogonal to one another.

30. The antenna reflector deployment mechanism of claim 29 , further comprising:

a first crossboom, the first crossboom coupled with the first positioning mechanism at a first end of the first crossboom, the first crossboom coupled with the third positioning mechanism at a second end of the first crossboom, and the first crossboom coupled with the first distal end between the first end and the second end of the first crossboom, wherein the first rigid antenna reflector and the third rigid antenna reflector are coupled with the first reflector boom via the first crossboom; and

a second crossboom, the second crossboom coupled with the second positioning mechanism at a first end of the second crossboom, the second crossboom coupled with the fourth positioning mechanism at a second end of the second crossboom, and the second crossboom coupled with the second distal end between the first end and the second end of the second crossboom, wherein the second rigid antenna reflector and the fourth rigid antenna reflector are coupled with the second reflector boom via the second crossboom.