Spacecraft with rigid antenna reflector deployed via linear extension boom
View Patent ↗A spacecraft with a linear extension boom, an antenna feed, and a rigid antenna reflector is provided. The rigid antenna reflector may be connected with one end of the linear extension boom, and the other end of the linear extension boom may be connected with the spacecraft main body. In a launch configuration of the spacecraft, the linear extension boom may be retracted into a stowed configuration, and in an on-orbit configuration of the spacecraft, the linear extension boom may be extended into a deployed configuration, thereby moving the rigid antenna reflector away from the yaw axis of the spacecraft and positioning the rigid antenna reflector such that the focal point of the rigid antenna reflector may be oriented to align on, and be collocated with, the antenna feed. The rigid antenna reflector may be connected with the linear extension boom by a positioning mechanism that provides for adjustment in the angular orientation of the rigid antenna reflector relative to the linear extension boom.
1. A spacecraft, the spacecraft comprising:
a main body;
a first antenna feed;
a second antenna feed;
a first rigid antenna reflector;
a second rigid antenna reflector;
a first linear extension boom; and
a second linear extension boom, wherein:
the first linear extension boom has a proximal end and a distal end,
the second linear extension boom has a proximal end and a distal end,
the first linear extension boom is configured to cause, when actuated, the distal end of the first linear extension boom to translate along a first linear axis with respect to the proximal end of the first linear extension boom,
the second linear extension boom is configured to cause, when actuated, the distal end of the second linear extension boom to translate along a second linear axis with respect to the proximal end of the second linear extension boom,
the first rigid antenna reflector is coupled with the first distal end of the first linear extension boom,
the second rigid antenna reflector is coupled with the distal end of the second linear extension boom,
the proximal ends of the first linear extension boom and the second linear extension boom are both coupled with the main body,
the first linear extension boom and the first rigid antenna reflector are configured such that the first rigid antenna reflector and the first linear extension boom are transitionable from a first stowed configuration to a first deployed configuration,
the second linear extension boom and the second rigid antenna reflector are configured such that the second rigid antenna reflector and the second linear extension boom are transitionable from a second stowed configuration to a second deployed configuration,
the first linear extension boom has a first length in the first stowed configuration and a second length in the first deployed configuration,
the second linear extension boom has a third length in the second stowed configuration and a fourth length in the second deployed configuration,
the first rigid antenna reflector is positioned a first distance from the main body in the first stowed configuration and a second distance from the main body in the first deployed configuration,
the second rigid antenna reflector is positioned a third distance from the main body in the second stowed configuration and a fourth distance from the main body in the second deployed configuration,
the first length and the first distance are each respectively less than the second length and the second distance,
the third length and the third distance are each respectively less than the fourth length and the fourth distance,
the first rigid antenna reflector illuminates the first antenna feed when in the first deployed configuration, and
the second rigid antenna reflector illuminates the second antenna feed when in the second deployed configuration.
2. The spacecraft of claim 1 , wherein the first rigid antenna reflector moves relative to the first antenna feed when the first linear extension boom is actuated.
3. The spacecraft of claim 1 , wherein the proximal end of the first linear extension boom is coupled with the main body by way of a rotational joint that is configured to allow the first linear extension boom to be rotated about a pivot axis relative to the main body.
4. The spacecraft of claim 1 , wherein the first linear extension boom is a storable tubular extendible mast (STEM).
5. The spacecraft of claim 4 , wherein the STEM comprises:
a tube having a long axis parallel to the first linear axis;
a winding spool configured to rotate about a winding axis perpendicular to the first linear axis;
a drive motor configured to rotate the winding spool;
one or more guides configured to engage with an outer surface of the tube; and
a support structure that supports the winding spool and the one or more guides in a spaced-apart manner, wherein:
the tube passes through the one or more guides,
a first end of the tube is flattened and a circumferential edge of the first end of the tube is coupled with the winding spool and is parallel to the winding axis, and
the one or more guides, the tube, and the winding spool are arranged such that when the winding spool is rotated in a first direction, the tube flattens out as it is drawn onto the winding spool and the distance between the winding spool and a second end of the tube opposite the first end decreases, and when the winding spool is rotated in a second direction opposite the first direction, the tube returns into a tubular shape as the tube unwinds from the winding spool and the distance between the winding spool and the second end increases.
6. The spacecraft of claim 5 , wherein the tube has a slit along the long axis.
7. The spacecraft of claim 1 , further comprising a positioning mechanism, wherein:
the first rigid antenna reflector is coupled with the distal end of the first linear extension boom via the positioning mechanism, and
the positioning mechanism is configured to adjust an angular orientation of the first rigid antenna reflector with respect to the first linear extension boom.
8. The spacecraft of claim 7 , wherein the positioning mechanism is a dual-axis positioning mechanism configured to adjust the angular orientation of the first rigid antenna reflector about two different rotational axes with respect to the first linear extension boom.
9. The spacecraft of claim 1 , wherein:
the spacecraft has a yaw axis that is oriented earthward when the spacecraft is on-orbit, and
the first linear extension boom is coupled with the main body such that the first linear axis forms an oblique angle with respect to the yaw axis.
10. The spacecraft of claim 9 , wherein the oblique angle is between 20 and 45 degrees.
11. The spacecraft of claim 1 , wherein:
the spacecraft is configured to be mounted in a launch vehicle for delivery to orbit;
the main body has a forward surface that is oriented away from an aft end of the launch vehicle when the spacecraft is mounted in the launch vehicle;
the spacecraft is reconfigurable between a launch configuration, in which the first rigid antenna reflector and the first linear extension boom are in the first stowed configuration, and an on-orbit configuration, in which the first rigid antenna reflector and the first linear extension boom are in the first deployed configuration;
the first rigid antenna reflector is stowed forward of the forward surface of the main body when the spacecraft is in the launch configuration; and
the first rigid antenna reflector is located further forward of the forward surface when the spacecraft is in the on-orbit configuration than when the spacecraft is in the launch configuration.
12. The spacecraft of claim 11 , wherein the spacecraft is configured such that the forward surface is oriented in an anti-Earth direction when the spacecraft is on-orbit.
13. The spacecraft of claim 1 , wherein:
the spacecraft is configured to be mounted in a launch vehicle for delivery to orbit;
the main body has a forward surface that is oriented away from an aft end of the launch vehicle when the spacecraft is mounted in the launch vehicle and an aft surface that is oriented towards the aft end of the launch vehicle when the spacecraft is mounted in the launch vehicle;
the spacecraft is reconfigurable between a launch configuration, in which the first rigid antenna reflector and the first linear extension boom are in the first stowed configuration, and an on-orbit configuration, in which the first rigid antenna reflector and the first linear extension boom are in the first deployed configuration;
the first rigid antenna reflector is stowed adjacent to a side of the main body of the spacecraft spanning between the forward surface of the main body and the aft surface of the main body when the spacecraft is in the launch configuration; and
the first rigid antenna reflector is positioned further aft of the forward surface when the spacecraft is in the on-orbit configuration than when the spacecraft is in the launch configuration.
14. The spacecraft of claim 13 , wherein the spacecraft is configured such that the forward surface is oriented earthward when the spacecraft is on-orbit.
15. The spacecraft of claim 1 , further comprising a third antenna feed, wherein:
the first linear extension boom and the first rigid antenna reflector are further configured such that the first rigid antenna reflector and the first linear extension boom are transitionable to a secondary first deployed configuration,
the first linear extension boom has a secondary second length in the secondary first deployed configuration,
the first rigid antenna reflector is positioned a secondary second distance from the main body in the secondary first deployed configuration,
the first length and the first distance are each respectively less than the secondary second length and the secondary second distance, and
the first rigid antenna reflector illuminates the third antenna feed when in the secondary first deployed configuration.
16. The spacecraft of claim 1 , wherein the first antenna feed and the second antenna feed are located on opposite sides of the main body.
17. A spacecraft, the spacecraft comprising:
a main body;
a first antenna feed;
a second antenna feed;
a first rigid antenna reflector; and
a first linear extension boom, wherein:
the first linear extension boom has a proximal end and a distal end,
the first linear extension boom is configured to cause, when actuated, the distal end to translate along a first linear axis with respect to the proximal end,
the first rigid antenna reflector is coupled with the distal end of the first linear extension boom,
the proximal end of the first linear extension boom is coupled with the main body,
the first linear extension boom and the first rigid antenna reflector are configured such that the first rigid antenna reflector and the first linear extension boom are transitionable between a first stowed configuration, a first deployed configuration, and a secondary first deployed configuration,
the first linear extension boom has a first length in the first stowed configuration, a second length in the first deployed configuration, and a secondary second length in the secondary first deployed configuration,
the first rigid antenna reflector is positioned a first distance from the main body in the first stowed configuration, a second distance from the main body in the first deployed configuration, and a secondary second distance in the secondary first deployed configuration,
the first length and the first distance are each respectively less than the second length and the second distance,
the first length and the first distance are each respectively less than the secondary second length and the secondary second distance,
the first rigid antenna reflector illuminates the first antenna feed when in the first deployed configuration, and
the first rigid antenna reflector illuminates the second antenna feed when in the secondary first deployed configuration.
18. The spacecraft of claim 17 , wherein the proximal end of the first linear extension boom is coupled with the main body by way of a rotational joint that is configured to allow the first linear extension boom to be rotated about a pivot axis relative to the main body.
19. The spacecraft of claim 17 , wherein the first linear extension boom is a storable tubular extendible mast (STEM) that comprises:
a tube having a long axis parallel to the first linear axis;
a winding spool configured to rotate about a winding axis perpendicular to the first linear axis;
a drive motor configured to rotate the winding spool;
one or more guides configured to engage with an outer surface of the tube; and
a support structure that supports the winding spool and the one or more guides in a spaced-apart manner, wherein:
the tube passes through the one or more guides,
a first end of the tube is flattened and a circumferential edge of the first end of the tube is coupled with the winding spool and is parallel to the winding axis, and
the one or more guides, the tube, and the winding spool are arranged such that when the winding spool is rotated in a first direction, the tube flattens out as it is drawn onto the winding spool and the distance between the winding spool and a second end of the tube opposite the first end decreases, and when the winding spool is rotated in a second direction opposite the first direction, the tube returns into a tubular shape as the tube unwinds from the winding spool and the distance between the winding spool and the second end increases.
20. The spacecraft of claim 17 , further comprising a positioning mechanism, wherein:
the first rigid antenna reflector is coupled with the distal end of the first linear extension boom via the positioning mechanism, and
the positioning mechanism is configured to adjust an angular orientation of the first rigid antenna reflector with respect to the first linear extension boom.