SYSTEM AND APPARATUS FOR DRIVING ANTENNA

• US 20190157749A1
• Filed: 10/18/2018
• Published: 05/23/2019
• Est. Priority Date: 06/27/2014
• Status: Active Grant

• Current Assignee: ViaSat Incorporated
• Original Assignee: ViaSat Incorporated
• Inventors: Newkirk, Jack C., Holt, B. Wayne, Smith, Bradley H., Skinner, Kevin M., Blalock, E. Mitchell
• Granted Patent: US 10,559,875 B2
• Time in Patent Office: Days
• CPC Class Codes: B01L 2200/087 Ergonomic aspects
• CPC Class Codes: B01L 2200/143 Quality control, feedback systems
• CPC Class Codes: B01L 2300/024 Storing results with means integrated into the container
• CPC Class Codes: B01L 2300/027 Digital display, e.g. LCD, LED
• CPC Class Codes: B01L 3/021 Pipettes, i.e. with only one conduit for withdrawing and redistributing liquids
• CPC Class Codes: B01L 3/0227 Details of motor drive means B01L3/0231, B01L3/0234 take precedence
• CPC Class Codes: B01L 3/0237 Details of electronic control, e.g. relating to user interface
• CPC Class Codes: B01L 3/0286 Ergonomic aspects, e.g. form or arrangement of controls
• CPC Class Codes: F16H 21/14 by means of cranks, eccentrics, or like members fixed to one rotary member and guided along tracks on the other
• CPC Class Codes: G01N 1/14 Suction devices, e.g. pumps; Ejector devices
• CPC Class Codes: H01Q 1/125 Means for positioning
• CPC Class Codes: H01Q 1/18 Means for stabilising antennas on an unstable platform
• CPC Class Codes: H01Q 1/28 Adaptation for use in or on aircraft, missiles, satellites, or balloons
• CPC Class Codes: H01Q 1/288 Satellite antennas
• CPC Class Codes: H01Q 21/28 Combinations of substantially independent non-interacting antenna units or systems multiple beam H01Q25/00
• CPC Class Codes: H01Q 3/06 over a restricted angle
• CPC Class Codes: H01Q 3/08 for varying two co-ordinates of the orientation
• CPC Class Codes: H04B 7/18508 with satellite system used as relay, i.e. aeronautical mobile satellite service
• CPC Class Codes: H04B 7/18515 Transmission equipment in satellites or space-based relays
• CPC Class Codes: H04B 7/18519 Operations control, administration or maintenance

Abstract

A multiple-antenna positioning system with a single drive element, providing reduced weight and complexity over systems that have a drive element for each antenna. In certain examples, each antenna can be coupled with a rotating spindle, with each antenna spindle being coupled with a pair of link arms. By driving a single drive spindle, each of the antenna spindles in the system can be rotated by the associated pair of link arms. The link arms can have an adjustable length, such as through a turnbuckle mechanism, to reduce backlash in the system, and in some examples can apply a preload to the system. By reducing backlash, the multiple antenna positioning system can have improved responsiveness to a rotation of the single drive element, as well as improved stability of the positioning of each antenna when the drive element is held in a fixed position.

Claims

1. (canceled)

2. A method of communication for an antenna assembly comprising a base structure and a support structure rotatably coupled with the base structure about a first axis, the method comprising:

tracking a first satellite for communication via a first antenna that is rotatably coupled with the support structure about a second axis, the first antenna having a first boresight, wherein tracking the first satellite comprises rotating the support structure about the first axis and rotating the first antenna about the second axis using a driven angular rotation about an axis that is non-coincident with the second axis;

determining to switch from communications via the first antenna to communications via a second antenna that is rotatably coupled with the support structure about a third axis, the second antenna having a second boresight, wherein a projection of the second boresight on a plane perpendicular to the first axis is separated by an angle from a projection of the first boresight on the plane perpendicular to the first axis; and

tracking a second satellite for communications via the second antenna, wherein tracking the second satellite comprises rotating the support structure about the first axis and rotating the second antenna about the third axis using a driven angular rotation about an axis that is non-coincident with the third axis.

3. The method of claim 2, wherein determining to switch from communications via the first antenna to communications via the second antenna is based at least in part on a change of position of the antenna assembly.

4. The method of claim 2, wherein determining to switch from communications via the first antenna to communications via the second antenna is based at least in part on a network availability, a communication capacity, a communication cost, or a combination thereof.

5. The method of claim 2, wherein determining wherein determining to switch from communications via the first antenna to communications via the second antenna is based at least in part on an error condition or a fault condition.

6. The method of claim 2, wherein determining to switch from communications via the first antenna to communications via the second antenna is based at least in part on a degradation of communications via the first antenna.

7. An antenna assembly, comprising:

a base structure;

a support structure rotatably coupled with the base structure about a first axis;

a first antenna having a first boresight, the first antenna rotatably coupled with the support structure about a second axis, wherein rotation of the first antenna about the second axis is responsive to a driven angular rotation about an axis that is non-coincident with the second axis; and

a second antenna having a second boresight, the second antenna rotatably coupled with the support structure about a third axis, wherein rotation of the second antenna about the third axis is responsive to a driven angular rotation about an axis that is non-coincident with the third axis,

wherein a projection of the first boresight on a plane perpendicular to the first axis is separated by an angle from a projection of the second boresight on the plane perpendicular to the first axis.

8. The antenna assembly of claim 7, wherein the second axis and the third axis are fixed with respect to the support structure.

9. The antenna assembly of claim 7, wherein:

rotation of the support structure about the first axis provides an azimuth adjustment to the first boresight and the second boresight.

10. The antenna assembly of claim 7, wherein the first antenna is configured to operate over a first frequency band, and the second antenna is configured to operate over a second frequency band that is different from the first frequency band.

11. The antenna assembly of claim 7, wherein the first axis is perpendicular to the second axis and the first axis is perpendicular to the third axis.

12. The antenna assembly of claim 7, wherein the second axis and the third axis are parallel.

13. The antenna assembly of claim 7, wherein:

rotation of the first antenna about the second axis provides an elevation adjustment to the first boresight; and

rotation of the second antenna about the third axis provides an elevation adjustment to the second boresight.

14. The antenna assembly of claim 7, wherein the second axis and the third axis are non-coincident.

15. The antenna assembly of claim 7, wherein the second axis and the third axis are not parallel.

16. The antenna assembly of claim 7, wherein the projection of the first boresight on the plane perpendicular to the first axis and the projection of the second boresight on the plane perpendicular to the first axis are separated by a fixed angle.

17. The antenna assembly of claim 7, wherein the projection of the first boresight on the plane perpendicular to the first axis and the projection of the second boresight on the plane perpendicular to the first axis are separated by 180 degrees.

18. The antenna assembly of claim 7, further comprising:

an antenna control unit operable to cause the antenna assembly to;

track a first satellite for communications via the first antenna; and

track a second satellite for communications via the second antenna.

19. The antenna assembly of claim 18, wherein the antenna control unit is operable to determine to switch between communications via the first antenna and communications via the second antenna.

20. The antenna assembly of claim 18, wherein the antenna control unit is operable to determine to switch between communications via the first antenna and communications via the second antenna based at least in part on a change of position of the antenna assembly.

21. The antenna assembly of claim 18, wherein the antenna control unit is operable to determine to switch between communications via the first antenna and communications via the second antenna based at least in part on a network availability, a communication capacity, or a communication cost, or a combination thereof.

22. The antenna assembly of claim 18, wherein the antenna control unit is operable to determine to switch between communications via the first antenna and communications via the second antenna based at least in part on an error condition or a fault condition.

23. The antenna assembly of claim 18, wherein the antenna control unit is operable to determine to switch between communications via the first antenna and communications via the second antenna based at least in part on a degradation of communications via the first antenna.