System and apparatus for driving antenna

• US 10,135,127 B2
• Filed: 04/28/2017
• Issued: 11/20/2018
• 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
• Primary Examiner(s): Nguyen, Hai V
• Application Number:
  US15/582,398
• Publication Number:
  US 20170237155A1
• Time in Patent Office: 571 Days
• Field of Search: 455 9
• 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. An antenna assembly, comprising:

a first antenna rotatably coupled with a support structure about a first axis, the first antenna having a first boresight;

a second antenna rotatably coupled with the support structure about a second axis, the second antenna having a second boresight that is not parallel with the first boresight; and

a drive element coupled with the first antenna and the second antenna and operable to simultaneously rotate the first antenna about the first axis and rotate the second antenna about the second axis.

2. The antenna assembly of claim 1, wherein the drive element is coupled with the first antenna by a first linkage and the drive element is coupled with the second antenna by a second linkage.

3. The antenna assembly of claim 1, wherein the coupling between the drive element and the first antenna is operable to change a degree of backlash between the drive element and the first antenna, or the coupling between the drive element and the second antenna is operable to change a degree of backlash between the drive element and the second antenna, or both.

4. The antenna assembly of claim 1, wherein the coupling between the drive element and the first antenna is operable to change a degree of preload between the drive element and the first antenna, or the coupling between the drive element and the second antenna is operable to change a degree of preload between the drive element and the second antenna, or both.

5. The antenna assembly of claim 1, wherein the first axis and the second axis are parallel.

6. The antenna assembly of claim 1, wherein the first axis and the second axis are not parallel.

7. The antenna assembly of claim 1, wherein the first axis and the second axis are both associated with a positioning degree of freedom, and simultaneously rotating the first antenna to cause a positive change with respect to the positioning degree of freedom causes a negative change with respect to the positioning degree of freedom for the second antenna.

8. The antenna assembly of claim 1, wherein the first axis and the second axis are both associated with a positioning degree of freedom, and simultaneously rotating the first antenna and the second antenna causes a positive change with respect to the positioning degree of freedom for both the first antenna and the second antenna, or causes a negative change with respect to the positioning degree of freedom for both the first antenna and the second antenna.

9. The antenna assembly of claim 1, 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.

10. The antenna assembly of claim 1, further comprising:

a base element rotatably coupled with the support structure about a third axis that is not parallel to the first axis and not parallel to the second axis; and

a second drive element to rotate the support structure about the base element.

11. The antenna assembly of claim 1, further comprising:

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

track a first satellite with the drive element for communications via the first antenna; and

track a second satellite with the drive element for communications via the second antenna.

12. The antenna assembly of claim 11, wherein the antenna control unit is operable to determine to switch between communications via the first antenna and communications via the second antenna.

13. The antenna assembly of claim 12, 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.

14. The antenna assembly of claim 12, 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.

15. The antenna assembly of claim 12, 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.

16. The antenna assembly of claim 12, 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.

17. The antenna assembly of claim 11, wherein the first satellite and the second satellite are different satellites.

18. The antenna assembly of claim 11, wherein the first satellite and the second satellite are the same satellite.

19. A method of communication, comprising:

providing an antenna assembly having a first antenna rotatably coupled with a support structure about a first axis, a second antenna rotatably coupled with the support structure about a second axis, and a drive element coupled with the first antenna and the second antenna and operable to simultaneously rotate the first antenna about the first axis and rotate the second antenna about the second axis, wherein a boresight of the first antenna is non-parallel with a boresight of the second antenna;

tracking a first satellite with the drive element for communications via the first antenna;

determining to switch from communications via the first antenna to communications via the second antenna; and

tracking a second satellite with the drive element for communications via the second antenna.

20. The method of claim 19, 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.

21. The method of claim 19, 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.

22. The method of claim 19, 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.

23. The method of claim 19, 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.

24. The method of claim 19, wherein the first satellite and the second satellite are the same satellite.

25. The method of claim 19, wherein the first satellite and the second satellite are different satellites.