Active array antenna with flexible membrane elements and tensioning arrangement

• US 6,515,636 B2
• Filed: 04/12/2001
• Issued: 02/04/2003
• Est. Priority Date: 04/12/2001
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Murray, Bronson, Berard, Clement Alphonse Jr., Munder, Joseph Charles
• Primary Examiner(s): Wimer, Michael C.
• Application Number:
  US09/833,549
• Publication Number:
  US 20020149540A1
• Time in Patent Office: 663 Days
• Field of Search: H01/Q.100, H01/Q.120, 343/DIG.2, 343/878, 343/881, 343/853, 343/708, 343/915, 343/916, 244/158.R
• US Class Current: 343/878
• CPC Class Codes: H01Q 1/08 Means for collapsing antennas or parts thereof collapsible loop antennas H01Q7/02; means for collapsing H-antennas or Yagi antennas H01Q19/04
• CPC Class Codes: H01Q 1/12 Supports; Mounting means
• CPC Class Codes: H01Q 1/20 Resilient mountings
• CPC Class Codes: H01Q 1/288 Satellite antennas
• CPC Class Codes: H01Q 21/061 Two dimensional planar arrays
• CPC Class Codes: Y10S 343/02 Satellite-mounted antenna

Abstract

An array antenna including: a frame having a two-dimensional array of a plurality of openings; an electromagnetically radiating tile disposed in each opening; and mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame. Preferably, each biasing member is a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile. Furthermore, it is preferred that each biasing member further have a way to vary the biasing force with temperature, such as fabricating the bow portion from a first and second material, each having a different coefficient of thermal expansion. Also provided is a spacecraft which utilizes the array antenna of the present invention.

Claims

1. An array antenna comprising:

a frame having a two-dimensional array of a plurality of openings;

an electromagnetically radiating tile disposed in each opening; and

mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame.

2. The antenna according to claim 1, wherein the frame lies essentially in a plane, and the plane of each tile is parallel to the plane of the frame.

3. The antenna according to claim 1, wherein each biasing member comprises a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile.

4. The antenna according to claim 3, wherein the biasing member further comprises a C-shaped clip portion, the C-shaped clip portion being disposed over an edge of the tile and retaining the bowed section therebetween.

5. The antenna according to claim 3, wherein the first and second ends form an axis perpendicular to the plane of a corresponding tile.

6. The antenna according to claim 1, wherein the at least two biasing members comprises four biasing members, each of the four biasing members being disposed at a corresponding corner of the tile.

7. The antenna according to claim 1, wherein the tile is flexible and the biasing members maintain the tile in tension.

8. The antenna according to claim 1, wherein the tile transmits and/or receives electromagnetic radiation.

9. The antenna according to claim 6, wherein each of the four biasing members are fastened to the tile at an extension protruding from each of the comers of the tile.

10. The antenna according to claim 1, wherein each biasing member further comprises means for varying the biasing force in response to a change in temperature.

11. The antenna according to claim 10, wherein each biasing member comprises a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile and wherein the means for varying the biasing force in response to a change in temperature comprises the bow portion being fabricated from a first and second material, each said material having a different coefficient of thermal expansion.

12. The antenna according to claim 11, wherein the first and second materials are selected from a group consisting of metals and composites.

13. The antenna according to claim 10, wherein the mounting means comprises a radial tensioning wire fixed to each of four corresponding corners of the tile at a first end and slipably disposed to a tensioning yoke at a second end for maintaining the radial wires and tile in tension, the means for varying the biasing force in response to a change in temperature comprising the tensioning yoke having a portion thereof of temperature compensating material which changes in length with changes in temperature.

14. The antenna according to claim 1, wherein each of the plurality of openings are rectangular and the radiating tiles are rectangular to fit therein.

15. The antenna according to claim 1, wherein the mounting means comprises a radial tensioning wire fixed to each of four corresponding comers of the tile at a first end and slipably disposed to a tensioning yoke at a second end, the tensioning yoke having a tensioning member for maintaining the radial wires and tile in tension.

16. In a spacecraft including a plurality of array antennas, each of the array antennas comprising:

a frame having a two-dimensional array of a plurality of openings;

an electromagnetically radiating tile disposed in each opening; and

mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame.

17. The spacecraft according to claim 16, wherein the frame lies essentially in a plane, and the plane of each tile is parallel to the plane of the frame.

18. The spacecraft according to claim 16, wherein each biasing member comprises a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile.

19. The spacecraft according to claim 18, wherein the biasing member further comprises a C-shaped clip portion, the C-shaped clip portion being disposed over an edge of the tile and retaining the bowed section therebetween.

20. The spacecraft according to claim 18, wherein the first and second ends form an axis perpendicular to the plane of a corresponding tile.

21. The spacecraft according to claim 16, wherein the at least two biasing members comprises four biasing members, each of the four biasing members being disposed at a corresponding corner of the tile.

22. The spacecraft according to claim 16, wherein the tile is flexible and the biasing members maintain the tile in tension.

23. The spacecraft according to claim 16, wherein the tile transmits and/or receives electromagnetic radiation.

24. The spacecraft according to claim 21, wherein each of the four biasing members are fastened to the tile at an extension protruding from each of the comers of the tile.

25. The spacecraft according to claim 16, wherein each biasing member further comprises means for varying the biasing force in response to a change in temperature.

26. The spacecraft according to claim 25, wherein each biasing member comprises a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile and wherein the means for varying the biasing force in response to a change in temperature comprises the bow portion being fabricated from a first and second material, each said material having a different coefficient of thermal expansion.

27. The spacecraft according to claim 26, wherein the first and second materials are selected from a group consisting of metals and composites.

28. The spacecraft according to claim 25, wherein the mounting means comprises a radial tensioning wire fixed to each of four corresponding corners of the tile at a first end and slipably disposed to a tensioning yoke at a second end for maintaining the radial wires and tile in tension, the means for varying the biasing force in response to a change in temperature comprising the tensioning yoke having a portion thereof of temperature compensating material which changes in length with changes in temperature.

29. The spacecraft according to claim 16, wherein each of the plurality of openings are rectangular and the radiating tiles are rectangular to fit therein.

30. The spacecraft according to claim 16, wherein the mounting means comprises a radial tensioning wire fixed to each of four corresponding corners of the tile at a first end and slipably disposed to a tensioning yoke at a second end, the tensioning yoke having a tensioning member for maintaining the radial wires and tile in tension.

31. An array antenna comprising:

a frame having a two-dimensional array of a plurality of openings;

a flexible electromagnetically radiating tile disposed in each opening; and

mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame to maintain the tile in tension.

32. In a spacecraft including a plurality of array antennas, each of the array antennas comprising:

a frame having a two-dimensional array of a plurality of openings;

a flexible electromagnetically radiating tile disposed in each opening; and

mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame to maintain the tile in tension.

33. An array antenna comprising:

a frame having a two-dimensional array of a plurality of openings;

an electromagnetically radiating tile disposed in each opening; and

mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame, each biasing member further having means for varying the biasing force in response to a change in temperature.

34. In a spacecraft including a plurality of array antennas, each of the array antennas comprising:

a frame having a two-dimensional array of a plurality of openings;

an electromagnetically radiating tile disposed in each opening; and

mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame, each biasing member further having means for varying the biasing force in response to a change in temperature.