Very high frequency line of sight winglet antenna

• US 7,737,898 B2
• Filed: 03/01/2007
• Issued: 06/15/2010
• Est. Priority Date: 03/01/2007
• Status: Expired due to Fees

• Current Assignee: L-3 Communications Integrated Systems LP (L3Harris Technologies, Inc.)
• Original Assignee: L-3 Communications Integrated Systems LP (L3Harris Technologies, Inc.)
• Inventors: Tignor, Claude W. III, May, Vincent A., Redus, Wesley D., Stuart, SueAnn, Hanusa, John H., Hein, Paul W.
• Primary Examiner(s): Mansen; Michael R
• Assistant Examiner(s): O'Hara; Brian M
• Application Number:
  US11/712,694
• Publication Number:
  US 20080210822A1
• Time in Patent Office: 1,202 Days
• Field of Search: 343/705, 343/708, 343/767
• US Class Current: 343/708
• CPC Class Codes: H01Q 1/287 integrated in a wing or a stabiliser

Abstract

A line of sight antenna supported in an upturned terminal winglet or similar vertical member of an aircraft is disclosed. An aperture is formed in the conductive winglet or vertical member, and the antenna is supported within the aperture by a support mechanism such that the antenna is exposed to the line of sight transmissions. A non-conductive covering may also be used for the aperture. Using the cover, the antenna within the winglet can be configured so that it does not alter the appearance or aerodynamic characteristics of the aircraft. Alternatively, the antenna can be coupled to the outside of the winglet or vertical member if cosmetics are not a concern. The frequency range of the antenna can be tuned to cover desired frequency ranges. The antenna position at the winglet maintains a large physical separation from fuselage-mounted antennas thereby reducing interference.

Claims

1. A line of sight antenna supported in a vertical portion of an aircraft, comprising:

an aperture in an upturned terminal winglet of an aircraft wing or similar vertical member of an aircraft, the winglet or member being conductive;

a supporting mechanism configured to support an antenna in the aperture;

an antenna supported by the supporting mechanism and configured to remain exposed to line of sight transmissions, the antenna comprising;

a shunt radiating element formed to fit within the aperture, the shunt radiating element comprising a sheet of conductive material configured to have a curved leading edge and a trailing edge including a pair of flat surfaces; and

a ground strap having a first end affixed to a first end of the shunt radiating element and a second end affixed to an aircraft structure, the ground strap being configured to provide an electrical grounding path from the shunt radiating element to the aircraft structure;

a coaxial connector having a ground and a feed-line, the feed-line for the coaxial connector being configured to electrically connect a second end of the shunt radiating element to an aircraft system, and the ground for the coaxial connector being electrically connected to the aircraft structure; and

a non-conductive covering for the aperture.

2. The antenna of claim 1, wherein the antenna is mounted by physically embedding it within the aperture in a leading edge of the winglet or vertical member.

3. The antenna of claim 2, wherein the leading edge is substantially unaltered cosmetically by the mounting of the antenna within the terminal winglet or vertical member.

4. The antenna of claim 2, wherein the aircraft wing is substantially unaltered aerodynamically by the mounting of the antenna within the terminal winglet or vertical member.

5. The antenna of claim 2, wherein the aperture is cut away for vertical length corresponding to a desired frequency range of reception for the antenna.

6. The antenna of claim 5, further comprising a non-conductive dielectric radome configured to create a cavity in the conductive terminal winglet or vertical member.

7. The antenna of claim 1, wherein the aperture is configured to have a length along an edge of the terminal winglet or vertical member that is greater than a depth into the edge of the terminal winglet or vertical member.

8. The antenna of claim 1, wherein the shunt radiating element is supported at a fixed separation from a floor of the aperture by non-conductive dielectric brackets.

9. The antenna of claim 8, wherein the coaxial connector is affixed to a floor of the aperture by a bracket at a bottom end of the shunt radiating element.

10. The antenna of claim 1, wherein frequency range of the antenna is configured to cover a frequency range within from about 30 MHz to about 3000 MHz.

11. The antenna of claim 10, wherein the frequency range of the antenna covers a frequency range from about 118 MHz to about 152 MHz.

12. The antenna of claim 1, wherein the antenna is mounted to an outside surface of the winglet or vertical member.

13. An aircraft having a wing antenna, comprising:

an aperture in a conductive upturned terminal winglet or vertical member of an aircraft;

a supporting mechanism for an antenna configured within the aperture;

a line of sight antenna supported within the upturned terminal winglet or vertical member by the supporting mechanism, the antenna configured to remain exposed to line of sight transmissions, the antenna comprising;

a shunt radiating element formed to fit within the aperture, the shunt radiating element comprising a sheet of conductive material configured to have a curved leading edge and a trailing edge including a pair of flat surfaces; and

a ground strap having a first end affixed to a first end of the shunt radiating element and a second end affixed to an aircraft structure, the ground strap being configured to provide an electrical grounding path from the shunt radiating element to the aircraft structure;

a coaxial connector having a ground and a feed-line, the feed-line for the coaxial cable being configured to electrically connect the a second end of the shunt radiating element to an aircraft system, and the ground for the coaxial connector being electrically connected to the aircraft structure; and

a non-conductive covering for the aperture.

14. The aircraft of claim 13, wherein the antenna is mounted by physically embedding it within an aperture in a leading edge of the terminal winglet or vertical member.

15. The antenna of claim 14, wherein the aircraft wing is substantially unaltered cosmetically by the mounting of the antenna within the terminal winglet or vertical member.

16. The antenna of claim 14, wherein the aircraft wing is substantially unaltered aerodynamically by the mounting of the antenna within the terminal winglet or vertical member.

17. The aircraft wing of claim 16, wherein the frequency range of the antenna covers a frequency range from about 118 MHz to about 152 MHz.

18. The aircraft wing of claim 13, wherein the antenna is mounted to an outside surface of the winglet or vertical member.

19. A method of receiving line of sight signals with an aircraft wing antenna, comprising:

providing a shunt radiating element for an antenna formed to fit within an aperture, the shunt radiating element comprising a sheet of conductive material configured to have a curved leading edge and a trailing edge including a pair of flat surfaces;

supporting the shunt radiating element within an aperture of an upturned terminal winglet or vertical member of an aircraft, the terminal winglet or vertical member being conductive;

connecting a ground strap between a first end of the shunt radiating element and an aircraft structure, the ground strap being configured to provide an electrical grounding path from the shunt radiating element to the aircraft structure;

connecting a feed-line for a coaxial connector to a second end of the shunt radiating element;

receiving line of sight transmissions with the antenna through a non-conductive covering; and

coupling signals received by the antenna to an aircraft system using the feed-line for the coaxial connector, the coaxial connector further having a ground electrically connected to the aircraft structure.

20. The method of claim 19, further comprising mounting the antenna by physically embedding it within an aperture in a leading edge of the terminal winglet or vertical member.

21. The method of claim 19, wherein frequency range of the antenna can be adapted to cover frequency ranges within from about 30 MHz to about 3000 MHz.

22. The method of claim 19, wherein frequency range of the antenna covers a very high frequency (VHF) radio spectrum from 118 to 152 MHz.

23. The method of claim 19, further comprising mounting the antenna to an outside surface of the winglet or vertical member.