Conformal load-bearing antenna system that excites aircraft structure

• US 6,097,343 A
• Filed: 10/23/1998
• Issued: 08/01/2000
• Est. Priority Date: 10/23/1998
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: TRW Inc. (Northrop Grumman Corporation)
• Inventors: Goetz, Allan C., Chea, Haigan K.
• Primary Examiner(s): Wimer, Michael C.
• Application Number:
  US09/178,356
• Time in Patent Office: 648 Days
• Field of Search: 343/708, 343/705, 343/767
• US Class Current: 343/708
• CPC Class Codes: H01Q 1/286 substantially flush mounted with the skin of the craft
• CPC Class Codes: H01Q 13/085 Slot-line radiating ends
• CPC Class Codes: H01Q 13/10 Resonant slot antennas

Abstract

An antenna system structurally integrated into a load-bearing structural member of an aircraft, such as a wing (30), horizontal tail section (36), or vertical tail fin (20) in such a way as to cause practically no added aerodynamic drag and to add minimal weight to the aircraft. The antenna system includes a flared notch (22, 32, 34 or 38) of non-conductive material and an antenna feed (12) that excites conductive portions of the structural member on opposite sides of the notch at a selected feed point (40). The conductive portions of the structural member and other conductive portions of the entire aircraft are excited by signals applied to the antenna feed. As a result, the antenna performance provides high gain omnidirectionally, and supports both vertically and horizontally polarized communication functions over a wide range of VHF and UHF bands.

Claims

1. An aircraft antenna system structurally integrated into a load-bearing structural member of an aircraft, the antenna comprising:

an antenna notch formed from non-conductive material and positioned between two adjacent conductive regions of an aircraft structural load-bearing member, wherein the notch and the two adjacent conductive regions are structurally integrated to perform mechanical functions of the load-bearing member, and wherein the notch extends from a narrow region to a flared wider region; and

an antenna feed terminating at a feed point located in the narrow region of the notch, to couple transmitted energy into the notch and to couple received energy out of the notch;

and wherein the adjacent conductive regions and other conductive regions of the entire aircraft structure function as a radiating and receiving component of the antenna system, which provides an omnidirectional radiation pattern supporting vertically and horizontally polarized communication functions.

2. An aircraft antenna system as defined in claim 1, wherein:

the load-bearing structural member into which the antenna is integrated is a vertical tail fin, and the antenna notch extends from a narrow region at a leading edge of the tail fin to a wider region located higher on the leading edge.

3. An aircraft antenna system structurally integrated into a load-bearing structural member of an aircraft, the antenna comprising:

an antenna notch formed from non-conductive material and positioned between two adjacent conductive regions of an aircraft structural load-bearing member, wherein the notch and the two adjacent conductive regions are structurally integrated to perform mechanical functions of the load-bearing member, and wherein the notch extends from a narrow region to a flared wider region; and

an antenna feed terminating at a feed point located in the narrow region of the notch, to couple transmitted energy into the notch and to couple received energy out of the notch;

and wherein the adjacent conductive regions and other conductive regions of the entire aircraft structure function as a radiating and receiving component of the antenna system, which provides an omnidirectional radiation pattern supporting vertically and horizontally polarized communication functions;

and wherein the load-bearing structural member into which the antenna is integrated is a wing section, and the antenna notch extends from a narrow region at an edge of the wing section to a wider region located on the same edge.

4. An aircraft antenna system as defined in claim 3, wherein:

the antenna is located near the leading edge of the wing section.

5. An aircraft antenna system as defined in claim 3, wherein:

the antenna is located near the trailing edge of the wing section.

6. An aircraft antenna system structurally integrated into a load-bearing structural member of an aircraft, the antenna comprising:

an antenna notch formed from non-conductive material and positioned between two adjacent conductive regions of an aircraft structural load-bearing member, wherein the notch and the two adjacent conductive regions are structurally integrated to perform mechanical functions of the load-bearing member, and wherein the notch extends from a narrow region to a flared wider region; and

an antenna feed terminating at a feed point located in the narrow region of the notch, to couple transmitted energy into the notch and to couple received energy out of the notch;

and wherein the adjacent conductive regions and other conductive regions of the entire aircraft structure function as a radiating and receiving component of the antenna system, which provides an omnidirectional radiation pattern supporting vertically and horizontally polarized communication functions;

and wherein the load-bearing structural member into which the antenna is integrated is a horizontal tail section, and the antenna notch extends from a narrow region at a leading edge of the horizontal tail section to a wider region located on the same edge.