Steerable disk antenna

• US 5,986,611 A
• Filed: 07/10/1998
• Issued: 11/16/1999
• Est. Priority Date: 07/10/1998
• Status: Expired due to Fees

• Current Assignee: Northrop Grumman Corporation
• Original Assignee: Northrop Grumman Corporation
• Inventors: Waterman, Timothy G., Harrison, Earnest R.
• Primary Examiner(s): Le, Hoanganh
• Assistant Examiner(s): Ho, Tan
• Application Number:
  US09/112,426
• Time in Patent Office: 494 Days
• Field of Search: 343/705, 343/708, 343/793, 343/810, 343/811, 343/812, 343/853, 343/872
• US Class Current: 343/705
• CPC Class Codes: H01Q 1/28 Adaptation for use in or on aircraft, missiles, satellites, or balloons
• CPC Class Codes: H01Q 1/42 Housings not intimately mechanically associated with radiating elements, e.g. radome
• CPC Class Codes: H01Q 21/062 using dipole aerials; H01Q21/067, H01Q21/068 take precedence
• CPC Class Codes: H01Q 3/2676 Optically controlled phased array

Abstract

A radar antenna system, adapted to be supported on an aircraft for surveillance, employs a nonconducting disk radome structured with aerodynamic fairing and otherwise to produce relatively low aerodynamic drag. A plurality of struts are used to secure the disk radome to the aircraft with the disk radome generally extending in a solid horizontal reference plane. A plurality of elongated, relatively low gain radiating elements are supported by a ground-plane box within the disk radome, with the radiating elements distributed across the disk radome and disposed to radiate generally in the vertical direction. An electronic system is supported within the ground-plane box, and it includes respective transmit/receive circuits which send and receive radio frequency signals to and from the radiating elements. Power cables extend through the struts to couple signals between the electronic system in the disk radome and radar system level circuitry located externally of the disk radome.

Claims

1. A radar antenna system adapted to be supported on an aircraft for surveillance, the antenna system comprising:

a nonconducting disk radome structured with aerodynamic fairing and otherwise to produce relatively low aerodynamic drag;

a support system for securing the disk radome to the aircraft with the disk radome generally extending in a solid horizontal reference plane;

a ground plane structure supported by the disk radome and extending generally horizontally across and within the disk radome;

a plurality of elongated, relatively low gain linear radiating elements distributed in spaced relation to each other as opposing pairs within and across the disk radome and supported relative to the disk radome by the ground plane structure to extend substantially in a vertical direction with respective poles of each radiating element disposed on opposite sides of the ground plane structure so at to radiate in a generally vertical direction;

an electronic system having transmit/receive circuits disposed within and supported relative to the disk radome and respectively connected to the radiating elements to transmit radio frequency signals therebetween; and

a system for coupling, through the support system, signals between the electronic system in the disk radome and radar system level circuitry located externally of the disk radome.

2. The antenna system of claim 1 wherein each of the elongated linear radiating elements comprises a dipole radiating element.

3. The antenna system of claim 2 wherein each dipole element of said plurality of dipole radiating elements, and an associated transmit/receive circuit are structured as a modular unit thereby facilitating antenna maintenance.

4. The antenna system of claim 1 wherein the ground plane structure is box-like in form and has sufficient internal space to house and operatively support the electronic system.

5. The antenna system of claim 1, wherein a power cable system is connected to the electronic system and extends through the support system to receive energy from a power supply located externally of the disk radome.

6. The antenna system of claim 5 wherein the support system includes at least one support member, and the cable system includes a plurality of cables.

7. The antenna system of claim 6 wherein the support system includes a plurality of support members spaced from each other and extending downwardly from the disk radome for securance to the aircraft.

8. The antenna system of claim 1 wherein a power cable system is connected to the electronic system and extends through the support system to receive power energy from a power supply located externally of the radome.

9. A radar antenna system adapted to be supported on an aircraft for surveillance, the antenna system comprising:

nonconducting disk radome means structured so as to produce relatively low aerodynamic drag;

means for securing the disk radome means to the aircraft with the disk radome means generally extending in a solid horizontal reference plane;

a plurality of elongated, relatively low gain linear radiating elements;

ground-plane means for supporting the radiating elements within the disk radome, the radiating elements extending outwardly from the round-plane means in mutually opposing pairs of radiating elements facing in opposite directions within the disk radome and disposed to radiate generally in a vertical direction;

means for sending and receiving radio frequency signal to and from the radiating elements;

the sending and receiving means disposed within and supported relative to the disk radome; and

means for coupling, through the supporting means, signals between the electronic system in the disk radome and radar system level circuitry located externally of the disk radome.

10. The antenna system of claim 9 wherein said linear radiating elements comprise dipole elements.

11. The antenna system of claim 9 wherein said pairs of radiating elements comprise dipoles configured in an end fire configuration, said dipoles being vertically polarized and having opposite poles extending upwardly and downwardly from the ground-plane means within the radome means.

12. The antenna system of claim 9 wherein said linear radiating elements are distributed in a regular pattern across the ground-plane means.

13. The antenna system of claim 12 wherein said regular pattern comprises a plurality of rows of radiating elements.

14. The antenna system of claim 13 wherein said plurality of rows of radiating elements are provided in a hexagonal grid.