Broadband conformal inclined slotline antenna array

• US 5,220,330 A
• Filed: 11/04/1991
• Issued: 06/15/1993
• Est. Priority Date: 11/04/1991
• Status: Expired due to Fees

• Current Assignee: Hughes Aircraft Company (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Salvail, Gary, Bartley, Steven W.
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US07/787,344
• Time in Patent Office: 589 Days
• Field of Search: 342/62, 342/374, 342/373, 343/700 MS, 343/705, 343/708, 343/786, 343/772, 343/770
• US Class Current: 342/62
• CPC Class Codes: H01Q 1/281 Nose antennas
• CPC Class Codes: H01Q 13/085 Slot-line radiating ends
• CPC Class Codes: H01Q 3/242 Circumferential scanning

Abstract

A missile guidance antenna that is conformal to the missile surface, dual-polarized and broadband. Slotline notch array elements (30, 52) are inclined toward boresight for both the E and H-planes. This inclination directs a greater portion of the energy toward the front of the missile. The additional energy directed forward reduces the nullifying effects of the metallic skin on the tangential E-field and enhances the performance of the other polarization. The slotline elements (30, 52) can be packed with spacing close enough to allow for electronic beam steering without creating grating lobes in the field at the highest frequency of operation.

Claims

1. An antenna array for a missile, said missile characterized by a boresight, the array comprising a plurality of aligned flared notch antenna elements, each said element inclined toward boresight of said missile to improve directivity of said array in the direction of boresight.

2. The array of claim 1 further characterized in that said antenna elements are disposed within said missile adjacent an exterior surface of the missile and arranged to conform to the contour of the exterior surface of the missile.

3. The array of claim 2 further characterized in that said array is disposed in a circumferential arrangement about said missile.

4. The array of claim 2 further characterized in that said array is arranged longitudinally along the missile.

5. The array of claim 1 wherein said antenna elements comprise a set of H-plane antenna elements inclined toward boresight.

6. The array of claim 1 wherein said antenna elements comprise a set of E-plane antenna elements inclined toward boresight.

7. The array of claim 6 wherein said E-plane antenna elements are further characterized as symmetrical flared notch antenna elements.

8. The array of claim 6 wherein said E-plane antenna elements are further characterized as asymmetrical flared notch antenna elements.

9. The array of claim 1 further characterized in that said array is dual polarized, in that it comprises a set of H-plane antenna elements inclined toward boresight and a set of E-plane antenna elements inclined toward boresight.

10. The array of claim 9 wherein said set of H-plane antenna elements comprises N H-plane elements and said set of E-plane antenna elements comprises N pairs of E-plane elements, the members of each E-plane element pairs flanking a respective one of said H-plane elements.

11. The array of claim 9 wherein said set of E-plane elements comprises N elements, and said set of H-plane elements comprises N pairs of H-plane elements, and wherein each E-plane element is positioned between a corresponding pair of H-plane elements.

12. The array of claim 1 wherein said antenna elements are further characterized as flared notch slotline elements.

13. A passive radar array system for detecting the location of a target in respect to a missile boresight, comprising:

a circumferential array of flared notch antenna elements disposed about the circumference of a missile, said elements inclined toward boresight to improve directivity in the direction of boresight;

a radar processor responsive to signals received from said array to determine the target location in relation to the missile boresight; and

means for selectively coupling the signals from selected ones or groups of ones of said antenna elements to said radar processor to permit the processor to determine the particular antenna having the highest output signal and to form a receiving subarray comprising said particular antenna element and a number of adjacent antenna elements.

14. The array system of claim 13 wherein said circumferential array comprises a set of H-plane antenna elements inclined toward the missile boresight.

15. The array system of claim 13 wherein said circumferential array comprises a set of E-plane antenna elements inclined toward the missile boresight.

16. The array system of claim 13 wherein said circumferential array is dual polarized, in that it comprises a set of H-plane antenna elements inclined toward boresight and a set of E-plane antenna elements inclined toward boresight.

17. The array system of claim 16 wherein said set of H-plane antenna elements comprises N H-plane elements and said set of E-plane antenna elements comprises N pairs of E-plane elements, the members of each E-plane element pair flanking a respective one of said H-plane elements.

18. The array system of claim 13 wherein said means for selectively coupling the signals from selected ones or groups of ones of said antenna elements comprises a switching means for selectively switching the signal from a selected antenna element to said processor, thereby enabling said processor to isolate the signal from respective antenna elements.

19. The array system of claim 18 wherein said selective coupling means further comprises a first combining network for selectively combining the signals from a first selected group of antenna elements adjacent said element producing said highest output signal, and a second combining network for selectively combining the signals from a second selected group of antenna elements adjacent said element producing said highest output signal, and a circuit responsive to the outputs from said first and second combining networks for producing respective sum and difference signals therefrom.

20. In a missile, a passive radar array system for detecting the location of a target, comprising:

a longitudinal array of flared notch antenna elements disposed longitudinally along a portion of exterior surface of said missile, said elements inclined toward boresight to improve directivity in the direction of boresight;

a radar processor responsive to signals received from said array elements to determine the target location; and

means for electronically scanning a beam formed by said longitudinal array to locate said target.

21. The array system of claim 20 wherein said longitudinal array is dual polarized, and comprises a first array of H-plane elements inclined toward the missile boresight, and a second array of E-plane elements inclined toward the missile boresight, wherein each E-plane element has a generally orthogonal orientation relative to a corresponding H-plane element, and wherein said electronic scanning means comprises means for scanning an H-plane beam formed from said array of H-plane elements and means for scanning an E-plane beam formed from said array of E-plane elements.

22. The array system of claim 21 wherein said array of H-plane elements comprises N H-plane elements and said array of E-plane elements comprises N pairs of E-plane elements, and wherein the elements comprising each pair are disposed to flank a corresponding H-plane element.

23. The array system of claim 21 wherein said array of E-plane elements comprises N elements, and said array of H-plane elements comprises N pairs of elements, each pair aligned along said longitudinal array, and wherein each E-plane element is disposed between the elements of a corresponding H-plane element pair.

24. The array system of claim 20 wherein said missile is characterized by a cylindrical body portion and a tapered nose portion, and wherein said longitudinal array is disposed along said cylindrical body portion.

25. The array system of claim 20 wherein said missile is characterized by a tapered nose portion, and wherein said longitudinal array is disposed within said nose portion and conforms to the shape of the exterior surface of said missile.