Airborne early warning radar system

• US 5,097,267 A
• Filed: 11/14/1990
• Issued: 03/17/1992
• Est. Priority Date: 11/16/1989
• Status: Expired due to Fees

• Current Assignee: Israel Aerospace Industries Limited (Government of Israel)
• Original Assignee: Israel Aerospace Industries Limited (Government of Israel)
• Inventors: Raviv, Dov
• Primary Examiner(s): Barron, Jr., Gilberto
• Application Number:
  US07/613,261
• Time in Patent Office: 489 Days
• Field of Search: 342/58, 342/60, 342/368, 342/158, 342/75, 244/3.11, 244/3.14, 343/705, 343/708
• US Class Current: 342/58
• CPC Class Codes: B64C 1/36 adapted to receive antennas or radomes
• CPC Class Codes: G01S 7/02 of systems according to group G01S13/00
• 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 3/02 using mechanical movement of antenna or antenna system as a whole

Abstract

An airborne early warning radar system comprising an automatically controlled pilotless aircraft, a phased array radar antenna disposed in the pilotless aircraft and apparatus for selectably varying the orientation of the phased array radar antenna relative to the aircraft.

Claims

1. An airborne early warning radar system comprising a pilotless aircraft, a phased array radar antenna disposed in the fuselage of the pilotless aircraft and means for selectably varying the mechanical orientation of the phased array radar antenna relative to the aircraft wherein said phased array radar antenna extends along most of the length and height of the fuselage of the aircraft.

2. An airborne early warning radar system according to claim 1 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

3. An airborne early warning radar system according to claim 2 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

4. An airborne early warning radar system according to claim 1 further comprising radio control means for controlling the operation of the means for selectably varying.

5. An airborne early warning radar system according to claim 4 wherein said means for selectably varying is operative to position said antenna in a position corresponding to either a Right, Left or Downward looking orientation.

6. An airborne early warning radar system according to claim 5 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

7. An airborne early warning radar system according to claim 6 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

8. An airborne early warning radar system according to claim 4 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

9. An airborne early warning radar system according to claim 8 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

10. An airborne warning radar system according to claim 1 wherein said means for selectably varying is operative to position said antenna in a position corresponding to either a Right, Left or Downward looking orientation.

11. An airborne early warning radar system according to claim 10 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

12. An airborne early warning radar system according to claim 11 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

13. An airborne early warning radar system according to claim 2 further comprising radio control means for controlling the operation of the means for selectably varying.

14. An airborne early warning radar system according to claim 13 wherein said means for selectably varying is operative to position said antenna in a position corresponding to either a Right, Left or Downward looking orientation.

15. An airborne early warning radar system according to claim 14 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

16. An airborne early warning system according to claim 15 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

17. An airborne early warning radar system according to claim 13 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

18. An airborne early warning radar system according to claim 17 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

19. An airborne early warning radar system according to claim 2 wherein said means for selectably varying is operative to position said antenna in a position corresponding to either a Right, Left or Downward looking orientation.

20. An airborne early warning radar system according to claim 19 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

21. An airborne early warning radar system according to claim 20 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

22. An airborne early warning radar system according to claim 1 wherein at least a portion of the fuselage of the aircraft is formed of a radar signal transparent material capable of bearing the mechanical stress brought to bear thereupon.

23. An airborne early warning radar system according to claim 22 wherein said radar signal transparent material comprises a honeycomb sandwich comprising a glass/epoxy skin and a Nomex honeycomb core.

24. An airborne radar system comprising:

a pilotless winged aircraft, at least a section of the central section portion of the fuselage of which is formed of radar transparent material;

a phased array antenna disposed in the central section; and

rotation means for rotating said phased array antenna about an axis of rotation.

25. A system according to claim 24 wherein said phased array antenna extends along most of the height and length of the fuselage.

26. A system according to claim 24 where said axis of rotation is generally along the axis of the fuselage whereby said phased array may be positioned in a position corresponding to a Right, Left or Downward looking position.