Radome having localized areas of reduced radio signal attenuation

• US 9,564,681 B2
• Filed: 03/13/2014
• Issued: 02/07/2017
• Est. Priority Date: 11/11/2013
• Status: Active Grant

• Current Assignee: Gogo Business Aviation LLC (GOGO Incorporated)
• Original Assignee: Gogo LLC (GOGO Incorporated)
• Inventors: Cordone, Sean Scott
• Primary Examiner(s): Levi, Dameon E
• Assistant Examiner(s): Alkassim, Jr., AB Salam
• Application Number:
  US14/209,713
• Publication Number:
  US 20150130672A1
• Time in Patent Office: 1,062 Days
• Field of Search: 343/705, 343/872
• US Class Current: 1/1
• 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

Abstract

A radome having localized areas of reduced radio signal attenuation includes a body having a first portion and a second portion. The first portion is mechanically stronger than the second portion and the second portion has a reduced radio signal attenuation property compared to the first portion.

Claims

1. A radome for an aircraft, the radome comprising:

a shell having a front end and an aft end, the shell forming an enclosure when mounted on an aircraft, the enclosure being sized and shaped to house a first radio antenna and a second radio antenna;

wherein the shell includes a first portion that has mechanical properties that are different from the mechanical properties of the remaining portions of the shell, a second portion that has a reduced radio signal attenuation property when compared to the first portion, and a third portion that has a reduced radio signal attenuation property when compared to the first portion, the first portion including a bulkhead plate that extends downward from an inner surface of the first portion, the bulkhead plate structurally reinforcing the first portion without interfering with line of sight transmission or reception to/from the radio antenna,

wherein the first portion is located towards the front end of the shell, the second portion is located aft of the first portion, and the third portion is located aft of the second portion; and

wherein the second portion and the third portion are joined by a cross bridge having a plurality of support posts extending downward, away from an inner surface of the shell, the support posts maintaining clearance from the mounting assembly during radome impacts.

2. The radome of claim 1, wherein the first portion is formed from one of an A-sandwich, a C-sandwich, a laminate, and a half-wave structure.

3. The radome of claim 1, wherein the second portion is formed from one of an A-sandwich, a C-sandwich, a laminate, and a half-wave structure.

4. The radome of claim 1, wherein the third portion is formed from one of an A-sandwich, a C-sandwich, a laminate, and a half-wave structure.

5. The radome of claim 1, wherein the cross bridge is formed from one of an A-sandwich, a C-sandwich, a laminate, and a half-wave structure.

6. The radome of claim 1, wherein at least one support post is formed from 0.25 inch outer diameter 6061-T6 aluminum.

7. The radome of claim 1, further comprising a skirt portion extending from the first portion.

8. The radome of claim 7, wherein the skirt portion is formed from 0.125 inch thick 6061-T6 aluminum.

9. The radome of claim 8, wherein the skirt portion is joined to the first portion with an edgeband that is formed from one of an A-sandwich, a C-sandwich, a laminate, and a half-wave structure.

10. The radome of claim 1, wherein the shell is attached to one of a dorsal portion of an aircraft, and a ventral portion of an aircraft.

11. An aircraft having a radome with a localized area of reduced radio signal attenuation, the aircraft comprising:

a fuselage having a first end and a second end;

a pair of wings attached to the fuselage, and

a radome attached to the fuselage, the radome including;

a shell having a front end and an aft end, the shell forming an enclosure when attached to the fuselage, the enclosure being sized and shaped to house a first radio antenna and a second radio antenna,

wherein the shell includes a first portion that has mechanical properties that are different from the mechanical properties of the remaining portions of the shell a second portion that has a reduced radio signal attenuation property when compared to the first portion, and a third portion that has a reduced radio signal attenuation property when compared to the first portion, the first portion including a bulkhead plate that extends downward from an inner surface of the first portion, the bulkhead plate structurally reinforcing the first portion without interfering with line of sight transmission or reception to/from the radio antenna,

wherein the first portion is located towards the front end of the shell, the second portion is located aft of the first portion, and the third portion is located aft of the second portion, and

wherein the second portion and the third portion are joined by a cross bridge having a plurality of support posts extending downward, away from an inner surface of the shell, the support posts maintaining clearance from the mounting assembly during radome impacts.

12. The aircraft of claim 11, wherein the first portion is mechanically stronger than the second portion.

13. The aircraft of claim 12, wherein the first portion is capable of withstanding an impact from a four pound bird at maximum Vc of the aircraft at sea level or at 0.85 times the maximum Vc of the aircraft at 8,000 feet.

14. The aircraft of claim 11, wherein the first radio antenna is a mechanically steered phased array antenna.

15. The aircraft of claim 11, wherein the second portion has less radio signal attenuation across a transmit band and the third portion has less radio signal attenuation across a receive band.

16. The aircraft of claim 15, wherein a radio transmit signal has an attenuation reduction of 2 dB or more when transmitted through the second portion than when transmitted through the first portion.