Integral antenna winglet
View Patent ↗Disclosed is a winglet radome assembly, which can include at least one antenna assembly that can send and receive signals, such as radio waves. Some implementations of the winglet radome assembly can be secured to a wing of an aircraft, such as a fixed-wing aircraft. In addition, the winglet radome assembly can be configured to secure to a distal end of the wing and can be securely adapted to a variety of aircraft.
1. A winglet radome apparatus, comprising:
an aerodynamic body configured to securely mate to a distal end of a wing of an aircraft, wherein the body comprises a leading edge, a trailing edge, a lower skin that extends between the leading edge and the trailing edge and defines a bottom surface of the body, and an upper skin that extends between the leading edge and the trailing edge and defines an upper surface of the body, and wherein the entire body is made entirely out of a material that allows uninterrupted transmission of a wireless signal through the material;
an antenna assembly enclosed within the body and configured to at least one of send the wireless signal to or receive the wireless signal from at least one location outside the body, the antenna assembly including a grounding element that enables the antenna assembly to ground to at least the wing of the aircraft.
2. The winglet radome apparatus of claim 1 , wherein the grounding element is made out of one or more of a copper material, copper coated material, tin-plated copper, or a highly conductive metal that is plated for corrosion resistance.
3. The winglet radome apparatus of claim 1 , wherein the grounding element includes a ground strap configured to directly mate with the wing and provide conductivity between the antenna assembly and the wing.
4. The winglet radome apparatus of claim 1 , wherein at least the body forms an extension to the wing of the aircraft when the body is securely mounted to the distal end of the wing.
5. The winglet radome apparatus of claim 4 , wherein the body extends along at least a part of a longitudinal axis of the wing.
6. The winglet radome apparatus of claim 5 , wherein the distal end of the body deflects away from the longitudinal axis of the wing forming an upturned wingtip.
7. The winglet radome apparatus of claim 6 , wherein at least a part of the antenna assembly resides in the upturned wingtip.
8. The winglet radome apparatus of claim 1 , wherein the antenna assembly includes a low band cable and a high band cable.
9. The winglet radome apparatus of claim 1 , wherein the wireless signal includes a radio wave.
10. The winglet radome apparatus of claim 1 , wherein the body is made out of one or more of an E-glass, S-glass, Quartz, Epoxy, Cyanate-Ester, Bismaleimide, Polyimide, Boron, fiberglass fabric or fiberglass tape.
11. The winglet radome apparatus of claim 1 , wherein the antenna assembly is configured to operate at one or more of a frequency range of 108 mHz to 174 mHz, 225 mHz to 400 mHz, or 960 mHz to 1220 mHz.
12. A method, comprising:
providing a winglet radome apparatus including an aerodynamic body configured to securely mate to a distal end of a wing of an aircraft, wherein the body comprises a leading edge, a trailing edge, a lower skin that extends between the leading edge and the trailing edge and defines a bottom surface of the body, and an upper skin that extends between the leading edge and the trailing edge and defines an upper surface of the body, and wherein the entire body is made entirely out of a material that allows uninterrupted transmission of a wireless signal through the material;
an antenna assembly enclosed within the body and configured to at least one of send the wireless signal to or receive the wireless signal from at least one location outside the body, the antenna assembly including a grounding element that enables the antenna assembly to ground to at least the wing of the aircraft; and
securing the winglet radome apparatus to the distal end of the wing of the aircraft.
13. The method of claim 12 , wherein the grounding element is made out of one or more of a copper material, copper coated material, tin-plated copper, or a highly conductive metal that is plated for corrosion resistance.
14. The method of claim 12 , wherein the grounding element includes a ground strap configured to directly mate with the wing and provide conductivity between the antenna assembly and the wing.
15. The method of claim 12 , wherein at least the body forms an extension to the wing of the aircraft when the body is securely mounted to the distal end of the wing.
16. The method of claim 15 , wherein the body extends along at least a part of a longitudinal axis of the wing.
17. The method of claim 16 , wherein the distal end of the body deflects away from the longitudinal axis of the wing forming an upturned wingtip.
18. The method of claim 17 , wherein at least a part of the antenna assembly resides in the upturned wingtip.
19. The method of claim 12 , wherein the antenna assembly includes a low band cable and a high band cable.
20. The method of claim 12 , wherein the signal includes a radio wave.
21. The method of claim 12 , wherein the body is made out of one or more of an E-glass, S-glass, Quartz, Epoxy, Cyanate-Ester, Bismaleimide, Polyimide, Boron, fiberglass fabric or fiberglass tape.
22. The method of claim 12 , wherein the antenna assembly is configured to operate at one or more of a frequency range of 108 mHz to 174 mHz, 225 mHz to 400 mHz, or 960 mHz to 1220 mHz.