Hybrid steerable avionic antenna
A telecommunications antenna system for use with an aircraft is described that includes an aperture that is mounted at an angle relative to the horizon plane that does not change during system operation. Additional angle of elevation for adjustment of azimuth is provided by electronic means, such as a Rotman lens, while rotation within the horizon plane is provided by a rotating mechanism. Also disclosed is a radome for use with such an antenna system, which is provided dimensioned to accommodate the at a large value of the mounting angle and which can be trimmed to accommodate the system at smaller values of the mounting angle in order to minimize the impact on aircraft aerodynamics.
1. A telecommunications antenna, comprising:
a planar substrate disposed on a horizon plane;
a radiating aperture disposed in a single, substantially flat plane, and integrated with the planar substrate such that the radiating aperture is fixedly inclined at a predetermined, nonzero angle relative to the plane of the substrate;
transmitting and receiving elements interlaced across the radiating aperture, such that the transmitting and receiving elements are fixedly inclined at the predetermined, nonzero angle;
a rotating assembly coupled to the substrate, and configured to rotate the radiating aperture around an axis that is perpendicular to the horizon plane, to permit pointing of the antenna in azimuth; and
an electronic beam steering assembly configured to adjust the pointing angle of the radiating aperture along a second plane that is perpendicular to the horizon plane, to enable the pointing of the antenna in elevation,
wherein the predetermined, nonzero angle is fixed during operation of the telecommunications antenna.
2. The telecommunications antenna of claim 1 , wherein the predetermined, nonzero angle is fixed on installation of the telecommunications antenna.
3. The telecommunications antenna of claim 1 , wherein the predetermined, nonzero angle is fixed on manufacture of the telecommunications antenna.
4. The telecommunications antenna of claim 1 , further comprising an adjustment mechanism configured to permit adjustment of the predetermined, nonzero angle following installation of the telecommunications antenna.
5. The telecommunications antenna of claim 1 , wherein the predetermined, nonzero angle is from 1 to 20°.
6. The telecommunications antenna of claim 1 , where the predetermined, nonzero angle is a function of both a desired range of latitude operations for an aircraft and a desired configuration of a radome of the aircraft.
7. The telecommunications antenna of claim 1 , wherein the electronic beam steering assembly is configured to adjust the pointing angle of the radiating aperture from the predetermined, nonzero angle to 110°.
8. The telecommunications antenna of claim 1 , further comprising a radome comprising a peripheral edge, wherein the radome is provided configured to accommodate the radiating aperture, the rotating assembly, and the electronic beam steering assembly at a maximum value of the predetermined, nonzero angle, and is adjustable to accommodate the radiating aperture, the rotating assembly, and the electronic beam steering assembly at a non-maximum value of the predetermined, nonzero angle by removal of all or part of the peripheral edge.
9. The telecommunications antenna of claim 8 , wherein the maximum value of the predetermined, nonzero angle is 20°.
10. The telecommunications antenna of claim 8 , wherein the radome comprises indicia marking portions of the peripheral edge to be removed to accommodate different values of the predetermined, nonzero angle.
11. The telecommunication antenna of claim 1 , wherein the receiving and transmitting elements are interlaced across the radiating aperture in a non-striped configuration along the single, substantially flat plane.
12. A low-profile avionics antenna having a fixed inclination during operation of the antenna, comprising:
a radiating aperture disposed in a first plane on a planar mounting surface having a circular cross-section, wherein the planar mounting surface is fixedly inclined at installation to a predetermined, nonzero angle relative to a horizon plane that is less than 20°;
transmitting and receiving elements interlaced across the radiating aperture at the fixed non-zero angle and along the first plane, such that the transmitting and receiving elements are fixedly inclined at the predetermined, nonzero angle;
a rotating assembly coupled to the mounting surface, and configured to rotate the radiating aperture around an axis that is perpendicular to the horizon plane, to enable the pointing of the antenna in azimuth; and
an electronic beam steering assembly configured to adjust the pointing angle of the radiating aperture along a second plane that it perpendicular to the horizon plane, to enable the pointing of the antenna in elevation.
13. The avionics antenna of claim 12 , wherein the predetermined, nonzero angle is fixed on installation of the antenna.
14. The avionics antenna of claim 12 , wherein the predetermined, nonzero angle is fixed on manufacture of the antenna.
15. The avionics antenna of claim 12 , further comprising an adjustment mechanism configured to permit adjustment of the predetermined, nonzero angle following installation of the antenna.
16. The avionics antenna of claim 12 , where the predetermined, nonzero angle is a function of both a desired range of latitude operations for an aircraft and a desired configuration of a radome of the aircraft.
17. The avionics antenna of claim 12 , wherein the electronic beam steering assembly is configured to adjust the pointing angle of the radiating aperture from the predetermined, nonzero angle to 110°.
18. The avionics antenna of claim 12 , further comprising a radome comprising a peripheral edge, wherein the radome is provided configured to accommodate the radiating aperture, the rotating assembly, and the electronic beam steering assembly at a maximum value of the predetermined, nonzero angle, and is adjustable to accommodate the radiating aperture, the rotating assembly, and the electronic beam steering assembly at a non-maximum value of the predetermined, nonzero angle by removal of all or part of the peripheral edge.
19. The avionics antenna of claim 18 , wherein the radome comprises indicia marking portions of the peripheral edge to be removed to accommodate different values of the predetermined, nonzero angle.
20. The avionics antenna of claim 12 , wherein the receiving and transmitting elements are interlaced across the radiating aperture in a non-striped configuration along the first plane.