An airborne antenna and a system for mechanically steering an airborne antenna

Abstract: A helical-element antenna as part of a communication system is mechanically steered with reference to an azimuth axis (28) and an elevation axis (32) within a positioning envelope greater than hemispherical. The system for mechanically steering the helical antenna (10) includes a supporting frame (22) having an azimuth member with a longitudinal axis coinciding with the azimuth axis (28) around which the antenna rotates. Further, the supporting frame includes an elevation member (30) that is integral with the azimuth member and has a longitudinal axis displaced from the azimuth axis. An interface fitting rotatably mounts the antenna to the elevation member. The supporting frame is rotatably mounted to a pedestal base (20) that has a plane perpendicular to the azimuth axis. To position the antenna about the azimuth axis, an azimuth steering unit (36) is energized to rotate the supporting frame 360 degrees around the azimuth axis. For positioning the antenna about the elevation axis, an elevation steering unit (56) rotates the interface fitting and the antenna through a gear coupling about the elevation axis. The total rotation excursion about the elevation axis is typically 180 degrees and points the antenna through a range of elevation angles.

Description: TECHNICAL FIELD This invention relates to a system for mechanically steering, with reference to an azimuth axis and an elevation axis, an airborne high gain antenna; and more particularly to a system for mechanically steering an airborne antenna with reference to non-orthogonal azimuth and elevational axes. BACKGROUND ART Heretofore, a number of systems have been developed to non-mechanically steer an airborne antenna of a communication system. These previous systems have been less than satisfactory because of degradation of antenna performance parameters such as: gain, axial ratio, beam width, and sidelobe levels, to illustrate a few examples. Such parameters were noted to be degraded as a function of the steering angle of such non-mechanically steered systems. Further, early non-mechanical steered systems had limited coverage of the total field of view from a given position. EP-A-0 274 979, which is an intermediate document falling under Article 54(3) EPC, discloses a system for mechanically steering an airborne antenna. In accordance with the present invention there is provided a system for mechanically steering an airborne antenna that provides for more than hemispherical coverage as the antenna is differentially positioned about non-orthogonal azimuth and elevational axes. Mechanically steering the antenna provides the advantage of minimizing or eliminating the degradation of the important antenna figures of merit. The antenna system of the present invention meets the technical requirements of satellite networks with which the antenna may interface. For example, the antenna steered by the system of the present invention finds utility in communication with a satellite system for air traffic control, passenger telephone and telex services, airline communications, and navigational communications, all over either secure or clear transmission links. Typically the antenna of the present invention which may be positioned by the system of the present invention comprises a radiating helical element that is designed to maximize antenna gain and minimize axial ratio. In one embodiment disclosed in EP-A-0 274 979, the element itself is surrounded by a metal cone in an effort to decrease the beam width of the helical element with the resulting advantage of increasing the gain of the antenna. Such a metal cone, however, is not a requirement for operation of the helical antenna of the present invention. In a conventional communication system, the helical antenna element interfaces to a diplexer, a low noise amplifier, and a high power amplifier. Although not limited thereto, the steering system of the present invention finds application for mounting an antenna on the vertical stabilizer of a Boeing 747 type aircraft. Also, the steering system finds utility for mounting an antenna on the fuselage of many presently operating aircraft. In all applications, a radome protects the antenna and the positioning systems from the airborne environment, and provides an installation with a desired aerodynamic shape to minimize drag. DISCLOSURE OF THE INVENTION In accordance with a first aspect of the invention, there is provided an antenna/pedestal assembly as claimed in claim 1 and in a second aspect as claimed in claim 3. BRIEF DESCRIPTION OF THE DRAWINGS For a more complete understanding of the present invention and the advantages thereof, reference is now made to the following description taken in conjunction with the accompanying drawing in which; FIGURE 1 is a pictorial view of a system for mechanically steering an airborne antenna; FIGURE 2 is a side view, partially cut away of the system of FIGURE 1 showing the antenna/pedestal assembly for the antenna of FIGURE 1; FIGURE 3 is a schematic illustration of the movement of the antenna around the azimuth and elevational axes; FIGURE 4 is a side view, partially cut away, of an embodiment of the helical antenna element of the present invention and the mounting thereof with reference to the antenna/pedestal assembly; FIGURE 5 is a block diagram of an aeronautical high gain antenna system including the antenna/pedestal assembly of FIGURE 2; and FIGURE 6 is a block diagram of a single element helical antenna system for use with the pedestal assembly of the present invention. DETAILED DESCRIPTION Referring to FIGURE 1, there is shown a pictorial view of a steerable/antenna and pedestal assembly including a single helix antenna element 10 surrounded by a metal cone 12 that functions to decrease the beamwidth of the helical element and therefore increase the gain of the antenna. The helical element 10 is supported in the metal cone 12 by crossbracing supporting rods 14 where each of the supporting rods is made from a composite non-metallic material. The cone 12 may also be made of a non-metallic material and serve only as a mechanical support for the antenna element 10. Supported on the cone 12 are electronic components of the antenna system including a diplexer 16, a low noise amplifier 18 and a power amplifier (not shown). The high power amplifier is located either on the cone 12 or in the interior of an aircraft when the system is mounted to an aircraft. These electronic components are interconnected into an antenna system such as illustrated in FIGURE 6, to be described. The antenna element is mechanically steered by a differentially mounted pedestal including a pedestal base ring 20 to which is rotatably mounted a support frame 22. Referring to FIGURE 2, there is shown the differentially mounted pedestal including the pedestal base ring 20 to which is rotatably mounted by means of a bearing 24 the support frame 22. The support frame 22 includes an azimuth member 26 having a longitudinal axis coinciding with the azimuth axis 28 of the antenna system. Integrally formed with azimuth member 26 is an elevation member 30 having a longitudinal axis coinciding with the elevation axis 32 of the antenna system. As illustrated in FIGURE 2, as an example, the angular displacement between the azimuth axis 28 and the elevational axis 32 is 52.5 degrees providing an elevation pointing range of 105 degrees, from -15 degrees to +90 degrees. The angle of displacement between the azimuth axis and the elevation axis is selected to provide the desired elevation pointing as the antenna 10 is rotated about the azimuth axis 28 and the elevation axis 32. In a first case, the antenna element 10 rotates about the elevational axis 32 from a position of -15 degrees to a position of +90 degrees relative to the plane of the base ring 20. Attached to the azimuth member 26, is a motor support 34 to which is mounted an azimuth steering unit 36 comprising a position encoder 44 and a drive motor having a drive and sprocket 38. An azimuth drive cogged belt 40 engages the drive sprocket 38 and also engages a fixed sprocket 42 of the pedestal base ring 20. Energization of the azimuth steering drive unit causes the entire support frame 22 including the azimuth member 26 to be rotated with reference to the pedestal base ring 20 around the azimuth axis 28. The support frame 22 is free to rotate 360 degrees with reference to the base ring 20. To limit and reference to a key position of the azimuth member 26 with reference to the pedestal base ring 20, an azimuth limit switch including a Hall-effect sensor 46 and a vane 48 is fixed to the pedestal ring 20 and the azimuth member 26. The position of the azimuth axis is determined by monitoring the output on an azimuth encoder 44 by counting and storing pulse data relative to the azimuth reference key identified by the limit switch. Subsequent to the arrival at the reference key position, azimuth feedback signals from the azimuth encoder 44 are applied to an antenna control unit to digitally control energization and rotational displacement of the azimuth steering unit 36. Integral with the elevation member 30 is an elevation bearing housing 50 that includes bearing members (one shown 51) for rotatably supporting an antenna/pedestal interface fitting 52. The antenna/pedestal interface fitting 52 includes a hollow bearing internal to the bearing member and a U-shaped bracket 54 attached to the outer surface of the metal cone 12. Supported by the elevation bearing housing 50 is an elevation steering unit 56 for rotatably driving a pinion gear 58 that engages a driven gear 60. The driven gear 60 is secured to the antenna/pedestal interface fitting 52 such that energization of the elevation steering unit 56 causes rotation of the cone 12 and the supported antenna element 10 around the elevation axis 32. To limit and reference to a key position of the antenna element 10 with reference to the elevation axis 32, there is provided an elevation limit switch assembly including a Hall-effect position sensor 64 mounted to the elevation member 30 and a sensor actuating vane 66 mounted to the antenna/pedestal interface fitting 50. Elevation feedback signals from an elevation encoder 62 are applied to the antenna control unit for monitoring the actual position of the elevation axis referenced to the elevation limit switch assembly. Typically, the antenna and pedestal assembly of the present invention is designed for installation on the vertical stabilizer of a Boeing 747 type aircraft, or on the fuselage of other aircraft. In any installation, the antenna and pedestal assembly is enclosed within a radome 68 to protect the assembly from the airborne environment and provide the desired aerodynamic configuration to minimize drag forces. Additional components of the system illustrated in FIGURE 2 include the diplexer 16 and the low noise amplifier 18 attached to the outer surface of the cone 12. These various electronic components are interconnected to the helical antenna 10 by means of an element connector 70. Such a connector and interconnections between the antenna element 10 and the various electronic components are part of a conventional installation and interconnection system. Referring to FIGURE 3, there is schematically illustrated the antenna/pedestal assembly of FIGURE 2 for positioning the antenna 10 with reference to the azimuth axis 28 and the elevation axis 32. Shown in dotted outline are various positions of the antenna 10 as it rotates about the elevation axis 32. As illustrated, the antenna 10 may be positioned in elevation from approximately -15 degrees to +90 degrees with reference to the plane of the base ring 20. In any of the positions illustrated, the antenna is also positionable about the azimuth axis 28 by rotation of the support frame 22 with reference to the base ring 20. As previously discussed, the antenna 10 is rotatable through 360 degrees around the azimuth axis 28. This combined rotational envelope provides pointing coverage which exceeds a hemispherical configuration and is achievable by the mechanical pedestal element of the present invention. The desired position for the antenna 10 is determined by the antenna control unit to be described with reference to FIGURE 5. Referring to FIGURE 4, there is shown an embodiment of the helical antenna element supported on the differentially mounted pedestal of the present invention wherein like reference numerals are used for parts found in FIGURES 1 through 3. The differentially mounted pedestal includes the pedestal base ring 20 of FIGURE 2 to which is mounted the support frame 22. The support frame 22 includes an azimuth member 26 having longitudinal axis coinciding with the azimuth axis 28 of the antenna system. Integrally formed with the azimuth member 26 is an elevation member 30 having a longitudinal axis coinciding with the elevation axis 32 of the antenna system. The differentially mounted pedestal of FIGURE 4 provides substantially the same angular displacement between the azimuth axis 28 and the elevation axis 32 as the differential mounted pedestal of FIGURE 2. Also similar to the differentially mounted pedestal of FIGURE 2 is an azimuth steering unit comprising a position encoder and a drive motor, not detailed in FIGURE 4. As explained with reference to FIGURE 2, energization of the azimuth steering drive unit causes the entire support frame 22 including the azimuth member 26 to be rotated with reference to the pedestal base ring 20 around the azimuth axis 28. Integral with the elevation member 30 is an elevation bearing housing 50 that includes bearing members for rotatably supporting an antenna/pedestal interface fitting 100. As illustrated, the fitting 100 is a support bracket having two sections integrally formed at an oblique angle to support the antenna about an axis 102. Attached to the antenna/pedestal interface fitting 100, is a single helix antenna element 104. This helix antenna element 104 is attached to and supported by the fitting 100 by means of a bracket 106. RF energy from the antenna element to the electronic components of the antenna system is transmitted by means of energy guides 108. As illustrated in FIGURE 4, the antenna element 104 comprises two sections, a first section 104a having a substantially uniform diameter terminating in a cone shaped section 104b tapering from a base integral with the section 104a to an apex. The antenna element 10 of FIGURE 2 and antenna element 104 of FIGURE 4 provide somewhat varying characteristics that depend on the use of the antenna system of the present invention. As illustrated in FIGURE 4. the antenna element 104 is mounted to the differentially mounted pedestal directly by means of the fitting 100. This is an alternate construction of the antenna system of FIGURE 2 in that the cone 12 is not utilized in the embodiment of FIGURE 4. Also included in the mechanism of FIGURE 4 is an elevation steering unit that when energized causes rotation of the antenna element 104 about the elevation axis. This is a similar construction to the pedestal of FIGURE 2. Additional components of the system illustrated in FIGURE 2 including the diplexer 16 and the low noise amplifier 18 are positioned remote from the pedestal of FIGURE 4 inasmuch as this embodiment does not utilize the cone 12 for mounting purposes. As described previously, these various electronic components are interconnected to the helical antenna 104 by means of various guides and connectors. Referring to FIGURE 5, there is shown a block diagram of the antenna/pedestal assembly for an antenna system of FIGURES 1, 2 and 4 including an antenna control unit 70. This control unit receives positioning information for position control of the antenna 10 or the antenna 104 on an input line 72. Also coupled to the antenna control unit are relative receive signal strength inputs on input line(s) 76. These relative strength signals are received from the helical antenna electronic components to position the antenna 10 or the antenna 104 to maximize received signal strength. In addition to position control signals for the pedestal steering units 36 and 56, the antenna control unit 70 outputs antenna status information on a line 80. Functionally, the antenna control unit 70 operates to provide elevation command signals on line(s) 82 to the elevation steering unit 56 and azimuth command signals on line(s) 84 to the azimuth steering unit 36. In FIGURE 5 these command signals are shown applied to the pedestal represented by a functional block identified by the reference numeral 86. Also applied to the pedestal 86 are RF input signals to the antenna 10 or the antenna 104 and RF output signals received by the antenna. As previously explained, the position of the azimuth member 26 and the elevation member 30 is monitored by means of encoders 44 and 62, respectively (FIGURES 2 and 4). Feedback signals from these encoders are applied by means of lines 88 and 90 to the antenna control unit 70. Also illustrated in FIGURE 5 is the radome 68 provided with controlled cooling by means of a conduit 92. Cooling of the radome 68 is conventional and further description is not deemed necessary for an understanding of the present invention. In operation, the antenna control unit 70 receives the various input signals which are evaluated and processed for differential coordinate conversion to determine the required rotation at the azimuth axis 28 and the elevational axis 32 to achieve the desired pointing angles of the antenna 10 or the antenna 104. Azimuth command signals are generated and applied to the azimuth steering unit 36 and elevation command signals are applied to the elevational steering unit 56. The respective steering units are energized until the desired position for the antenna is identified by means of the feedback signals from the encoders 44 and 62. Thus, the antenna control unit 70 along with the steering units 36 and 56 are part of a servo control system including a feedback loop provided by the encoders 44 and 62. Referring to FIGURE 6, there is shown a block diagram of the antenna system where the single element helical antenna 10 is interconnected to electronic components of the system. Radiating helical elements of the antenna 10 are connected to the diplexer 16, which in the receive mode, applies an RF input to a low noise amplifier 18. In a transmit mode, the diplexer 16 receives RF output signals from the power amplifier 94. In accordance with conventional antenna systems, the low noise amplifier 18 is connected to a receiver and the power amplifier 94 is connected to a transmitter. A further description of such a receiver and transmitter is not considered necessary to understand the present invention and will not be further described.

Claims: An antenna/pedestal assembly for an airborne communications system where the assembly includes an antenna (104) having a longitudinal axis and including a radiating element positioned with reference to an azimuth axis (28) and an elevational axis (32), a pedestal including a pedestal base (22), an azimuth member (26) having a longitudinal axis coinciding with the azimuth axis (28), means to couple the azimuth member (26) to the pedestal base (22) to permit rotation of said azimuth member (26), an azimuth steering unit (36) to rotate the azimuth member (26) with reference to the pedestal base (22), an elevational member (30) integral with the azimuth member (26) and having a longitudinal axis coinciding with the elevational axis (32) and displaced from the azimuth axis (28) as the bisector of the included angle of desired elevation coverage, an elevational-steering unit (56) to rotate the antenna (104) with reference to the elevational member (30), and an antenna control unit (70), coupled to the azimuth steering unit and the elevational-steering unit, to generate steering control signals in response to antenna position signals, RF signals received by said antenna (104) and navigational and altitude information signals, characterized by: said elevational axis (32) being non-orthogonal to and intersecting the azimuth axis (28), interface means for coupling said antenna (104) to the elevational member (30) such that the longitudinal axis of the antenna (104) will be non-orthogonal to and intersecting said elevational axis (32) to permit rotation of said antenna (104) with reference to the elevational member (30) such that the antenna (104) may cover an area greater than hemispherical and in at least one position the antenna (104) and the longitudinal axis thereof coincide with the azimuth axis (28), and the antenna (104) having a helical cylindrical section (104a) of substantially uniform diameter and being mounted to the differentially mounted pedestal (22) directly by means of a fitting (100), without the use of a cone (12). An antenna/pedestal assembly as in Claim 1 further characterized by the antenna (104) terminating in a cone section (104b) tapering from a base integral with the cylindrical section (104a) to an apex. An antenna/pedestal assembly for an airborne communications system where the assembly includes an antenna (104) having a longitudinal axis (102) and including a radiating element positioned with reference to an azimuth axis (28) and an elevational axis (32), a pedestal including a pedestal base (22), an azimuth member (26) having a longitudinal axis coinciding with the azimuth axis (28), means to couple the azimuth member (26) to the pedestal base (22) to permit rotation of said azimuth member (26), an azimuth steering unit (36) to rotate the azimuth member (26) with reference to the pedestal base (22), an elevational member (30) integral with the azimuth member (26) and having a longitudinal axis coinciding with the elevational axis (32) and displaced from the azimuth axis (28) as the bisector of the included angle of desired elevation coverage, an elevational-steering unit (56) to rotate the antenna (104) with reference to the elevational member (30), and an antenna control unit (70), coupled to the azimuth steering unit and the elevational-steering unit, to generate steering control signals in response to antenna position signals, RF signals received by said antenna (104) and navigational and altitude information signals, characterized by: said elevational axis (32) being non-orthogonal to and intersecting the azimuth axis (28) at a point, interface means for coupling said antenna (104) to the elevational member (30) such that the longitudinal axis (102) of the antenna (104) will be non-orthogonal to said elevational axis (32) to permit rotation of said antenna (104) with reference to the elevational member (30) such that the antenna (104) may cover an area greater than hemispherical, said longitudinal axis (102) of the antenna (104) intersecting both the azimuth axis (28) and elevational axis (32) at a point other than the intersection of the azimuth axis (28) and elevational axis (32) and the antenna (104) having a helical cylindrical section (104a) of substantially uniform diameter and being mounted to the differentially mounted pedestal (22) directly by means of a fitting (100), without the use of a cone (12).

Inventors: ABDELRAZIK MOHAMED, CORCORAN BOYD LEE, MARTIN JOHN DURANT, ABDELRAZIK, MOHAMED, CORCORAN, BOYD LEE, MARTIN, JOHN DURANT
Applicants: E SYSTEMS INC, E-SYSTEMS, INC.
Application year: 1988
Main classification: H01Q3
IPC codes: H01Q1, H01Q3