US3737906A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Electrically steerable aircraft mounted antenna
Assignee: Department of National Defence
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Filing: 1971-11-18
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Granted: 1973-06-05
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Expires: 1991-11-18
Abstract
Abstract The application discloses an electronically steerable aircraftto-satellite antenna system using a linear series of parallel dipoles fed through phase-shifting controls. By variation of the phase-shift to the various dipoles, different cones of radiation (or preferred reception) are provided. The cone axes are parallel to or coincident with the longitudinal axis of the aircraft, so that aircraft roll has little effect on the orientation of the cone.
Inventors
- 👤 L Maynard
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 07:41
CPC Classifications
H; H01; H01Q; H01Q3/00; H01Q3/26; H01Q3/30
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
156 words
An electrically steerable antenna system for use in an airborne communications system to provide communications between an aircraft and an orbiting satellite comprising: an antenna comprising a fixed linear array of dipole elements mounted on the upper parts of the aircraft on a common axis parallel to the longitudinal axis of the aircraft; phase shifting means connected to the array of dipole elements for introducing into a signal to be communicated a predetermined phase shift between adjacent dipole elements to produce an annular lobe of maximum radiation in the form of a hollow cone with its apex at the array and its axis collinear with the axis of the array; means for applying the signal to be communicated to the phase shifting means; and, means for varying the apex angle of the cone of radiation to include the orbiting satellite within the lobe of maximum radiation regardless of the relative orientations of the aircraft and satellite.
Claim 2
Dependent Claim
156 words
An electrically steerable antenna system for use in an airborne communications system to provide communications between an aircraft and an orbiting satellite comprising: an antenna comprising a fixed linear array of dipole elements mounted on the upper parts of the aircraft on a common axis parallel to the longitudinal axis of the aircraft; phase shifting means connected to the array of dipole elements for introducing into a signal to be communicated a predetermined phase shift between adjacent dipole elements to produce an annular lobe of maximum radiation in the form of a hollow cone with its apex at the array and its axis collinear with the axis of the array; means for applying the signal to be communicated to the phase shifting means; and, means for varying the apex angle of the cone of radiation to include the orbiting satellite within the lobe of maximum radiation regardless of the relative orientations of the aircraft and satellite.
Claim 3
Dependent Claim
31 words
The antenna system of claim 1 wherein the means for varying the apex angle of the cone of radiation comprises means for varying the phase shift introduced between adjacent dipole elements.
Claim 4
Dependent Claim
17 words
The antenna system of claim 2 wherein said array of dipole elements comprises at least three elements.
Claim 5
Dependent Claim
18 words
An antenna system as claimed in claim 1 wherein the number of elements in the array is nine.
Claim 6
Independent Claim
100 words
A method of communication between an in-flight aircraft having a fixed linear dipole array antenna mounted on the upper parts of the aircraft on a common axis parallel to the logitudinal axis of the aircraft and an orbiting satellite which comprises: radiating from the antenna the signal to be communicated as an annular lobe of maximum radiation in the form of a hollow cone with its apex at the array and its axis parallel to the longitudinal axis of the aircraft; and adjusting the apex angle of the cone to include the orbiting satellite within the lobe of maximum radiation.
Claim 7
Independent Claim
100 words
A method of communication between an in-flight aircraft having a fixed linear dipole array antenna mounted on the upper parts of the aircraft on a common axis parallel to the logitudinal axis of the aircraft and an orbiting satellite which comprises: radiating from the antenna the signal to be communicated as an annular lobe of maximum radiation in the form of a hollow cone with its apex at the array and its axis parallel to the longitudinal axis of the aircraft; and adjusting the apex angle of the cone to include the orbiting satellite within the lobe of maximum radiation.
Claim 8
Dependent Claim
43 words
The method of claim 5 wherein the step of radiating the signal comprises: applying the signal to one end of the linear array; and, shifting the phase of the signal between adjacent dipoles as it passes to the other end of the array.
Claim 9
Dependent Claim
24 words
The method of claim 6 wherein the step of adjusting the apex angle of the cone comprises varying the phase shift between adjacent dipoles.
References Cited (Backward Citations)
US2245660A
Cited
US2464276A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-06-04 | 1976-12-04 | 1977-06-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-06-04 | 1980-12-04 | 1981-06-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-06-04 | 1984-12-04 | 1985-06-05 | $7700.00 | Window Closed / Lapsed |