EP0346105A2 - Spacecraft antenna system - Google Patents
Spacecraft antenna system Download PDFInfo
- Publication number
- EP0346105A2 EP0346105A2 EP19890305766 EP89305766A EP0346105A2 EP 0346105 A2 EP0346105 A2 EP 0346105A2 EP 19890305766 EP19890305766 EP 19890305766 EP 89305766 A EP89305766 A EP 89305766A EP 0346105 A2 EP0346105 A2 EP 0346105A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- sub
- antenna system
- reflector
- reflectors
- coverage area
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/18—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces
- H01Q19/19—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface
- H01Q19/192—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface with dual offset reflectors
Definitions
- This invention relates to a spacecraft antenna system capable of passing radiation to or from more than one coverage area.
- a spacecraft antenna system capable of passing radiation to or from more than one coverage area, characterised by including feed means, a single shaped main reflector and at least two shaped sub-reflectors which are operable simultaneously, one for each coverage area.
- the system has two shaped sub-reflectors and the feed means provides two feeds, one for each said sub-reflector.
- a spacecraft antenna system of the invention as shown in Figure 1 of the accompanying drawings has feed means, a single shaped main reflector 3 and at least two, in this case only two, shaped sub-reflectors 4,5.
- the shaped reflector concept as disclosed in our European Patent Application No. 219321 and our co-pending UK Patent Application No. 8813655-1 of even date herewith is used to shape the main reflector 3 and two sub-reflectors 4,5.
- the feed means provides two feeds 6 and 7, with the feed 6 and sub-reflector 4 providing the coverage area 1 of Figure 2 and with the feed 7 and sub-reflector 5 providing the coverage area 2 of Figure 2.
- the feeds 6,7 and sub-reflectors 4,5 are operable simultaneously.
- the antenna system has two feeds rather than about 140 which would be needed for a multiple feed unshaped single reflector antenna of the same diameter.
- the sub-reflectors 4,5 may alternatively be mounted side by side, i.e. along a line perpendicular to the plane of Figure 1, or alternatively separated in any direction to enable the antenna system to be mounted most conveniently on a spacecraft.
- the shaped reflector optimisation technique used is based on iterative use of analysis software within a standard minimax algorithm. Essentially any parameter describing an antenna system may be optimised in an attempt to drive the antenna gains, evaluated at the set of observations points, towards a specified target template.
- the optimisation parameters are sets of biharmonic distortions on all three reflectors. At each iteration both dual reflector systems are analysed in order to compare the two sets of gains with the target values. There are over 100 optimisation variables.
- This optimisation procedure allows suppression of gain in specified regions as well as enhancement in others.
Abstract
Description
- This invention relates to a spacecraft antenna system capable of passing radiation to or from more than one coverage area.
- Obtaining several (specifically two) non-identical antenna patterns from a single antenna has previously required the very large number of feeds associated with a multiple beam antenna technique.
- There is thus a need for a generally improved and simpler antenna system for applications where several coverages are required from a single antenna, and where it is not required to change the individual pattern shapes while the satellite is in orbit. A good example is the INTELSAT hemi coverages of Earth, as shown in the accompanying Figure 2 in which it is necessary to cover
areas - According to the present invention there is provided a spacecraft antenna system capable of passing radiation to or from more than one coverage area, characterised by including feed means, a single shaped main reflector and at least two shaped sub-reflectors which are operable simultaneously, one for each coverage area.
- Preferably the system has two shaped sub-reflectors and the feed means provides two feeds, one for each said sub-reflector.
- For a better understanding of the present invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which:-
- Figure 1 is a diagrammatic side view of a spacecraft antenna system according to the present invention, and
- Figure 2 is a general view of the planet Earth showing two coverage areas.
- A spacecraft antenna system of the invention, as shown in Figure 1 of the accompanying drawings has feed means, a single shaped
main reflector 3 and at least two, in this case only two, shapedsub-reflectors 4,5. - In this invention, the shaped reflector concept, as disclosed in our European Patent Application No. 219321 and our co-pending UK Patent Application No. 8813655-1 of even date herewith is used to shape the
main reflector 3 and twosub-reflectors 4,5. - In the example illustrated in Figure 1 the feed means provides two
feeds feed 6 and sub-reflector 4 providing thecoverage area 1 of Figure 2 and with thefeed 7 andsub-reflector 5 providing thecoverage area 2 of Figure 2. Thefeeds sub-reflectors 4,5 are operable simultaneously. Thus the antenna system has two feeds rather than about 140 which would be needed for a multiple feed unshaped single reflector antenna of the same diameter. - The
sub-reflectors 4,5 may alternatively be mounted side by side, i.e. along a line perpendicular to the plane of Figure 1, or alternatively separated in any direction to enable the antenna system to be mounted most conveniently on a spacecraft. - The shaped reflector optimisation technique used is based on iterative use of analysis software within a standard minimax algorithm. Essentially any parameter describing an antenna system may be optimised in an attempt to drive the antenna gains, evaluated at the set of observations points, towards a specified target template. In this case the optimisation parameters are sets of biharmonic distortions on all three reflectors. At each iteration both dual reflector systems are analysed in order to compare the two sets of gains with the target values. There are over 100 optimisation variables.
- This optimisation procedure allows suppression of gain in specified regions as well as enhancement in others.
Claims (2)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8813656 | 1988-06-09 | ||
GB888813656A GB8813656D0 (en) | 1988-06-09 | 1988-06-09 | Spacecraft antenna system |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0346105A2 true EP0346105A2 (en) | 1989-12-13 |
EP0346105A3 EP0346105A3 (en) | 1991-07-03 |
Family
ID=10638349
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19890305766 Withdrawn EP0346105A3 (en) | 1988-06-09 | 1989-06-07 | Spacecraft antenna system |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0346105A3 (en) |
GB (1) | GB8813656D0 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6603437B2 (en) * | 2001-02-13 | 2003-08-05 | Raytheon Company | High efficiency low sidelobe dual reflector antenna |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4298877A (en) * | 1979-01-26 | 1981-11-03 | Solar Energy Technology, Inc. | Offset-fed multi-beam tracking antenna system utilizing especially shaped reflector surfaces |
GB2098806A (en) * | 1981-04-27 | 1982-11-24 | Kokusai Denshin Denwa Co Ltd | Multiple reflector antenna |
US4591866A (en) * | 1983-02-04 | 1986-05-27 | Kokusai Denshin Denwa Kabushiki Kaisha | Multi-beam antenna and its configuration process |
EP0219321A1 (en) * | 1985-10-10 | 1987-04-22 | British Aerospace Public Limited Company | Antenna systems |
-
1988
- 1988-06-09 GB GB888813656A patent/GB8813656D0/en active Pending
-
1989
- 1989-06-07 EP EP19890305766 patent/EP0346105A3/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4298877A (en) * | 1979-01-26 | 1981-11-03 | Solar Energy Technology, Inc. | Offset-fed multi-beam tracking antenna system utilizing especially shaped reflector surfaces |
GB2098806A (en) * | 1981-04-27 | 1982-11-24 | Kokusai Denshin Denwa Co Ltd | Multiple reflector antenna |
US4591866A (en) * | 1983-02-04 | 1986-05-27 | Kokusai Denshin Denwa Kabushiki Kaisha | Multi-beam antenna and its configuration process |
EP0219321A1 (en) * | 1985-10-10 | 1987-04-22 | British Aerospace Public Limited Company | Antenna systems |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6603437B2 (en) * | 2001-02-13 | 2003-08-05 | Raytheon Company | High efficiency low sidelobe dual reflector antenna |
Also Published As
Publication number | Publication date |
---|---|
EP0346105A3 (en) | 1991-07-03 |
GB8813656D0 (en) | 1988-07-13 |
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Legal Events
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
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17P | Request for examination filed |
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17Q | First examination report despatched |
Effective date: 19931026 |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 19940308 |