CN103515714A - Slightly-inclined synchronous communication satellite superimposed double-paraboloid ellipsoid field antenna - Google Patents
Slightly-inclined synchronous communication satellite superimposed double-paraboloid ellipsoid field antenna Download PDFInfo
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- CN103515714A CN103515714A CN201210208965.0A CN201210208965A CN103515714A CN 103515714 A CN103515714 A CN 103515714A CN 201210208965 A CN201210208965 A CN 201210208965A CN 103515714 A CN103515714 A CN 103515714A
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Abstract
The invention relates to a slightly-inclined synchronous communication satellite superimposed double-paraboloid ellipsoid field antenna. The paraboloid antenna is divided into two parts along the axis: a first paraboloid and a second paraboloid. Focuses of the first paraboloid and the second paraboloid respectively form an included angle with the axis. An oval-shaped horn waveguide is arranged between the focus of the first paraboloid and the focus of the second paraboloid. The antenna provided by the invention covers the whole satellite drifting trajectory of the latitude +/-8 degrees, and a satellite earth station with a CAPS system as communication can adopt fixed directional antennas. Thus, complexity of ground antennas is minimized, and costs and maintenance difficulty of the antenna are reduced.
Description
Technical field
The present invention relates to the oval field pattern antenna of the superimposed dual paraboloid of a kind of small inclination synchronous communication satellite.
Background technology
Utilize the transponder on synchronous communication satellite, forward the carrier signal that the modulation of being launched by area navigation central station has ranging code and navigation message, broadcast earthward, realizes the design concept that passive satellite navigates, and is the central principle that CAPS system realizes location.Transponder more than needed on CAPS system synchronization communication satellite, can also forward the signal of communication of being launched by ground satcom, and this is the communication function of CAPS system.
CAPS system is controlled earth stationary satellite by changing rail position and attitude, make synchronous communication satellite develop into the inclined plane satellite of small inclination, synchronous satellite is only implemented to maintenance and the adjustment of longitudinal position, do not do maintenance and the adjustment of latitude direction position, allow it in latitude direction, freely drift about.Like this, can adjust the working track that fuel keeps satellite by the less attitude of satellite, greatly extend the useful life of synchronous communication satellite.So just open up the 2nd life cycle utilization of fixed service satellite---navigation communications applications life cycle.Generally, CAPS system can extend synchronous satellite 5-8 in useful life, has so greatly reduced the communication cost that CAPS system adopts stationary satellite satellite.
From the angle of location navigation, the synchronous inclined plane satellite that to utilize fixed service satellite drift be small inclination becomes the another class constellation of navigation positioning system, can improve the space layout of constellation, reduces DOP value, improves positioning precision
[3～5].Fixed service satellite become small inclination satellite for relay type global position system after, its satellite orbit parameter still need to forecast by surveying tracking system.For satellite navigation location, concerning the requirement of constellation, and do not require that satellite strictly on equatorial synchronous orbit position, have drift value better on the contrary, and drift value is the bigger the better in latitude direction.Retired satellite is not done, after the control of latitude direction, can make every year satellite increase drift amplitude in North and South direction, and drift increases speed variation between approximately 0.75 ° ~ 0.94 ° every year, and the cycle of variation is about 18.6a.The accumulative total effect of drift makes the orbit inclination angle of satellite As time goes on constantly become large, and maximum can reach approximately 14.5 ° of left and right, then reduces gradually again, becomes the synchronous inclined plane navigation satellite of a small inclination.
But, while utilizing transponder on CAPS navigation satellite to use as communication port, ground-plane antenna need to carry out ± 8 ° from motion tracking.This has just greatly increased antenna cost and the failure rate of CAPS system ground satellite station.Therefore, need a kind of new antenna to address the above problem.
Summary of the invention
The present invention proposes the oval field pattern antenna of the superimposed dual paraboloid of a kind of small inclination synchronous communication satellite.Object of the present invention is achieved through the following technical solutions:
The oval field pattern antenna of the superimposed dual paraboloid of small inclination synchronous communication satellite, described parabolic antenna is divided into two parts along axis, the first parabola and the second parabola, described the first parabola and the second paraboloidal focus have angle with axis shape respectively; Between described the first paraboloidal focus and the second paraboloidal focus, an elliptical horn waveguide is set.
The invention has the advantages that:
For overcoming the deficiency of the necessary You Zi motion tracking of the transponder communication function ground station of CAPS navigation satellite, this programme has proposed the burnt antenna of fan, contain latitude ± 8 ° whole satellite drift track, the ground satellite station that makes CAPS system do to communicate by letter can adopt fixed directional antenna.Reduce the complexity of ground-plane antenna, reduced antenna cost and maintenance difficulties.Make cheap CAPS system communication channel system, had the cheap earth station equipment matching with it.
Accompanying drawing explanation
Fig. 1: structural representation of the present invention;
Fig. 2: the present invention is in vertical 2D direction analogous diagram;
Fig. 3: the present invention is in horizontal 2D direction analogous diagram.
Embodiment
Be illustrated in figure 1 the oval field pattern antenna structure view of the superimposed dual paraboloid of small inclination synchronous communication satellite of the present invention.The oval field pattern antenna of the superimposed dual paraboloid of small inclination synchronous communication satellite is divided into two parts along axis, the first parabola and the second parabola, and described the first parabola and the second paraboloidal focus have angle with axis shape respectively; Between described the first paraboloidal focus and the second paraboloidal focus, an elliptical horn waveguide is set.If Fig. 2-3 are for the present invention is respectively in vertical 2D direction, horizontal 2D direction analogous diagram.
Should be appreciated that the above detailed description of technical scheme of the present invention being carried out by preferred embodiment is illustrative and not restrictive.Those of ordinary skill in the art modifies reading the technical scheme that can record each embodiment on the basis of specification of the present invention, or part technical characterictic is wherein equal to replacement; And these modifications or replacement do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (1)
1. the oval field pattern antenna of the superimposed dual paraboloid of small inclination synchronous communication satellite, it is characterized in that, described parabolic antenna is divided into two parts along axis, the first parabola and the second parabola, and described the first parabola and the second paraboloidal focus have angle with axis shape respectively; Between described the first paraboloidal focus and the second paraboloidal focus, an elliptical horn waveguide is set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210208965.0A CN103515714B (en) | 2012-06-20 | 2012-06-20 | Small inclination synchronous communication satellite overlapping dual paraboloid ellipse field pattern antenna |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210208965.0A CN103515714B (en) | 2012-06-20 | 2012-06-20 | Small inclination synchronous communication satellite overlapping dual paraboloid ellipse field pattern antenna |
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| Publication Number | Publication Date |
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| CN103515714A true CN103515714A (en) | 2014-01-15 |
| CN103515714B CN103515714B (en) | 2016-12-21 |
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| CN201210208965.0A Expired - Fee Related CN103515714B (en) | 2012-06-20 | 2012-06-20 | Small inclination synchronous communication satellite overlapping dual paraboloid ellipse field pattern antenna |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86104580A (en) * | 1986-07-08 | 1987-02-11 | 孔令如 | Microwave antenna |
| CN86211074U (en) * | 1986-12-29 | 1987-12-12 | 虎永存 | Board type multi-focal-distance paraboloidal aerial for ground satellite station |
| CN1128063A (en) * | 1993-07-30 | 1996-07-31 | 考金特光学技术公司 | Condensing and collecting optical system using an ellipsoidal reflector |
| CN2408577Y (en) * | 2000-03-02 | 2000-11-29 | 寰波科技股份有限公司 | Parabolic reflector antenna |
| CN1328628A (en) * | 1998-10-13 | 2001-12-26 | 考金特光学技术公司 | Concentrating and collecting optical system using concave toroidal reflectors |
| CN1926719A (en) * | 2003-12-04 | 2007-03-07 | 约翰·雷蒙德·Jr.·埃西格 | Modular inflatable multifunction field-deployable apparatus and methods of manufacture |
| CN202111229U (en) * | 2011-06-23 | 2012-01-11 | 浙江中星光电子科技有限公司 | Feed source of combined type |
| CN202633515U (en) * | 2012-06-20 | 2012-12-26 | 北京宏达科美科技有限公司 | Small inclination angle synchronous communication satellite superposition double-paraboloid elliptical field type antenna |
-
2012
- 2012-06-20 CN CN201210208965.0A patent/CN103515714B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86104580A (en) * | 1986-07-08 | 1987-02-11 | 孔令如 | Microwave antenna |
| CN86211074U (en) * | 1986-12-29 | 1987-12-12 | 虎永存 | Board type multi-focal-distance paraboloidal aerial for ground satellite station |
| CN1128063A (en) * | 1993-07-30 | 1996-07-31 | 考金特光学技术公司 | Condensing and collecting optical system using an ellipsoidal reflector |
| CN1328628A (en) * | 1998-10-13 | 2001-12-26 | 考金特光学技术公司 | Concentrating and collecting optical system using concave toroidal reflectors |
| CN2408577Y (en) * | 2000-03-02 | 2000-11-29 | 寰波科技股份有限公司 | Parabolic reflector antenna |
| CN1926719A (en) * | 2003-12-04 | 2007-03-07 | 约翰·雷蒙德·Jr.·埃西格 | Modular inflatable multifunction field-deployable apparatus and methods of manufacture |
| CN202111229U (en) * | 2011-06-23 | 2012-01-11 | 浙江中星光电子科技有限公司 | Feed source of combined type |
| CN202633515U (en) * | 2012-06-20 | 2012-12-26 | 北京宏达科美科技有限公司 | Small inclination angle synchronous communication satellite superposition double-paraboloid elliptical field type antenna |
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| CN103515714B (en) | 2016-12-21 |
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