CN103515715A - Double-reflection-surface antenna specialized for small-inclination-angle synchronous communication satellite - Google Patents
Double-reflection-surface antenna specialized for small-inclination-angle synchronous communication satellite Download PDFInfo
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- CN103515715A CN103515715A CN201210211225.2A CN201210211225A CN103515715A CN 103515715 A CN103515715 A CN 103515715A CN 201210211225 A CN201210211225 A CN 201210211225A CN 103515715 A CN103515715 A CN 103515715A
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Abstract
The present invention relates to a double-reflection-surface antenna specialized for a small-inclination-angle synchronous communication satellite, which comprises a main reflection surface and a back reflection surface. The back reflection surface is arranged between the main reflection surface and the focal point of the main reflection surface. The axis of the main reflection surface is provided with a horn-shaped irradiator. The antenna of the invention covers whole satellite drift track in a latitude range of +/-8 DEG, so that a fixed directional antenna can be adopted for a satellite ground station in which CAPS system is used for communication. The double-reflection-surface antenna further has the following functions: reducing complicity degree of the ground antenna, and reducing antenna cost and maintenance difficulty.
Description
Technical field
The present invention relates to the special-purpose dual reflector antenna 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 annual approximately 0.75°~0。Between 94 °, change, 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.
Summary of the invention
For overcoming the deficiency of the necessary You Zi motion tracking of the transponder communication function ground station of CAPS navigation satellite, the present invention proposes the special-purpose dual reflector antenna of a kind of small inclination synchronous communication satellite.
Object of the present invention is achieved through the following technical solutions:
The special-purpose dual reflector antenna of small inclination synchronous communication satellite, described dual reflector antenna comprises: primary reflection surface and back reflection face, described back reflection face is arranged between primary reflection surface and primary reflection surface focus, and place, described primary reflection surface axle center is provided with loudspeaker irradiator.
The invention has the advantages that:
This programme has proposed the burnt antenna of fan, contains latitude ± 8 ° whole satellite drift track, and 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 specific embodiment of the invention 1 structural representation;
Fig. 3: the specific embodiment of the invention 2 structural representations.
Embodiment
Be illustrated in figure 1 the special-purpose dual reflector antenna of small inclination synchronous communication satellite.This is fanned burnt antenna and adopts the positive rear feed mode of double-reflecting face, and subreflector is in primary reflection surface focus with firmly between reflecting surface.When small inclination satellite is positioned at angle zero degree position, same primary reflection surface axle center, wave beam reflexes to after subreflector zone line by primary reflection surface, through subreflector secondary reflection, enters the loudspeaker irradiator that is positioned at reflecting surface center, converges on feed.
Fig. 2 is specific embodiment 1 structural representation, when small inclination satellite moves to primary reflection surface shaft core position top≤+ 8 ° of positions.Wave beam projects to subreflector location on the lower side by primary reflection surface, and we are by extending the mode of subreflector downwards, and the wave beam that primary reflection surface reflection is come carries out secondary reflection and enters in the loudspeaker irradiator at reflecting surface center, finally converges on feed.
Fig. 3 is the specific embodiment of the invention 2 structural representations, when small inclination satellite moves to primary reflection surface shaft core position below≤-8 ° of positions.Wave beam projects to subreflector location on the lower side by primary reflection surface, and we are by upwards extending the mode of subreflector, and the wave beam that primary reflection surface reflection is come carries out secondary reflection and enters in the loudspeaker irradiator at reflecting surface center, finally converges on feed.
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 special-purpose dual reflector antenna of small inclination synchronous communication satellite, it is characterized in that, described dual reflector antenna comprises: primary reflection surface and back reflection face, and described back reflection face is arranged between primary reflection surface and primary reflection surface focus, and place, described primary reflection surface axle center is provided with loudspeaker irradiator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210211225.2A CN103515715A (en) | 2012-06-20 | 2012-06-20 | Double-reflection-surface antenna specialized for small-inclination-angle synchronous communication satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210211225.2A CN103515715A (en) | 2012-06-20 | 2012-06-20 | Double-reflection-surface antenna specialized for small-inclination-angle synchronous communication satellite |
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| Publication Number | Publication Date |
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| CN103515715A true CN103515715A (en) | 2014-01-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210211225.2A Pending CN103515715A (en) | 2012-06-20 | 2012-06-20 | Double-reflection-surface antenna specialized for small-inclination-angle synchronous communication satellite |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501471A (en) * | 2015-12-16 | 2016-04-20 | 上海卫星工程研究所 | Configuration of satellite loaded with large deployable antenna with double reflecting surfaces |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2408577Y (en) * | 2000-03-02 | 2000-11-29 | 寰波科技股份有限公司 | Parabolic reflector antenna |
| CN101483276A (en) * | 2008-01-10 | 2009-07-15 | 塞特玛克国际株式会社 | Antenna system for receiving signals from satellites and method for driving the same |
| CN202633516U (en) * | 2012-06-20 | 2012-12-26 | 北京宏达科美科技有限公司 | Special double-reflector antenna for slightly-inclined synchronous communication satellites |
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2012
- 2012-06-20 CN CN201210211225.2A patent/CN103515715A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2408577Y (en) * | 2000-03-02 | 2000-11-29 | 寰波科技股份有限公司 | Parabolic reflector antenna |
| CN101483276A (en) * | 2008-01-10 | 2009-07-15 | 塞特玛克国际株式会社 | Antenna system for receiving signals from satellites and method for driving the same |
| CN202633516U (en) * | 2012-06-20 | 2012-12-26 | 北京宏达科美科技有限公司 | Special double-reflector antenna for slightly-inclined synchronous communication satellites |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501471A (en) * | 2015-12-16 | 2016-04-20 | 上海卫星工程研究所 | Configuration of satellite loaded with large deployable antenna with double reflecting surfaces |
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Application publication date: 20140115 |