CN102723582B - Meta-material satellite antenna and satellite receiving system - Google Patents

Abstract

The invention discloses a meta-material satellite antenna, comprising a meta-material flat plate which is arranged behind a signal transceiver, wherein the meta-material flat plate comprises a core layer and a reflection plate arranged on the rear surface of the core layer; the core layer comprises a substrate and a plurality of artificial micro-structures attached to the front surface of the substrate; the reflection plate is attached to the rear surface of the substrate; after electromagnetic waves sent by the signal receiver pass through the meta-material flat plate, the minor lobe level of the satellite antenna is effectively reduced; and the sheet-shaped meta-material flat plate replaces a traditional parabolic antenna, so that the manufacturing and machining are easier and the cost is lower; the whole thickness of the meta-material flat plate designed by the invention is at a millimeter grade and the meta-material flat plate is very light and thin; and the special artificial micro-structures are adopted so that the satellite antenna has a frequency selection function. The invention further provides a satellite receiving system.

Description

A kind of meta-material satellite antenna and satellite receiving system

Technical field

The present invention relates to the communications field, more particularly, relate to a kind of meta-material satellite antenna and satellite receiving system.

Background technology

Existing satellite antenna, such as satellite television receiving antenna, usually adopt traditional reflector antenna to be generally parabolic antenna, parabolic antenna is responsible for the signal reflex received to the signal transceiver being positioned at focus place.

When receiving from the electromagnetic wave signal that satellite transmits, after parallel electromagnetic wave (because the distance of satellite and the earth is quite far away, its electromagnetic wave sent can think plane wave when arriving ground) is reflected by parabolic antenna, converge on signal transceiver.Usually, the signal transceiver that parabolic antenna is corresponding is a horn antenna, and the selection of this satellite antenna to frequency has certain limitation.

But the Machining of Curved Surface difficulty of the reflecting surface of parabolic antenna is large, and required precision is also high, therefore, make trouble, and cost is higher.

Summary of the invention

Technical problem to be solved by this invention is, for the processing of existing satellite antenna not easily, defect that cost is high, provide a kind of and process simple, low cost of manufacture and there is the meta-material satellite antenna of He Ne laser function.

The technical solution adopted for the present invention to solve the technical problems is: a kind of meta-material satellite antenna, described meta-material satellite antenna comprises the metamaterial flat being arranged on signal transceiver rear, described metamaterial flat comprises core layer and is arranged on the reflecting plate of core layer rear surface, described core layer comprises substrate and is attached to multiple man-made microstructure of substrate front surface, described substrate rear surface is attached with described reflecting plate, and described reflecting plate is latticed reflecting plate; Described each man-made microstructure comprises many from the outside spiral extension of a central point and mutually disjoint helix; Described core layer in the normal direction refractive index remains unchanged, with the front surface of core layer for XY plane, with signal transceiver equivalent point core layer front surface in the plane be projected as origin of coordinates O, set up the two-dimensional coordinate system of XOY, the refractive index of described core layer front surface any point (x, y) meets following formula:

$n_{(x,y)}=n_{\max }-\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\×\sin \mathrm{\γ}-(s+\mathrm{k\λ})}{D};$

s＝2z _ocosγ；

$k=\mathrm{floor}\left\{\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\×\sin \mathrm{\γ}-2z_o\cos \mathrm{\γ}}{\mathrm{\λ}}\right\};$

$D=\frac{\mathrm{\λ}}{2(n_{\max }-n_{\min })};$

Wherein, n _{(x, y)}represent the refractive index of core layer front surface any point (x, y);

Z _orepresent the vertical range of signal transceiver equivalent point to core layer front surface;

Y _orepresent the y coordinate figure of the front surface edge of this core layer and the intersection point of y-axis positive direction;

When γ represents that signal transceiver is used as to launch, its electromagnetic wave launched after metamaterial flat, angle formed by the plane electromagnetic wave of outgoing and core layer normal direction, γ is not equal to zero;

N _maxrepresent the maximum of the refractive index of core layer;

N _minrepresent the minimum value of the refractive index of core layer;

λ represents the electromagnetic wavelength corresponding to the centre frequency of meta-material satellite antenna;

D is the thickness of core layer;

Floor represents and rounds downwards.

Further, each bar helix of described each man-made microstructure is outwards clockwise or counter-clockwise helical from described central point.

Further, described each man-made microstructure comprises many spiral broken lines.

Further, described each bar spiral broken line is at the formation right angle, position of bending.

Further, described helix is metal wire.

Further, described meta-material satellite antenna also comprises the diaphragm covered in man-made microstructure, and described diaphragm is PS plastics, PET or HIPS plastic, and the thickness of described diaphragm is 0.1-2mm.

Further, the thickness of described core layer is 0.11-2.5mm, and wherein, the thickness of substrate is 0.1-2mm, and the thickness of multiple man-made microstructure is 0.01-0.5mm.

Further, the thickness of described core layer is 1.036mm, and wherein, the thickness of substrate is 1.018mm, and the thickness of multiple man-made microstructure is 0.018mm.

Further, in described latticed reflecting plate, each sheet metal is identical square-shaped metal sheet, and its length of side is 18-20mm; Gap between adjacent metal sheet is 0.13-0.18mm, and the thickness of sheet metal is 0.01-0.5mm.

Further, the square-shaped metal sheet of each sheet metal of described reflecting plate to be the length of side be 19mm, the gap between adjacent metal sheet is 0.15mm, and the thickness of sheet metal is 0.018mm.

Further, described man-made microstructure is the metal micro structure be made up of copper cash or silver-colored line, described metal micro structure by etching, plating, bore quarters, photoetching, electronics carve or ion carve method adhere on the substrate.

According to meta-material satellite antenna of the present invention, by the refraction index profile of careful design core layer, the electromagnetic wave that signal transceiver is sent is after metamaterial flat, formed by the plane electromagnetic wave of outgoing and core layer normal direction, angle is non-vanishing, namely the electromagnetic wave of outgoing is different with the normal direction of core layer, relative to electromagnetic wave with the normal direction outgoing of core layer, effectively can reduce the minor level of satellite antenna, conversely, when the electromagnetic wave sent by satellite is incident with above-mentioned angle, after metamaterial flat, can converge at signal transceiver equivalent point place, in addition, replace traditional parabolic antenna by the metamaterial flat of sheet, manufacture processing and be more prone to, cost is cheaper, and the metamaterial flat integral thickness designed according to this is in addition in millimeter rank, and suitable is frivolous.

Present invention also offers a kind of satellite receiving system, comprise satellite antenna, signal transceiver, the tuner of connection signal transceiver and the satellite receiver that is connected with tuner, described satellite antenna is above-mentioned meta-material satellite antenna, and described satellite antenna set is at the rear of signal transceiver.

Accompanying drawing explanation

Fig. 1 is the structural representation of meta-material satellite antenna of the present invention;

Fig. 2 is the structural representation of core layer of the present invention;

Fig. 3 is the schematic diagram of one of them metamaterial unit of core layer of the present invention;

Fig. 4 is the schematic diagram of man-made microstructure of the present invention;

Fig. 5 is the schematic diagram of another man-made microstructure of the present invention;

Fig. 6 is the structural representation of the satellite receiving system of an embodiment of the present invention;

Fig. 7 is another visual angle figure of Fig. 6.

Embodiment

As shown in Figure 1 to Figure 3, meta-material satellite antenna according to the present invention comprises the metamaterial flat 100 being arranged on signal transceiver 1 rear, described metamaterial flat 100 comprises core layer 10 and is arranged on the reflecting plate 200 of core layer rear surface, described core layer 10 comprises substrate 13 and is attached to multiple man-made microstructure 12 of substrate 13 front surface, described substrate 13 rear surface is attached with described reflecting plate 200, and the front surface of signal transceiver axis Z1 and metamaterial flat 100 has a non-vanishing angle theta.Signal transceiver is traditional corrugated horn in addition.

Reflecting plate 200 of the present invention adopts the conventional pure aluminum plate with smooth surface or fine copper plate etc., also metal coating directly can be coated on the effect that core surface realizes reflection electromagnetic wave.

In the present invention, the arbitrary longitudinal section of core layer of described metamaterial flat 100 is of similar shape and area, and longitudinal section herein refers to section vertical with the axis of metamaterial flat in metamaterial flat.The longitudinal section of the core layer of described metamaterial flat is square, circular or oval, preferably, the longitudinal section of the core layer of described metamaterial flat is that square, such core layer is easily processed, the square of such as 300X300mm or 450X450mm, the rectangle of 450X475mm.The circle of circle can be diameter be 250,300 or 450mm.The shape of reflecting plate is mated with core layer, and reflecting plate covers on a surface of core layer substantially completely.

In the present invention, described core layer 10 in the normal direction refractive index remains unchanged, as Fig. 1 and Fig. 2, with the front surface of core layer 10 for XY plane, with signal transceiver equivalent point X core layer front surface in the plane be projected as origin of coordinates O, set up the two-dimensional coordinate system of XOY, the refractive index of described core layer front surface any point (x, y) meets following formula:

$n_{(x,y)}=n_{\max }-\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\×\sin \mathrm{\γ}-(s+\mathrm{k\λ})}{D}---\left(1\right);$

s＝2z _ocosγ （2）；

$k=\mathrm{floor}\left\{\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\×\sin \mathrm{\γ}-2z_o\cos \mathrm{\γ}}{\mathrm{\λ}}\right\}---\left(3\right);$

$D=\frac{\mathrm{\λ}}{n_{\max }-n_{\min }}---\left(4\right);$

Fig. 1 is the cutaway view that metamaterial flat in the plane cutting satellite antenna of the present invention that forms of axis Z1 and the geostationary satellite that will communicate (being equivalent to a bit) of signal transceiver and signal transceiver two parts obtain, the cutaway view that the metamaterial flat also namely in the SOTM satellite antenna of plane cutting the present embodiment that forms of y-axis and signal transceiver axis Z1 and signal transceiver two parts obtain.Wherein, as shown in Figure 2, in order to substrate in clearly displaing core layer 13 and the relation of man-made microstructure 12, the layer at man-made microstructure 12 place represents with hatching, we are referred to as man-made microstructure layer 120, and namely man-made microstructure layer 120 is made up of all man-made microstructure that substrate adheres to.

Wherein, n _{(x, y)}represent the refractive index of core layer front surface any point (x, y);

Z _orepresent the vertical range of signal transceiver equivalent point X to core layer front surface; In fact the equivalent point X of signal transceiver is exactly the feedback point (point focused on occurs electromagnetic wave in signal transceiver) of satellite antenna of the present invention herein; The angle of signal transceiver axis Z1 and metamaterial flat front surface is θ, in the present embodiment, the equivalent point X of signal transceiver is on the Z1 of signal transceiver axis, putative signal transceiver bore mid point is ds to the distance of the equivalent point X of signal transceiver, ginseng (namely allowing signal transceiver scan optimum position) can be become by variation ds, θ these two, make convergence effect optimum;

Y _orepresent the y coordinate figure of the front surface edge of this core layer and the intersection point of y-axis positive direction.

When γ represents that signal transceiver is used as to launch, its electromagnetic wave launched after metamaterial flat, angle formed by the plane electromagnetic wave of outgoing and core layer normal direction, γ is not equal to zero, preferably 10 °≤γ≤80 °; Concrete angle is determined by many factors, the geographical position (longitude and latitude) residing for satellite antenna, the performance index (gain, minor level etc.) of satellite antenna.

N _maxrepresent the maximum of the refractive index of core layer;

N _minrepresent the minimum value of the refractive index of core layer;

λ represents that frequency is the electromagnetic wavelength of center of antenna frequency;

D is the thickness of core layer;

floor represents rounded down, for example, when <math> <mfrac> <mrow> <msqrt> <msup> <mi> x </ mi > <mn> 2 </ mn> </ msup> <mo> + </ mo> <msup> <mi> y </ mi> <mn> 2 </ mn> </ msup> <mo> + </ mo> <msup> <msub> <mi> z </ mi> <mi> o </ mi> </ msub> <mn> 2 </ mn> </ msup> </ msqrt> <mo> + </ mo> <mrow> <mo> (</ mo> <msub> <mi> y </ mi> <mi> o </ mi> </ msub> <mo> - </ mo> <mi> y </ mi> <mo>) </ mo> </ mrow> <mo> &amp; times; </ mo> <mi> sin </ mi> <mi> &amp; gamma; </ mi> <mo> - </ mo> <mn > 2 </ mn> <msub> <mi> z </ mi> <mi> o </ mi> </ msub> <mi> cos </ mi> <mi> &amp; gamma; </ mi> </ mrow> <mi> &amp; lambda; </ mi> </ mfrac> </ math> greater than or equal to 0 is less than 1, k take 0, when $\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\&times;\sin \mathrm{\&gamma;}-2z_o\cos \mathrm{\&gamma;}}{\mathrm{\&lambda;}}$ greater than equal to 1 less than 2, k takes 1, and so on.

By formula (1) to formula (4) determined metamaterial flat, the electromagnetic wave that signal transceiver can be made to send can being the form outgoing of the plane wave of γ angle with the normal direction of metamaterial flat after metamaterial flat; Equally, as shown in Figure 1, by formula (1) to formula (4) determined metamaterial flat, the plane wave that antenna can be made to receive (to be that the form of the plane wave of γ angle is incident with the normal direction of metamaterial flat) can converge at signal transceiver equivalent point X place after metamaterial flat.

In addition, in the present invention, preferably; described meta-material satellite antenna also comprises the diaphragm covered in man-made microstructure 12, and diaphragm hides man-made microstructure layer 120 completely, can protect like this to man-made microstructure; meanwhile, the mechanical performance of metamaterial flat can also be strengthened.In the present invention, described diaphragm can be PS plastics (polystyrene plastics), PET (poly terephthalic acid class plastics) or HIPS plastic (impact resistant polystyrene).

In the present invention, the thickness of described diaphragm is 0.1-2mm, and concrete thickness determines in conjunction with wave penetrate capability and mechanical performance, such as, can be 1mm.

In the present invention, preferably, the thickness of described core layer is 0.11-2.5mm, and wherein, the thickness of substrate is 0.1-2mm, and the thickness of multiple man-made microstructure is 0.01-0.5mm, and namely the thickness of man-made microstructure layer is 0.01-0.5mm.As a concrete example, the thickness of described core layer is 1.036mm, and wherein, the thickness of substrate is 1.018mm, and the thickness of multiple man-made microstructure is 0.018mm.

Meta-material satellite antenna of the present invention is when using as transmitting antenna, and namely signal transceiver is as radiation source, the effect of metamaterial flat be plane wave that signal transceiver is sent after metamaterial flat with the form outgoing of plane wave.

Meta-material satellite antenna of the present invention is when using as reception antenna, namely signal transceiver is as wave collecting device, and the effect of metamaterial flat is that the plane wave (incident with the direction in Fig. 1) that antenna can be made to receive can converge at signal transceiver equivalent point X place after metamaterial flat.

In the present invention, described man-made microstructure is the metal micro structure be made up of copper cash or silver-colored line, described metal micro structure by etching, plating, bore quarters, photoetching, electronics carve or ion quarter method adhere to respectively on the substrate.Described each man-made microstructure comprises many from the outside spiral extension of a central point and mutually disjoint helix.Preferably, described man-made microstructure is the metal micro structure shown in Fig. 4, by adopting this man-made microstructure, makes satellite antenna have the function of He Ne laser.

In the present invention, core layer can obtain by the following method, namely on any one surface of substrate, cover copper, then obtain multiple metal micro structure (shape of multiple metal micro structure and its arrangement on substrate are obtained by Computer Simulation in advance) by etching method.

Namely core layer, reflecting plate pressing one are obtained metamaterial flat of the present invention.

In the present invention, described substrate is obtained by ceramic material, macromolecular material, ferroelectric material, ferrite material or ferromagnetic material etc.Macromolecular material is available F4B composite material, FR-4 composite material, PS(polystyrene) etc.

Please refer to Fig. 4, is the first embodiment of man-made microstructure of the present invention.Described man-made microstructure comprises many identical spiral broken lines, and in the present embodiment, preferably four identical spiral broken lines, these four spiral broken lines form respectively to outer clock wise spirals bending extension from same central point.Every bar spiral broken line overlaps with adjoining spiral broken line after the angle of described central point rotating 360 degrees/4=90 °.Each bar spiral broken line of man-made microstructure described in figure is at the formation right angle, position of bending, and each bar spiral broken line extends respectively to outer clock wise spirals bending from the central point of corresponding metamaterial unit, outermost one section of straight line is parallel with four sides of described metamaterial unit respectively.Certainly, these spiral broken lines also can extend to form respectively to outer counter-clockwise helical bending from same central point.

Please refer to Fig. 5, is the second embodiment of man-made microstructure of the present invention.Described man-made microstructure comprises six identical helical curves, and these six helical curves bend extension from same central point respectively to outer clock wise spirals and form.Every bar helical curve after this central point rotating 360 degrees/6=60 ° with adjoining spiral curve co-insides.The same, these helical curves also can extend to form respectively to outer counter-clockwise helical is bending from same central point.

Visible, every from same central point outwards clockwise or the people that formed of counter-clockwise helical and one or more helix mutually disjoint are all protection scope of the present invention in micro-structural.

In the present invention, described core layer 11 can be divided into multiple metamaterial unit D as shown in Figure 3 of array arrangement, each metamaterial unit D comprises base board unit U and is attached to the man-made microstructure 12 on base board unit U, the length, width and height of usual metamaterial unit D are all not more than 1/5th wavelength, be preferably 1/10th wavelength, therefore, the size of metamaterial unit D can be determined according to the operating frequency of antenna.As shown in Figure 2, described man-made microstructure is attached to the SR surface of base board unit U.

Known refractive index wherein μ is relative permeability, and ε is relative dielectric constant, and μ and ε is collectively referred to as electromagnetic parameter.Experiment proves, when electromagnetic wave is by refractive index dielectric material heterogeneous, and can to the large direction deviation of refractive index.When relative permeability is certain (usually close to 1), refractive index is only relevant with dielectric constant, when substrate is selected, utilize the arbitrary value (within the specific limits) that only can realize metamaterial unit refractive index to the man-made microstructure of electric field response, under this center of antenna frequency, utilize simulation software, as CST, MATLAB, COMSOL etc., the situation that the dielectric constant being obtained the man-made microstructure of a certain given shape by emulation is changed along with the refractive index variable of topology, data one to one can be listed, the core layer 10 of the specific refractive index distribution that we need can be designed.

In the present invention, the structural design of core layer obtains by Computer Simulation (CST emulation), specific as follows:

(1) attaching substrates of metal micro structure is determined.Such as dielectric constant is the medium substrate of 2.7, and the material of medium substrate can be FR-4, F4b or PS.

(2) size of metamaterial unit is determined.The size of the size of metamaterial unit is obtained by the centre frequency of antenna, utilizes frequency to obtain its wavelength, then get be less than wavelength 1/5th a numerical value as the length CD of metamaterial unit D and width KD.Such as, corresponding to the centre frequency of 11.95G, described metamaterial unit D can be long CD as shown in Figure 2 and wide KD is 2.8mm, thickness HD is 1.036mm square platelet.

(3) material and the topological structure of metal micro structure is determined.In the present invention, the material of metal micro structure is copper, and the topological structure of metal micro structure is the structure shown in Fig. 4, and its live width W is consistent everywhere; .

In addition, present invention also offers a kind of satellite receiving system, comprise satellite antenna, signal transceiver 1, the tuner of connection signal transceiver 1 and the satellite receiver (not indicating in figure) that is connected by cable with tuner, described satellite antenna is the above-mentioned meta-material satellite antenna of the present invention, and described satellite antenna set is at the rear of signal transceiver 1.In the present invention, described signal transceiver 1 is traditional corrugated horn.Satellite receiver and tuner are also existing technology, no longer state herein.Herein, meta-material satellite antenna is used to satellite earth antenna, such as satellite television receiving antenna.

Described signal transceiver, can be such as the CL11R integral high frequency head of Tongzhou Electronics, incoming frequency be 11.7 ~ 12.2GHz, and output frequency is 950 ~ 1450MHz, can watch most of Ku band satellite TV.Satellite receiver, such as, can adopt the N6188 of Tongzhou Electronics, for receiving the satellite TV signal of No. 9, culminant star.

In addition, the metamaterial board support in Fig. 6 and Fig. 7 is an optimal way of metamaterial board support of the present invention, and it comprises framework 3 and the metamaterial flat angle regulating device of fixing metamaterial flat 100; Described reflecting plate adjusting device comprise the Connection Block 4 be fixedly connected with frame 3 and signal transceiver pole 2, the hinged seat 5 be fixed on Connection Block 4, with the rotating articulated joint 6 be connected of hinged seat 5 and the adjusting rod 7 removably connected with articulated joint 6.

In the present embodiment, described articulated joint 6 is placed in hinged seat 5, articulated joint 6 realizes rotating be connected by running through articulated joint with the first screw rod LG1 of hinged seat with hinged seat 5, the two ends of the first screw rod LG1 are provided with two screwed retaining ring LM1, the bilateral symmetry of hinged seat 5 is provided with the first sliding tray HC1 and the second sliding tray HC2, described reflecting plate adjusting device also comprises the second screw rod LG2 running through the first sliding tray HC1, articulated joint 6 and the second sliding tray HC2, and the two ends of the second screw rod LG2 are provided with two locking nut LM2.

In the present embodiment, described adjusting rod 7 is connected by locking device is dismountable with articulated joint 6, described adjusting rod 7 is round bar, described locking device comprises the latch SJB being close to the circular arc that adjusting rod 7 outer surface is arranged and the upper locking flange STY be oppositely arranged with latch SJB and lower locking flange XTY, the outward flange of described upper locking flange STY and lower locking flange XTY is arc-shaped, the outside of described upper locking flange STY and lower locking flange XTY is all close on the outer surface of adjusting rod 7, the both sides of latch SJB are threaded with articulated joint 6 by bolt LS3, the position that described upper locking flange STY and lower locking flange XTY contacts with adjusting rod 7 is arranged offers the equally distributed anti-slop serrations (not shown) of energy.

In the present embodiment, described antenna mounting seat also comprise be connected to adjusting rod 7 other end meet wallboard QB, described in meet strong plate QB and can be fixed to (as wall in the south) on the metope in house, be such as fixed on metope by plain screw or tapping screw.

In the present embodiment, described framework 3 comprises upper side frame 31, middle frame 32 and lower frame 33, described upper side frame 31, middle frame 32 and lower frame 33 are fixed on the back side of metamaterial flat 100 respectively by bolt LS4, and described upper side frame 31, middle frame 32 and lower frame 33 are fixed on feed pole 2 respectively by upper holder SJ, Connection Block 4 and lower fixed frame XJ.

In the present embodiment, a side of described hinged seat 5 is also provided with angle dial KD, so that the adjustment reading at the reflecting plate elevation angle, namely the elevation angle can directly read out from scale, the Installation and Debugging of convenient antenna.

The azimuth adjustment of metamaterial flat 100 is specific as follows:

First, looser a bolt LS3, then articulated joint 6 relieves locking, can relative adjustment bar 7 freely movable (adjusting rod 7 is fixed on metope); Turn to correct position, namely the azimuth of antenna is also debugged complete, and tight a bolt LS3 again, then reflecting plate is by towards selected communication satellite, completes azimuthal adjustment.

After azimuth is adjusted, just the elevation angle can be regulated.

The elevation angle of metamaterial flat 100 regulates specific as follows:

First, namely outside locking nut LM2(removes the angle locking of reflecting plate);

Rotate metamaterial flat 100(clockwise or counterclockwise), now metamaterial flat 100 can be rotated around the first screw rod LG1, until appropriate location, inwardly namely rotational lock nut LM2(locks the angle of reflecting plate again), appropriate location herein refers to, the satellite that the elevation angle of reflecting plate just equals to communicate is at the elevation angle (this angle directly can read on angle dial KD) in this geographical position, and the elevation angle namely reaching reflecting plate regulates, and the elevation angle namely achieving antenna regulates.

Antenna azimuth and the elevation angle be adjusted to the conventional antenna debugging method in this area, the present invention no longer describes in detail.

By reference to the accompanying drawings embodiments of the invention are described above; but the present invention is not limited to above-mentioned embodiment; above-mentioned embodiment is only schematic; instead of it is restrictive; those of ordinary skill in the art is under enlightenment of the present invention; do not departing under the ambit that present inventive concept and claim protect, also can make a lot of form, these all belong within protection of the present invention.

Claims (10)

1. a meta-material satellite antenna, it is characterized in that, described meta-material satellite antenna comprises the metamaterial flat being arranged on signal transceiver rear and antenna mounting seat metamaterial flat be fixedly mounted on metope, described metamaterial flat comprises core layer and is arranged on the reflecting plate of core layer rear surface, described core layer comprises substrate and is attached to multiple man-made microstructure of substrate front surface, described substrate rear surface is attached with described reflecting plate, and described each man-made microstructure comprises many from the outside spiral extension of a central point and mutually disjoint helix; Described core layer refractive index in the normal direction of its lamella place plane remains unchanged, with the front surface of core layer for XY plane, with signal transceiver equivalent point core layer front surface in the plane be projected as origin of coordinates O, set up the two-dimensional coordinate system of XOY, the refractive index of described core layer front surface any point (x, y) meets following formula:

$n_{(x,y)}=n_{\max }-\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\&times;\sin \mathrm{\&gamma;}-(s+\mathrm{k\&gamma;})}{D};$

s＝2z _ocosγ；

$k=\mathrm{floor}\left\{\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\&times;\sin \mathrm{\&gamma;}-2z_o\cos \mathrm{\&gamma;}}{\mathrm{\&lambda;}}\right\};$

$D=\frac{\mathrm{\&lambda;}}{2(n_{\max }-n_{\min })};$

Wherein, n _{(x, y)}represent the refractive index of core layer front surface any point (x, y);

Z _orepresent the vertical range of signal transceiver equivalent point to core layer front surface;

Y _orepresent the y coordinate figure of the front surface edge of this core layer and the intersection point of y-axis positive direction;

When γ represents that signal transceiver is used as to launch, its electromagnetic wave launched after metamaterial flat, angle formed by the plane electromagnetic wave of outgoing and core layer normal direction, γ is not equal to zero;

N _maxrepresent the maximum of the refractive index of core layer;

N _minrepresent the minimum value of the refractive index of core layer;

λ represents the electromagnetic wavelength corresponding to the centre frequency of meta-material satellite antenna;

D is the thickness of core layer;

Floor represents and rounds downwards.

2. meta-material satellite antenna according to claim 1, is characterized in that, each bar helix of described each man-made microstructure is outwards clockwise or counter-clockwise helical from described central point.

3. meta-material satellite antenna according to claim 1, is characterized in that, described each man-made microstructure comprises many spiral broken lines.

4. meta-material satellite antenna according to claim 3, is characterized in that, described each bar spiral broken line is at the formation right angle, position of bending.

5. meta-material satellite antenna according to claim 1, is characterized in that, described helix is metal wire.

6. meta-material satellite antenna according to claim 1; it is characterized in that; described meta-material satellite antenna also comprises the diaphragm covered in man-made microstructure, and described diaphragm is PS plastics, PET or HIPS plastic, and the thickness of described diaphragm is 0.1-2mm.

7. meta-material satellite antenna according to claim 1, is characterized in that, the thickness of described core layer is 0.11-2.5mm, and wherein, the thickness of substrate is 0.1-2mm, and the thickness of multiple man-made microstructure is 0.01-0.5mm.

8. meta-material satellite antenna according to claim 7, is characterized in that, the thickness of described core layer is 1.036mm, and wherein, the thickness of substrate is 1.018mm, and the thickness of multiple man-made microstructure is 0.018mm.

9. meta-material satellite antenna according to claim 1, it is characterized in that, described man-made microstructure is the metal micro structure be made up of copper cash or silver-colored line, described metal micro structure by etching, plating, bore quarters, photoetching, electronics carve or ion carve method adhere on the substrate.

10. a satellite receiving system, comprises satellite antenna, signal transceiver, satellite receiver, it is characterized in that, described satellite antenna is the meta-material satellite antenna described in claim 1 to 9 any one, and described satellite antenna set is at the rear of signal transceiver.