CN102709674B - 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 arranged behind a feed source, wherein the meta-material flat plate comprises a core layer and a reflection plate arranged on the rear surface of the core layer; the reflection plate is a grid-shaped reflection plate and comprises a plurality of metal sheets which are arranged at intervals and have the same gaps; 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 feed source pass through the meta-material flat plate, an included angle formed between emitted plane electromagnetic waves and the normal line direction of the core layer is not equal to zero and the plane electromagnetic waves are emitted in the normal line direction of the core layer corresponding to the electromagnetic waves, so that the minor lobe level of the satellite antenna can be effectively reduced; the sheet-shaped meta-material flat plate is used for replacing a traditional paraboloid antenna so that the manufacturing and the machining are easier and the cost is lower; and the whole thickness of the meta-material flat plate is in a millimeter grade and is very light and thin.. 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 feed 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 feed.Usually, the feed that parabolic antenna is corresponding is a horn antenna.

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 meta-material satellite antenna that is simple, low cost of manufacture.

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 feed 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, described reflecting plate is latticed reflecting plate, it comprises the sheet metal that multi-disc is separated by identical gap, described core layer in the normal direction refractive index remains unchanged, with the front surface of core layer for XY plane, with feed 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, described core layer front surface any point (x, y) refractive index 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 feed 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 feed 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, 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.

Further, described metal micro structure is plane flakes, described metal micro structure has the first metal wire and the second metal wire mutually vertically divided equally, described first metal wire is identical with the length of the second metal wire, described first metal wire two ends are connected with two the first metal branch of equal length, described first metal wire two ends are connected on the mid point of two the first metal branch, described second metal wire two ends are connected with two the second metal branch of equal length, described second metal wire two ends are connected on the mid point of two the second metal branch, described first metal branch is equal with the length of the second metal branch.

Further, each first metal branch of the alabastrine metal micro structure of described plane and the two ends of each second metal branch are also connected with identical 3rd metal branch, and the mid point of corresponding 3rd metal branch is connected with the end points of the first metal branch and the second metal branch respectively.

Further, first metal wire of the alabastrine metal micro structure of described plane and the second metal wire are provided with two kinks, and the alabastrine metal micro structure of described plane all overlaps with former figure to the figure of any direction 90-degree rotation with the intersection point of the second metal wire around the first metal wire in plane residing for metal micro structure.

According to meta-material satellite antenna of the present invention, by the refraction index profile of careful design core layer, the electromagnetic wave that feed 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 feed 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, feed, the tuner of connection feed 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 feed.

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 the alabastrine metal micro structure of plane of the present invention;

Fig. 5 is a kind of derived structure of the alabastrine metal micro structure of plane shown in Fig. 4;

Fig. 6 is a kind of distressed structure of the alabastrine metal micro structure of plane shown in Fig. 4.

Fig. 7 is the first stage of the differentiation of the topology of the alabastrine metal micro structure of plane;

Fig. 8 is the second stage of the differentiation of the topology of the alabastrine metal micro structure of plane;

Fig. 9 is the structural representation of the satellite receiving system of an embodiment of the present invention;

Figure 10 is the floor map of square core layer of the present invention;

Figure 11 is the floor map of the core layer of circle of the present invention;

Figure 12 is another visual angle figure of Fig. 9;

Figure 13 is the structural representation of latticed reflecting plate.

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 feed 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 feed axis Z1 and metamaterial flat 100 has a non-vanishing angle theta.Feed is traditional corrugated horn in addition.

Reflecting plate 200 of the present invention does not adopt the conventional pure aluminum plate with smooth surface or fine copper plate etc., metal coating directly neither be coated on the effect that core surface realizes reflection electromagnetic wave.The present invention adopts latticed reflecting plate 200, and its structure chart as shown in figure 13.

When adopt have the fine copper plate of smooth surface or pure aluminum plate etc. prepare reflecting plate time, due to its thinner thickness, be generally 0.01 millimeter to 0.03 millimeter, its thickness relatively, its length and width are longer, when Synthesis and applications easily because the effect generation warpage of stress, reduce the yield in product preparation process on the one hand, cause a large amount of waste, also increase the maintenance cost after product use on the other hand.When after the latticed reflecting plate 200 of employing, its sheet metal 2000 being separated by identical gap by multi-disc is formed, and the length and width value of each sheet metal 2000 and the difference of one-tenth-value thickness 1/10 reduce, thus the stress of product can not by each sheet metal 2000 warpage.But owing to there is gap 2001 between each sheet metal 2000, if the wide meeting of the width in gap 2001 makes electromagnetic wave be produced graing lobe effect by latticed reflecting plate 200 reflex time, impact is brought to antenna performance, if the width in gap 2001 is narrow, the length and width value of each sheet metal 2000 and the difference of one-tenth-value thickness 1/10 can be made to increase, be unfavorable for the release of stress.

In the latticed reflecting plate of the present invention 200, each sheet metal 2000 is identical square-shaped metal sheet, and its length of side is 18-20mm; Gap between adjacent metal sheet 2000 is 0.13-0.18mm; The thickness of sheet metal 2000 is 0.01-0.5mm.In above-mentioned span, reflecting plate 200 1 aspect because of the excessive generation causing its border warping phenomenon of stress, also effectively can not avoid the generation of graing lobe effect, can strengthen antenna performance on the other hand, improves the yield in antenna preparation process.

In one embodiment of the invention, each sheet metal 2000 of described reflecting plate for the length of side be the square-shaped metal sheet of 19mm, the gap of adjacent metal sheet 2000 is 0.15mm, and the thickness of sheet metal 2000 is 0.018mm.

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, the effect of impedance matching layer be realize from air to core layer 10 impedance matching, to reduce the reflection of electromagnetic wave of air and Meta Materials joint, the loss of reduction electromagnetic wave energy.

In the present invention, described core layer 10 in the normal direction refractive index remains unchanged, as shown in Figure 1, Figure 2, shown in Figure 10 and Figure 11, with the front surface of core layer 10 for XY plane, with feed 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)；

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

$D=\frac{\mathrm{\λ}}{2(n_{\max }-n_{\min })}---\left(4\right);$

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 feed and feed 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 feed axis Z1 and feed 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 feed equivalent point X to core layer front surface; In fact the equivalent point X of feed is exactly the feedback point (point focused on occurs electromagnetic wave in feed) of satellite antenna of the present invention herein; The angle of feed axis Z1 and metamaterial flat front surface is θ, in the present embodiment, the equivalent point X of feed is on the Z1 of feed axis, assuming that feed bore mid point is ds to the distance of the equivalent point X of feed, ginseng (namely allowing feed 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; Such as, as shown in Figure 9, when core layer is square, it represents that square core layer goes up along the y value of mid point in XOY coordinate most, the line segment OA namely in figure.When core layer is circular or oval, as shown in Figure 10, core layer is circular, y _ofor the peak A of circumference and the line OA of initial point O.Certain core layer can also have other shape, and only needs to intercept a shape arbitrarily in the core layer shown in Fig. 9 or Figure 10.

When γ represents that feed 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 and rounds downwards, such as, when $\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\×\sin \mathrm{\γ}-{2z}_o\cos \mathrm{\γ}}{\mathrm{\λ}}$ Be more than or equal to 0 when being less than 1, k gets 0, when $\frac{\sqrt{x^2+y^2+{z_o}^2}+(y_o-y)\×\sin \mathrm{\γ}-{2z}_o\cos \mathrm{\γ}}{\mathrm{\λ}}$ Be more than or equal to 1 when being less than 2, k gets 1, and the rest may be inferred.

By formula (1) to formula (4) determined metamaterial flat, the electromagnetic wave that feed 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 feed 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 feed is as radiation source, the effect of metamaterial flat be plane wave that feed 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 feed 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 feed 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.Preferably, described man-made microstructure to develop the metal micro structure of the multiple different topology obtained for the alabastrine metal micro structure of the plane shown in Fig. 4 by topology.

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.

Figure 4 shows that the schematic diagram of the alabastrine metal micro structure of plane, described alabastrine metal micro structure has the first metal wire J1 and the second metal wire J2 that mutually vertically divide equally, described first metal wire J1 is identical with the length of the second metal wire J2, described first metal wire J1 two ends are connected with two the first metal branch F1 of equal length, described first metal wire J1 two ends are connected on the mid point of two the first metal branch F1, described second metal wire J2 two ends are connected with two the second metal branch F2 of equal length, described second metal wire J2 two ends are connected on the mid point of two the second metal branch F2, described first metal branch F1 is equal with the length of the second metal branch F2.

Fig. 5 is a kind of derived structure of the alabastrine metal micro structure of plane shown in Fig. 4.It is all connected with identical 3rd metal branch F3 at the two ends of each first metal branch F1 and each second metal branch F2, and the mid point of corresponding 3rd metal branch F3 is connected with the end points of the first metal branch F1 and the second metal branch F2 respectively.The rest may be inferred, and the present invention can also derive the metal micro structure of other form.

Fig. 6 is a kind of distressed structure of the alabastrine metal micro structure of plane shown in Fig. 4, the metal micro structure of this kind of structure, first metal wire J1 and the second metal wire J2 is not straight line, but folding line, first metal wire J1 and the second metal wire J2 is provided with two kink WZ, but the first metal wire J1 remains vertical with the second metal wire J2 to be divided equally, by arrange kink towards with the relative position of kink on the first metal wire and the second metal wire, metal micro structure shown in Fig. 7 is all overlapped with former figure to the figure of any direction 90-degree rotation around the axis perpendicular to the first metal wire and the second metal wire intersection point.In addition, other can also be had to be out of shape, such as, the first metal wire J1 and the second metal wire J2 all arranges multiple kink WZ.

In the present invention, described core layer 11 can be divided into multiple metamaterial unit D as shown in Figure 2 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.Preferably, point (the x mentioned herein and in formula (1), y) coordinate that the central point on its SR surface of metamaterial unit D is residing in XOY two-dimensional coordinate the is referred to, each metamaterial unit D has an equivalent refractive index value, therefore (x, y) be not continuous print strictly speaking, the variations in refractive index of core layer is approximate continuous.It the collective entity that in core layer, (x, y) puts is the set of the central point on its SR surface of all metamaterial unit D.Therefore, core layer refractive index in the normal direction remains unchanged.

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 (the alabastrine metal micro structure of plane as shown in Figure 4) 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 alabastrine metal micro structure of the plane shown in Fig. 4, and its live width W is consistent everywhere; Topological structure herein, refers to the basic configuration that topology develops.

(4) the topology parameter of metal micro structure is determined.As shown in Figure 4, in the present invention, the topology parameter of the alabastrine metal micro structure of plane comprises the live width W of metal micro structure, the length a of the first metal wire J1, the length b of the first metal branch F1.

(5) the differentiation restrictive condition of the topology of metal micro structure is determined.In the present invention, the differentiation restrictive condition of the topology of metal micro structure has, the minimum spacing WL (namely as shown in Figure 4, the long limit of metal micro structure and metamaterial unit or the distance of broadside are WL/2) between metal micro structure, the live width W of metal micro structure, the size of metamaterial unit; Due to processing technology restriction, WL is more than or equal to 0.1mm, and equally, live width W is greater than to equal 0.1mm.First time, when emulating, WL can get 0.1mm, and W can get 0.3mm, and it is 2.8mm that metamaterial unit is of a size of long and wide, and thickness is 1.018mm, and now the topology parameter of metal micro structure only has a and b Two Variables.The topology of metal micro structure, by the differentiation mode as shown in Fig. 7 to Fig. 8, corresponding to a certain characteristic frequency (such as 11.95GHZ), can obtain a continuous print variations in refractive index scope.

Particularly, the differentiation of the topology of described metal micro structure comprises two stages (basic configuration that topology develops is the metal micro structure shown in Fig. 4):

First stage: according to differentiation restrictive condition, when b value remains unchanged, a value is changed to maximum from minimum value, the metal micro structure in this evolution process is " ten " font when minimum value (a get except).In the present embodiment, the minimum value of a is 0.3mm (live width W), and the maximum of a is (CD-WL).Therefore, in the first phase, the differentiation of the topology of metal micro structure as shown in Figure 7, is namely the square JX1 of W from the length of side, develops into maximum " ten " font topology JD1 gradually.In the first phase, along with the differentiation of the topology of metal micro structure, the refractive index of the metamaterial unit corresponding with it increases (respective antenna one characteristic frequency) continuously.

Second stage: according to differentiation restrictive condition, when a is increased to maximum, a remains unchanged; Now, b is increased continuously maximum from minimum value, the metal micro structure in this evolution process is plane flakes.In the present embodiment, the minimum value of b is 0.3mm, and the maximum of b is (CD-WL-2W).Therefore, in second stage, the differentiation of the topology of metal micro structure as shown in Figure 8, namely from maximum " ten " font topology JD1, develop into the alabastrine topology JD2 of maximum plane gradually, the alabastrine topology JD2 of maximum plane herein refers to, the length b of the first metal branch J1 and the second metal branch J2 can not extend again, otherwise the first metal branch is crossing by generation with the second metal branch.In second stage, along with the differentiation of the topology of metal micro structure, the refractive index of the metamaterial unit corresponding with it increases (respective antenna one characteristic frequency) continuously.

If the variations in refractive index scope being obtained metamaterial unit by above-mentioned differentiation contains n _minto n _maxconsecutive variations scope, then meet design needs.If the variations in refractive index scope that above-mentioned differentiation obtains metamaterial unit does not meet design needs, such as maximum is too little or minimum value is excessive, then change WL and W, again emulate, until obtain the variations in refractive index scope of our needs.

According to formula (1) to (4), a series of metamaterial unit emulation obtained, according to after the refractive index arrangement of its correspondence (being in fact exactly the arrangement of multiple man-made microstructure on substrate of different topology shape), can obtain core layer of the present invention.

Described meta-material satellite antenna described above is different according to working frequency range and environment for use, can be satellite television receiving antenna, satellite communication antena (two-way communication), microwave antenna or radar antenna.Certainly, described meta-material satellite antenna of the present invention can also substitute other various reflector antenna.

In addition, as shown in Fig. 9 and Figure 12, present invention also offers a kind of satellite receiving system, comprise satellite antenna, feed 1, the tuner connecting feed 1 and the satellite receiver (not indicating in figure) be 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 feed 1.In the present invention, described feed 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 feed, 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, in the present invention, as shown in Fig. 9 and Figure 12, satellite receiving system also comprises antenna mounting seat, described antenna mounting seat comprises feed pole 2, the framework 3 of fixing metamaterial flat 100 and antenna elevation angle adjusting device, one end of described feed pole 2 is fixedly connected with feed 1, the other end is fixing on the frame 3, described antenna elevation angle adjusting device comprises by the first hinge JL1 and the hinged base 4 of feed pole 2 and the supporting mechanism for metamaterial flat 100 being fixed on particular elevation, described supporting mechanism comprises by the second hinge JL2 and the hinged hollow stem 5 of base 4, be placed in the interior bar 6 of hollow stem 5 and the locking device of interior bar 6 position of locking, the outer end of described interior bar 6 is fixedly connected with feed source bracket 2 by connecting plate 7, can slide by opposite hollow bar 5 when described interior bar 6 is under locking device is in unlocked state, described first hinge JL1 and the second hinge JL2 divides and is located on two relative positions of base 4.

In the present embodiment, described base 4 is circular frame structure, and the line of described first hinge JL1 and the second hinge JL2 crosses the center of circle of circular frame structure.Base is also provided with multiple fixed head GD, behind the good azimuth of tested rotating platform and the elevation angle, entire physical is fixed on the ground.

In the present embodiment, described locking device comprises the screwed hole (not shown) be arranged in hollow stem 5 and the adjusting bolt 8 coordinated with screwed hole, described adjusting bolt 8 to support on the lateral wall of interior bar 6 bar 6 position in locking by inwardly rotating, because interior bar 6 connects on the frame 3 by connecting plate 7, therefore, indeed achieve the pitch regulation of metamaterial flat 100, i.e. the adjustment at the elevation angle of antenna.

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 reflecting plate 100 respectively by bolt LS1, described upper side frame 31, middle frame 32 and lower frame 33 are fixed on feed pole 2 by three fixed mounts 9, and described connecting plate 7 is fixedly connected with in the position near middle frame 32 with feed pole 2.

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

First, to inner rotary adjusting bolt 8 (namely removing the locking position of interior bar);

Bar (stretching out or retraction) in sliding, now reflecting plate 100 can rotate around the first hinge JL1, until appropriate location, again inwardly rotate adjusting bolt 8 (i.e. the position of the interior bar of locking), appropriate location herein refers to, the satellite that the elevation angle of metamaterial flat just equals to communicate is at the elevation angle in this geographical position, and the elevation angle namely reaching metamaterial flat regulates, and the elevation angle namely achieving antenna regulates.

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 (11)

1. a meta-material satellite antenna, it is characterized in that, described meta-material satellite antenna comprises the metamaterial flat being arranged on feed 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, described reflecting plate is latticed reflecting plate, it comprises the sheet metal that multi-disc is separated by identical gap, described core layer in the normal direction refractive index remains unchanged, with the front surface of core layer for XY plane, with feed 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, described core layer front surface any point (x, y) refractive index 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；

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

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

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

Z _orepresent the vertical range of feed 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 feed 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; 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.

3. 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.

4. meta-material satellite antenna according to claim 3, 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.

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

6. meta-material satellite antenna according to claim 5, is characterized in that, 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.

7. 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.

8. meta-material satellite antenna according to claim 7, it is characterized in that, described metal micro structure is plane flakes, described metal micro structure has the first metal wire and the second metal wire mutually vertically divided equally, described first metal wire is identical with the length of the second metal wire, described first metal wire two ends are connected with two the first metal branch of equal length, described first metal wire two ends are connected on the mid point of two the first metal branch, described second metal wire two ends are connected with two the second metal branch of equal length, described second metal wire two ends are connected on the mid point of two the second metal branch, described first metal branch is equal with the length of the second metal branch.

9. meta-material satellite antenna according to claim 8, it is characterized in that, each first metal branch of the alabastrine metal micro structure of described plane and the two ends of each second metal branch are also connected with identical 3rd metal branch, and the mid point of corresponding 3rd metal branch is connected with the end points of the first metal branch and the second metal branch respectively.

10. meta-material satellite antenna according to claim 8, it is characterized in that, first metal wire of the alabastrine metal micro structure of described plane and the second metal wire are provided with two kinks, and the alabastrine metal micro structure of described plane all overlaps with former figure to the figure of any direction 90-degree rotation with the intersection point of the second metal wire around the first metal wire in plane residing for metal micro structure.

11. 1 kinds of satellite receiving systems, comprise satellite antenna, feed, the tuner of connection feed and the satellite receiver that is connected with tuner, it is characterized in that, described satellite antenna is the meta-material satellite antenna described in claim 1 to 10 any one, and described satellite antenna set is at the rear of feed.