CN105470653A - Design method for continuous phase correction reflector antenna in limited space - Google Patents

Design method for continuous phase correction reflector antenna in limited space Download PDF

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Publication number
CN105470653A
CN105470653A CN201510932475.9A CN201510932475A CN105470653A CN 105470653 A CN105470653 A CN 105470653A CN 201510932475 A CN201510932475 A CN 201510932475A CN 105470653 A CN105470653 A CN 105470653A
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interarea
axis
continuous phase
center
coordinate
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CN201510932475.9A
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CN105470653B (en
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徐刚
余川
常超
孟凡宝
施美友
宋志敏
屈劲
李才阳
陈世韬
卢朝政
鲜海鹏
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Northwest Institute of Nuclear Technology
Institute of Applied Electronics of CAEP
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Northwest Institute of Nuclear Technology
Institute of Applied Electronics of CAEP
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/148—Reflecting surfaces; Equivalent structures with means for varying the reflecting properties

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

The invention discloses a design method for a continuous phase correction reflector antenna in a limited space. The method is used for constructing a novel continuous phase correction reflector antenna in a limited space having a certain thickness and conformal with the surface of a system carrier to solve the difficult problem in designing a high-gain reflector antenna in a given limited space at present, and can be widely applied to the conformal reflector antenna design in the fields of high-power microwaves, radars, high-power millimeter waves and the like.

Description

A kind of method for designing of confinement space continuous phase correction reflecting antenna
Technical field
The present invention relates to microwave antenna art field, specifically refer to a kind of method for designing of confinement space continuous phase correction reflecting antenna.
Background technology
Along with developing rapidly of High-Power Microwave and high-power Millimeter Wave Applications, the gain requirement of people to radiating antenna is more and more higher, array antenna because of its feeder line merit divide loss with Antenna aperture electricity size increase and raise rapidly, the radiation efficiency of antenna system is declined to a great extent, therefore, reflector antenna because of its feed structure simple, the features such as loss is little, obtain increasing application at High-Power Microwave and high-power millimeter-wave technology field.
At some application scenarios, people wish that the profile of antenna can conformal with carrier surface (comprising curved surface or plane), and section will unexpectedly may be low, traditional parabolic reflective surface antenna can not meet this type of emerging demand, therefore a kind of novel reflector antenna is needed, its profile in the given certain thickness restricted area space conformal with carrier surface, and has the gain suitable with traditional reflective surface antenna.
Summary of the invention
The object of this invention is to provide a kind of method for designing of confinement space continuous phase correction reflecting antenna, for with the conformal certain thickness confined space on systemic vectors surface in construct novel continuous phase correction reflecting antenna, solve the difficult problem designing high-gain reflector antenna at present in given confinement space, the conformal reflector antenna design in the fields such as High-Power Microwave, radar and high-power millimeter wave can be widely used in.
For achieving the above object, the present invention adopts following technical scheme:
A method for designing for confinement space continuous phase correction reflecting antenna, comprises the following steps:
Step one: the phase center of Feed Horn is set to coordinate origin O, the beam axis of Feed Horn is coordinate system Z axis, and the axis perpendicular to Z axis is X-axis, and the axle perpendicular to Z, X-axis face is Y-axis;
Step 2: find a point as interarea central point (x at the interface, top of confinement c, z c), this point meets the center that its subpoint on actinal surface is positioned at actinal surface, and radiation beam and Z axis angle are α, simultaneously the some position at given subreflector center;
Step 3: build secondary coordinate system, initial point is identical with cylindrical coordinate, Z ' axle and aerial radiation beam parallel are α, X with the angle of cylindrical coordinate ' parallel with actinal surface.
Step 4: determine interarea central point (x c, z c) after, calculate from feed center to subreflector center, then to interarea center, then arrive total wave-path L of aperture centre o;
Step 5: in given confinement space, from interarea center, outside pointwise solves and meets light path L=L ointerarea on point coordinates, solution formula is by a series of geometrical relationship process and mathematical derivation, and the axial coordinate that can obtain interarea is put is:
z f m = ( x f m - x f s ) 2 + ( y f m - y f s ) 2 - ( L 0 - ρ s ) 2 + z f s 2 2 ( L 0 - ρ s + z f s )
Wherein: (x f*, y f*, z f*) for interarea or minor face be the coordinate in the secondary coordinate system of Descartes of α at the angle of pitch, L 0for total optical path, ρ sfor the pole span of subreflector in spherical coordinates.
Step 6: the some cloud completing interarea and minor face solves, preserves the face type data of interarea and minor face
In technique scheme, state in step 3, construct a secondary coordinate system parallel with radiation beam, it is characterized by initial point identical with cylindrical coordinate, Z ' axle and aerial radiation beam parallel, is α, X with the angle of cylindrical coordinate ' parallel with the actinal surface tilted.
In technique scheme, in described step 5, the solution formula of the interarea face type in secondary coordinate system that tilts:
z f m = ( x f m - x f s ) 2 + ( y f m - y f s ) 2 - ( L 0 - ρ s ) 2 + z f s 2 2 ( L 0 - ρ s + z f s ) ,
Wherein: (x f*, y f*, z f*) for interarea or minor face be the coordinate in the secondary coordinate system of Descartes of α at the angle of pitch, L 0for total optical path, ρ sfor the pole span of subreflector in spherical coordinates.
In technique scheme, in described step 5 when solving the interarea point obtained and being positioned at outside confinement space, perform a total optical path correction, total optical path is updated to L 0=L 0proceed to solve after+n λ, in formula, λ is wavelength corresponding to operating frequency, and n is integer.
In technique scheme, the choosing of n should make again to solve the interarea point obtained and be positioned at confinement space, and as far as possible close to interface, top.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows: can in given special confined space design reflectivity surface antenna, produce the directional beam suitable with the Shaped reflector gain in traditional free space, the fields such as High-Power Microwave emission system, radar and high-power millimeter wave emission system can be widely used in.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the design geometric representation of FZP reflecting surface;
Fig. 2 is design example face type figure
Wherein: 1 is subreflector, 2 is the primary reflection surfaces that will design, and 3 is given confinement spaces, and 4 is Antenna apertures, and 5 is Feed Horns, and 6 is interarea face type, and 7 is minor face face type.
Embodiment
The invention provides a kind of method for designing of confinement space continuous phase correction reflecting antenna, its design principle mainly:
Traditional reflector antenna utilizes aplanatism principle, make microwave radiation from the phase heart, through the reflection of subreflector and primary reflection surface, the light path reached on actinal surface is consistent, the electric field phase distribution on actinal surface can be made consistent, thus realize electromagnetic high-gain radiation.For the High-Power Microwave working in single-frequency point and high-power millimeter wave antenna, do not need to be strict with aplanatism, path length difference only between the quasi-optical ray of need is the integral multiple of operating frequency corresponding wavelength, also can realize the entirety of electric field phase on Antenna aperture consistent.
Method for designing of the present invention is in design geometric representation (as shown in Figure 1), comprises given confinement space, the primary reflection surface that will design in confinement space, subreflector, for Antenna aperture be Feed Horn.
Design process and step are:
(1) phase center of Feed Horn 5 is set to coordinate origin O, the beam axis of Feed Horn is coordinate system Z axis, and being X-axis perpendicular to the axis of Z axis in paper, is Y-axis perpendicular to the axle that paper is outside;
(2) find a point as interarea central point (x at the interface, top of confinement c, z c), this point meets the center that its subpoint on actinal surface 4 is positioned at actinal surface, and radiation beam and Z axis angle are α, simultaneously the some position at given subreflector center;
(3) build secondary coordinate system, initial point is identical with cylindrical coordinate, Z ' axle and aerial radiation beam parallel, is α, X with the angle of cylindrical coordinate ' parallel with actinal surface.
(4) interarea central point (x is determined c, z c) after, calculate from feed center to subreflector center, then to interarea center, then arrive total wave-path L of aperture centre o;
(5) in given confinement space, from interarea center, outside pointwise solves and meets light path L=L ointerarea on point coordinates, solution formula is by a series of geometrical relationship process and mathematical derivation, and the axial coordinate that can obtain interarea is put is:
z f m = ( x f m - x f s ) 2 + ( y f m - y f s ) 2 - ( L 0 - ρ s ) 2 + z f s 2 2 ( L 0 - ρ s + z f s ) - - - ( 1 )
Wherein: (x f*, y f*, z f*) for interarea or minor face be the coordinate in the secondary coordinate system of Descartes of α at the angle of pitch, L 0for total optical path, ρ sfor the pole span of subreflector in spherical coordinates.When solving the interarea point obtained and being positioned at outside confinement space, perform a total optical path correction, total optical path is updated to L 0=L 0proceed to solve after+n λ, in formula, λ is wavelength corresponding to operating frequency, and n is integer, and the choosing of n should make again to solve the interarea point obtained and be positioned at confinement space, and as far as possible close to interface, top, this can make the piecemeal step number of whole interarea the least possible.
(6) the some cloud completing interarea and minor face solves, and preserves the face type data of interarea and minor face.
In described step 3, construct a secondary coordinate system parallel with radiation beam, initial point is identical with cylindrical coordinate, Z ' axle and aerial radiation beam parallel, is α, X with the angle of cylindrical coordinate ' parallel with the actinal surface tilted.
In described step 5, the solution formula of the interarea face type in secondary coordinate system that tilts:
z f m = ( x f m - x f s ) 2 + ( y f m - y f s ) 2 - ( L 0 - ρ s ) 2 + z f s 2 2 ( L 0 - ρ s + z f s ) ,
Wherein: (x f*, y f*, z f*) for interarea or minor face be the coordinate in the secondary coordinate system of Descartes of α at the angle of pitch, L 0for total optical path, ρ sfor the pole span of subreflector in spherical coordinates.
In described step 5, when solving the interarea point obtained and being positioned at outside confinement space, perform once to the correction of total optical path, total optical path is updated to L 0=L 0the choosing of+n λ, n should make again to solve the interarea point obtained and be positioned at confinement space, and as far as possible close to interface, top.
By above-mentioned method for designing, in the flat space that given thickness is 5mm, devise the continuous phase correction reflector antenna of a W-waveband, its technical parameter is:
● operating frequency f:95GHz;
● actinal surface dimension D a: 660mm;
● radiation beam angle [alpha]: 0 °;
● minor face distance feed: 600mm
● actinal surface amplitude distribution: E ( r ) = 1 - 0.99 ( 2 r D a ) 12
As shown in Figure 2, wherein 6 is interarea face type to the face type that design obtains, and 7 is minor face face type, and visible interarea is completely in given flat confined space.
The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.

Claims (5)

1. a method for designing for confinement space continuous phase correction reflecting antenna, is characterized in that comprising the following steps:
Step one: the phase center of Feed Horn is set to coordinate origin O, the beam axis of Feed Horn is coordinate system Z axis, and the axis perpendicular to Z axis is X-axis, and the axle perpendicular to Z, X-axis face is Y-axis;
Step 2: find a point as interarea central point (x at the interface, top of confinement c, z c), this point meets the center that its subpoint on actinal surface is positioned at actinal surface, and radiation beam and Z axis angle are α, simultaneously the some position at given subreflector center;
Step 3: build secondary coordinate system, initial point is identical with cylindrical coordinate, Z ' axle and aerial radiation beam parallel are α, X with the angle of cylindrical coordinate ' parallel with actinal surface.
Step 4: determine interarea central point (x c, z c) after, calculate from feed center to subreflector center, then to interarea center, then arrive total wave-path L of aperture centre o;
Step 5: in given confinement space, from interarea center, outside pointwise solves and meets light path L=L ointerarea on point coordinates, solution formula is by a series of geometrical relationship process and mathematical derivation, and the axial coordinate that can obtain interarea is put is:
Wherein: (x f*, y f*, z f*) for interarea or minor face be the coordinate in the secondary coordinate system of Descartes of α at the angle of pitch, L 0for total optical path, ρ sfor the pole span of subreflector in spherical coordinates.
Step 6: the some cloud completing interarea and minor face solves, preserves the face type data of interarea and minor face.
2. the method for designing of a kind of confinement space continuous phase correction reflecting antenna according to claim 1, it is characterized in that stating in step 3, construct a secondary coordinate system parallel with radiation beam, it is characterized by initial point identical with cylindrical coordinate, Z ' axle and aerial radiation beam parallel, be α, X with the angle of cylindrical coordinate ' parallel with the actinal surface tilted.
3. the method for designing of a kind of confinement space continuous phase correction reflecting antenna according to claim 1, is characterized in that in described step 5, the solution formula of the interarea face type in secondary coordinate system that tilts:
Wherein: (x f*, y f*, z f*) for interarea or minor face be the coordinate in the secondary coordinate system of Descartes of α at the angle of pitch, L 0for total optical path, ρ sfor the pole span of subreflector in spherical coordinates.
4. the method for designing of a kind of confinement space continuous phase correction reflecting antenna according to claim 1, to is characterized in that in described step 5, when solving the interarea point obtained and being positioned at outside confinement space, performing a total optical path correction, total optical path being updated to L 0=L 0proceed to solve after+n λ, in formula, λ is wavelength corresponding to operating frequency, and n is integer.
5. the method for designing of a kind of confinement space continuous phase correction reflecting antenna according to claim 4, is characterized in that choosing of n should make again to solve the interarea point obtained and be positioned at confinement space, and as far as possible close to interface, top.
CN201510932475.9A 2015-12-15 2015-12-15 A kind of design method of confinement space continuous phase amendment reflecting antenna Active CN105470653B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107121600A (en) * 2017-06-07 2017-09-01 中国工程物理研究院应用电子学研究所 A kind of automatic testing equipment for testing aerial radiation field uniformity

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1248077A (en) * 1999-09-07 2000-03-22 信息产业部电子第五十四研究所 Manufacture of multibeam parabolic torus antenna with secondary phase correcting surface
WO2000067345A1 (en) * 1999-04-30 2000-11-09 France Telecom Antenna with continuous reflector for multiple reception of satellite beams

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000067345A1 (en) * 1999-04-30 2000-11-09 France Telecom Antenna with continuous reflector for multiple reception of satellite beams
CN1248077A (en) * 1999-09-07 2000-03-22 信息产业部电子第五十四研究所 Manufacture of multibeam parabolic torus antenna with secondary phase correcting surface

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107121600A (en) * 2017-06-07 2017-09-01 中国工程物理研究院应用电子学研究所 A kind of automatic testing equipment for testing aerial radiation field uniformity
CN107121600B (en) * 2017-06-07 2023-04-07 中国工程物理研究院应用电子学研究所 Automatic testing device for testing uniformity of antenna radiation field

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