Novel auxiliary reflecting face supporting satellite borne ring focus antenna

A space-borne ring focus and antenna technology, which is applied in the directions of antenna, antenna support/installation device, radiation unit cover, etc., can solve the problems of large loss, complicated preparation method of dielectric cover material, and influence on antenna radiation efficiency, etc., and achieve low loss , increase the difficulty of installation, the effect of strong space adaptability

Active Publication Date: 2017-07-18
SHANGHAI SPACEFLIGHT INST OF TT&C & TELECOMM
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the design method of dielectric support is adopted, the preparation method of the dielectric cover material is complicated, and the basic mold is combined with complex process processing, and the glass fiber reinforced plastic dielectric material used in the high frequency band (above the Ka frequency band) has a large loss, which in turn affects the antenna. Radiation efficiency

Method used

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  • Novel auxiliary reflecting face supporting satellite borne ring focus antenna
  • Novel auxiliary reflecting face supporting satellite borne ring focus antenna
  • Novel auxiliary reflecting face supporting satellite borne ring focus antenna

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] see figure 1 , the space-borne ring-focus antenna based on the new type of supporting sub-reflector described in the present invention includes a main reflector 1, a sub-reflector 2, a feed source assembly 3, a cylindrical dielectric cover 4, a circular frustum dielectric cover 5, an adjusting gasket 7 and a center The support cover, the feed source assembly 3 is installed on the central support barrel 6, the cylindrical dielectric cover 4 is tightly connected with the secondary reflector 2 and then fixed with the round table dielectric cover 5 by screws and then installed on the central support barrel 6, the central support barrel 6 Adjusting gaskets 7 are added between the round frustum dielectric cover 5, and finally it is connected and fixed with the main reflective surface 1.

Embodiment 2

[0030] see Figure 1 to Figure 5 , this embodiment is an improvement made on the basis of Embodiment 1, in particular, the sub-reflector 2 is an elliptical surface of revolution made of metal, and its diameter is d=6.75λ 0 ,λ 0 is the wavelength of the center frequency electromagnetic wave, and the elliptic generatrix equation is -3.10λ 0 ≤X≤3.10λ 0 , -2.37λ 0 ≤Y≤2.37λ 0 ; The main reflector 1 is an aluminum honeycomb rotating paraboloid made of carbon fiber, and its diameter is D=67.5λ 0 , the focal length is F=18.23λ 0 , the parabolic generatrix equation is (X-d / 2) 2 =4×F×Z, Z≥0, X∈R (that is, X is a real number); the feed source component 3 is an axial groove corrugated horn, and the radius of the horn mouth surface r=1.92λ 0 , using BJ180 waveguide for circular polarization feeding; the cylindrical dielectric cover 4 is made of polyimide material, and its aperture size is about 6.75λ 0 , which is the same as the diameter d of the sub-reflector 2, and the height i...

Embodiment 3

[0032] see Figure 1 to Figure 5 , the present embodiment is an improvement made on the basis of the embodiment, wherein the sub-reflector 2 is an elliptical surface of revolution made of metal, its diameter is d=100mm, and the ellipse generatrix equation is -3.10λ 0 ≤X≤3.10λ 0 , -2.37λ 0 ≤Y≤2.37λ 0 ; The main reflector 1 is an aluminum honeycomb rotating paraboloid of carbon fiber material, its diameter is D=1000mm, the focal length is F=270mm, and the parabola generatrix equation is (X-d / 2) 2 =4×F×Z, Z≥0, X∈R (that is, X is a real number); the feed component 3 is an axial groove corrugated horn, the radius of the horn mouth is r=28.5mm, and the BJ180 waveguide is used for circularly polarized feed Electricity: Cylindrical dielectric cover 4 is made of polyimide material, its aperture size is the same as the diameter d of the secondary reflector 2, the height is H1=73mm, the side wall thickness t1=0.8mm, the bottom surface thickness t2=2mm, and the diameter R1=30mm roun...

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Abstract

The invention discloses a novel auxiliary reflecting face supporting satellite borne ring focus antenna comprising a main reflecting face, an auxiliary reflecting face, a feed source assembly, a cylinder medium cover, a round platform medium cover, adjusting pads and a central support cover, wherein the feed source assembly is mounted on a central support bucket; after the cylinder medium cover is firmly connected with the auxiliary reflecting face in a fixed manner, the cylinder medium cover and the auxiliary reflecting face are connected with the round platform medium cover in a fixed manner via screws; the cylinder medium cover, the auxiliary reflecting face and the round platform medium cover are jointly mounted on the central support bucket, adjusting pads are added between the central support bucket and the round platform medium cover and between the central support bucket and the main reflecting face, and the central support bucket is finally fixed on the main reflecting face. According to the satellite borne ring focus antenna disclosed in the invention, a large aperture antenna is enabled to be advantaged by high assembling precision, high antenna efficiency, reliable structure, convenient debugging operation, low cost and the like; the large aperture antenna is particularly suitable for being used as the satellite borne ring focus antenna.

Description

technical field [0001] The invention belongs to the field of space-borne communication antennas, and in particular relates to a space-borne ring-focus antenna based on a novel supporting sub-reflector. Background technique [0002] Because of its simple structure, easy design, high structural strength and superior performance, the reflector antenna is currently the antenna form commonly used in spaceborne antennas. Ring-focus antennas generally support the sub-reflector with 3 or 4 metal struts on the main reflector or the feed horn to maintain the relative positional relationship. Its main disadvantages are: 1) Due to the influence of metal struts on the shielding and scattering of electromagnetic waves and other factors, the efficiency of the antenna is reduced; 2) 3 or 4 metal struts also have the relative positional relationship between the main and auxiliary poles, and the assembly accuracy is low. Difficult adjustments, low connection reliability, etc. It is difficul...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q1/12H01Q1/42H01Q13/02H01Q19/19
Inventor 张丽娜李春晖王见苏晟石同武
Owner SHANGHAI SPACEFLIGHT INST OF TT&C & TELECOMM
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