CN108461925A - A kind of list covering grid reinforcement backing strip high-precision reflector - Google Patents
A kind of list covering grid reinforcement backing strip high-precision reflector Download PDFInfo
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- CN108461925A CN108461925A CN201810211433.XA CN201810211433A CN108461925A CN 108461925 A CN108461925 A CN 108461925A CN 201810211433 A CN201810211433 A CN 201810211433A CN 108461925 A CN108461925 A CN 108461925A
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- grid
- covering
- backing strip
- reflector
- reinforces
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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
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
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- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention relates to a kind of single covering grids to reinforce backing strip high-precision reflector.The present invention includes that covering and grid reinforce backing strip.The covering lower surface is reinforced backing strip with grid and is connect, and covering upper surface is as reflecting surface；Covering is paraboloid pressing plate, and grid reinforces backing strip along covering following table EDS maps, and covering reinforces backing strip with grid and is all made of zero expansion composite material.The present invention disclosure satisfy that superelevation microwave reflector is less than or equal to 10 μm of requirements for reflecting surface thermal deformation RMS value.Thermal deformation numerical value can be significantly reduced relative to conventional carbon fiber composite honeycomb sandwich structures reflector；Relative to conventional carbon fiber composite material hyperboloid grid sandwich structure, originally eliminates one layer of covering and use Zero-expansion material, while ensureing that thermal deformation is met the requirements, reduce the quality of reflector.
Description
Technical field
The invention belongs to space flight Reflectron technology fields, are related to a kind of single covering grid reinforcement backing strip high-precision reflector.
Background technology
With the development of satellite technology, spaceborne hyperfrequency microwave reflector uses frequency in satellite communication and remote sensing observations
Rate is higher and higher.When satellite is in-orbit, since solar irradiation, the earth are to Orbital heat flux such as the reflection of sunlight and earth infra-red radiations
It can change over time, satellite retroreflector can undergo larger difference variation during in orbit, therefore need to reduce reflector
In-orbit thermal deformation, to meet the requirement of reflecting surface electrical property.Reflector electric property generally requires reflector type face precision (RMS
Value) it is no more than 1st/50th of working frequency range microwave wavelength, therefore, space hyperfrequency remote sensing reflector (working frequency range
100GHz-600GHz) require its reflecting surface RMS≤10 μm.
The reflecting surface of spaceborne hyperfrequency microwave reflector is mostly the paraboloid structure made of carbon fibre composite, generally
Using the honeycomb sandwich construction as shown in Fig. 1 (a) and two kinds of forms of hyperboloid grid sandwich structure as shown in Fig. 1 (b).
Conventional carbon fiber composite honeycomb sandwich structures are made of upper and lower covering, glued membrane and hexagonal honeycomb, wherein covering
Skin material is generally high modulus carbon fiber/resin composite materials, and honeycomb generally has two kinds of aluminum honeycomb and Nomex honeycombs.From existing
Result of study summary show that the honeycomb sandwich construction reflector thermal deformation of 1.2m bores reaches tens micron dimensions, therefore honeycomb
Sandwich haves the shortcomings that thermal deformation is larger, is not suitable for the higher reflector structure of reflector type face required precision；Often
Rule carbon fibre composite hyperboloid grid sandwich structure is made of upper and lower covering and grid reinforcing rib, existing research shows that hyperbolic
Although panel grid sandwich structure thermal deformation is smaller, there is the shortcomings that heavier mass.
Therefore the reflector for the suitable high-precision reflector structure that a kind of quality of the proposition present invention is small and thermal deformation resistant is strong.
Invention content
It is an object of the invention to provide a kind of single covering grids to reinforce backing strip high-precision reflector.
The present invention includes that covering and grid reinforce backing strip.The covering lower surface is reinforced backing strip with grid and is connect, covering
Upper surface is as reflecting surface；Covering is paraboloid pressing plate, and grid reinforces backing strip along covering following table EDS maps, and covering is reinforced with grid
Backing strip is all made of zero expansion composite material.
Further, the covering is along warp symmetrical paraboloid.
The grid reinforce backing strip by the zero degree parallel grid parallel with paraboloid warp, with zero degree parallel grid in-
It -60 ° of parallel grids at 60 ° of angles and is formed in 60 ° of parallel grids at 60 ° of angles with zero degree parallel grid；Grid is reinforced backing strip and is covered
The skin connecting side center of area is overlapped with the covering center of area.
Preferably, it is -125 DEG C~+125 DEG C that the reflecting surface, which uses offset-fed paraboloid, operating temperature,.
The covering and grid reinforce backing strip adhesion.
The Zero-expansion material is along plane respectively to coefficient of thermal expansion≤0.5 × 10-7/℃。
The paraboloid is：Parabola x2The paraboloid that=26000z is rotated into around central shaft Z, distance is revolved in x-axis
Turn the parabolic element of the cylinder interception at the 7100mm of center with radius R=1820mm.
The covering is reinforced backing strip with grid and is formed by hot setting.
The present invention disclosure satisfy that superelevation (100GHz-600GHz) microwave reflector is less than reflecting surface thermal deformation RMS value
It is required equal to 10 μm.The present invention can significantly reduce heat relative to conventional carbon fiber composite honeycomb sandwich structures reflector
Deform numerical value (1.2m bore reflector thermal deformation RMS values from tens microns to ten micron or less)；It is multiple relative to conventional carbon fiber
Condensation material hyperboloid grid sandwich structure, the present invention is innovative to be eliminated one layer of covering and uses Zero-expansion material, is being protected
While card thermal deformation is met the requirements, the quality of reflector can be reduced.The Characteristics of Thermal deformation of the present invention enables to be applied to
The spaceborne hyperfrequency microwave reflector such as satellite communication, remote sensing observations, has wide practical use.
Description of the drawings
Fig. 1 (a) is existing superelevation microwave frequency band reflector honeycomb sandwich construction；
Fig. 1 (b) is existing superelevation microwave frequency band hyperboloid grid sandwich structure；
Fig. 2 is the overall structure diagram of the present invention；
Fig. 3 is the geometric constitution of covering during the present invention is implemented；
Fig. 4 is the structural schematic diagram of covering in the embodiment of the present invention；
Fig. 5 is the structural schematic diagram that grid reinforces backing strip in the embodiment of the present invention.
Specific implementation mode
The structure type of the present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in Fig. 2, it is 1.82m that a kind of list covering grid, which reinforces backing strip high-precision reflector bore, in the present embodiment, instead
It is -125 DEG C~+125 DEG C to penetrate face and use offset-fed paraboloid reflecting surface, operating temperature.
It includes that covering 1 and grid reinforce backing strip 2 that single covering grid, which reinforces backing strip high-precision reflector, and covering and grid are reinforced
Backing strip adhesion；
Covering 1 is paraboloid pressing plate, using zero expansion composite material；Zero-expansion material is along plane respectively to coefficient of thermal expansion
(CTE)≤0.5×10-7/℃。
Parabola x as shown in Figure 32The paraboloid that=26000z is rotated into around central shaft Z, in x-axis in distance rotation
The parabolic element intercepted with the cylinder of radius R=1820mm at heart 7100mm is the geometric constitution of the present embodiment reflector；
Preferably, the present embodiment under the limitation of reflector size, quality and fundamental frequency condition, to reflection face thickness and adds
Strengthening tendons thickness, arrangement and height optimize analysis：
It is excellent using reflecting surface overlay thickness, reinforcing rib density, reinforcing rib overlay thickness and reinforcement height as analyzing first
The parameter of change, using thermal deformation RMS value, reflector size, rigidity requirement as restrictive condition, the most light target as an optimization of quality.
Then finite element model is established using patran/nastran finite element softwares, studies each parameter respectively for reflector thermal deformation
Influence, analysis variation tendency obtain following rule：Reflect face thickness, reinforcing rib density, reinforcing rib overlay thickness and reinforcing rib
The increase of highly four parameters can be such that RMS value reduces, and quality linear increases.
The factor for then considering quality, to reflection face thickness, reinforcing rib layout angle, reinforcing rib density, reinforcing rib laying
The parameters such as thickness and reinforcement height are determined.Following scheme is finally obtained：
As shown in Figures 4 and 5, reflection face thickness is 2mm thick, and the thickness that grid reinforces backing strip is 0.34mm, is highly 90mm,
Covering 1 is symmetrical about paraboloid warp 4, the center of area 3；Grid reinforces backing strip 2 by the zero degree parallel lattice parallel with paraboloid warp 4
Grid 6 are in -60 ° of parallel grids 7 at -60 ° of angles and 60 ° of parallel lattice with zero degree parallel grid 6 in 60 ° of angles with zero degree parallel grid 6
Grid 8 form, and the distance between one group of two grid of parallel grid is 80mm, is overlapped with the covering center of area 3 with the 1 adhesion side heart 5 of covering；
1.82m bores list covering grid reinforcement backing strip high-precision reflector is by quality after optimization in the present embodiment
8.6kg, RMS value 6.1, RMS value≤10 μm.Meet the type face essence of the spaces 100GHz-600GHz hyperfrequency remote sensing reflector
Spend index request.
The principle of the present invention is：Paraboloid covering is made using zero thermal expansion composite laminate and grid reinforces backing strip, covering
For reflector face, reinforce the rigidity that backing strip is used to reinforce reflector.By to reflection face thickness and Rib Thickness and height
The adjustment of degree makes single covering grid reinforce the requirements that backing strip high-precision reflector meets space hyperfrequency reflector.
Above-described embodiment is used for illustrating the present invention, rather than limits the invention, the present invention spirit and
In scope of the claims, to any modifications and changes that the present invention makes, protection scope of the present invention is both fallen within.
Claims (7)
1. a kind of list covering grid reinforces backing strip high-precision reflector, including covering and grid reinforce backing strip；It is characterized in that：Institute
The covering lower surface stated is reinforced backing strip with grid and is connect, and covering upper surface is as reflecting surface；Covering is paraboloid pressing plate, and grid adds
Strong backing strip along covering following table EDS maps, reinforce backing strip with grid and be all made of zero expansion composite material by covering.
2. a kind of single covering grid as described in claim 1 reinforces backing strip high-precision reflector, it is characterised in that：The illiteracy
Skin is along warp symmetrical paraboloid.
3. a kind of single covering grid as described in claim 1 reinforces backing strip high-precision reflector, it is characterised in that：The lattice
Grid reinforce backing strip by the zero degree parallel grid parallel with paraboloid warp, -60 ° of parallel lattice with zero degree parallel grid in -60 ° of angles
Grid and with zero degree parallel grid in 60 ° of angles 60 ° of parallel grids form；Grid reinforces backing strip and the same covering of the covering connecting side center of area
The center of area overlaps.
4. a kind of single covering grid as described in claim 1 reinforces backing strip high-precision reflector, it is characterised in that：Described is anti-
It is -125 DEG C~+125 DEG C to penetrate face and use offset-fed paraboloid, operating temperature.
5. a kind of single covering grid as described in claim 1 reinforces backing strip high-precision reflector, it is characterised in that：Covering and lattice
Grid reinforce backing strip adhesion.
6. a kind of single covering grid as described in claim 1 reinforces backing strip high-precision reflector, it is characterised in that：Described zero
Expanding material is along plane respectively to coefficient of thermal expansion≤0.5 × 10-7/℃。
7. a kind of single covering grid as described in claim 1 reinforces backing strip high-precision reflector, it is characterised in that：The illiteracy
Skin is reinforced backing strip with grid and is formed by hot setting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810211433.XA CN108461925A (en) | 2018-03-15 | 2018-03-15 | A kind of list covering grid reinforcement backing strip high-precision reflector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810211433.XA CN108461925A (en) | 2018-03-15 | 2018-03-15 | A kind of list covering grid reinforcement backing strip high-precision reflector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108461925A true CN108461925A (en) | 2018-08-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810211433.XA Withdrawn CN108461925A (en) | 2018-03-15 | 2018-03-15 | A kind of list covering grid reinforcement backing strip high-precision reflector |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110534876A (en) * | 2019-07-23 | 2019-12-03 | 西安空间无线电技术研究所 | A kind of reflector antenna and preparation method thereof |
| CN111224245A (en) * | 2020-01-13 | 2020-06-02 | 电子科技大学 | Honeycomb electromagnetic wave-absorbing reinforcing structure |
| CN112407334A (en) * | 2020-11-12 | 2021-02-26 | 北京理工大学 | Near-zero expansion lattice structure |
| CN113165307A (en) * | 2018-12-13 | 2021-07-23 | 三菱电机株式会社 | Honeycomb sandwich panel, optical device and artificial satellite |
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|---|---|---|---|---|
| CN113165307A (en) * | 2018-12-13 | 2021-07-23 | 三菱电机株式会社 | Honeycomb sandwich panel, optical device and artificial satellite |
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Application publication date: 20180828 |