CN115598823A - Sun filter component of solar space telescope and thermal analysis method thereof - Google Patents
Sun filter component of solar space telescope and thermal analysis method thereof Download PDFInfo
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- CN115598823A CN115598823A CN202211587642.7A CN202211587642A CN115598823A CN 115598823 A CN115598823 A CN 115598823A CN 202211587642 A CN202211587642 A CN 202211587642A CN 115598823 A CN115598823 A CN 115598823A
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B5/00—Optical elements other than lenses
- G02B5/20—Filters
- G02B5/22—Absorbing filters
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B5/00—Optical elements other than lenses
- G02B5/20—Filters
- G02B5/26—Reflecting filters
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention relates to the technical field of spacecraft thermal control, and provides a solar filter assembly of a solar space telescope. The thermal analysis method provided by the invention calculates and obtains the integral energy distribution of the filter mirror assembly in the direct sunlight state according to the spectral energy distribution of sunlight and the spectral radiation characteristic parameters of the optical film system, and then the integral energy distribution is used as the input condition of the spacecraft thermal analysis simulation software, and the on-orbit temperature of the sun filter mirror assembly of the solar space telescope is calculated and obtained through an energy equivalent method. According to the method, the on-orbit temperature of the filter mirror assembly is calculated by spacecraft thermal analysis simulation software under the condition that spectral thermal analysis is not carried out, and the problem that the temperature distribution of the counterglow filter mirror assembly cannot be accurately obtained by spacecraft thermal analysis simulation software in the prior art is solved.
Description
Technical Field
The invention relates to the technical field of spacecraft thermal control, and particularly provides a solar filter component of a solar space telescope and a thermal analysis method thereof.
Background
The solar space telescope has the advantages of full time, no atmospheric interference and the like, and is widely applied in the field of solar observation. Wherein, the filter assembly is settled at telescope owner optical system front end, pass through filter group, allow specific wave band light to pass through filter assembly and enter into owner optical system, filter assembly generally contains a plurality of filters, the membrane system parameter on each filter surface is different to some extent, filter assembly rises to the air after ground environment assembly and regulation is accomplished and is gone into the rail, can produce deformation because temperature variation on the track, lead to filter deformation or even damage, influence the formation of image quality, consequently need accurately calculate filter assembly's the temperature level at the rail in ground development stage, avoid it to produce the condition of deformation and damage. At present, thermal analysis of a spacecraft is mainly carried out through simulation analysis software, such as NX/TMG, thermal Desktop and the like, and the capability of calculating the on-orbit Thermal effect of a spacecraft component under complex optical mirror film system parameters and multispectral spectral bands is not provided.
For the filter lens assembly arranged outside a cabin plate outside a satellite load cabin, because of long-term sun-oriented observation, the filter lens assembly is subjected to direct sunlight for a long time, film system parameters of each filter are directly input into simulation analysis software under the action of solar spectrum energy, the spectral heat effect of the filter lens assembly and the heat distribution influence of the telescope assembly are not easy to realize by calculation, and the temperature distribution of the filter lens assembly cannot be accurately obtained.
Disclosure of Invention
The invention aims to solve the problems and provides a sun filter component of a solar space telescope and a thermal analysis method thereof.
The invention provides a solar space telescope sun filter assembly, comprising: along the sunlight incidence direction, N optical filters are arranged in sequence, the N optical filters are lenses, wherein N is any positive integer, one side or two side mirror surfaces of each optical filter are plated with different optical film systems, the optical film systems only reflect or transmit sunlight of specific wave bands, the N optical filters are fixedly connected in the installation frame, the outer side of the installation frame is provided with a light shield, the installation frame is connected onto an outer cabin plate of the satellite load cabin through an installation flexible joint, a heat insulation pad is further arranged between the installation flexible joint and the outer cabin plate of the satellite load cabin, and the heat conduction between the outer cabin plate of the satellite load cabin and a solar space telescope sun filter assembly is isolated.
Preferably, the N pieces of optical filters are fixed in position through pressing rings on two sides and connected with the mounting frame in a gluing mode.
Preferably, the mounting frame is made of aluminum alloy or titanium alloy material.
The invention provides a thermal analysis method of a sun filter mirror assembly of a solar space telescope, which comprises the following steps:
s1, determining spectral energy distribution of sunlight, the light absorption rate of each filter material, and the reflectivity and the transmissivity of each optical film system to the sunlight which enters the optical film system;
s2, respectively calculating the energy distribution of the sunlight of each wave band passing through each optical film system and each optical filter, namely obtaining the transmission energy of the sunlight of each wave band penetrating through the solar space telescope counterglow filter assembly, the reflection energy reflected back to the space environment by the counterglow filter assembly of the solar space telescope and the absorption energy absorbed by the counterglow filter assembly of the solar space telescope;
s3, grouping and summing the transmitted energy, the reflected energy and the absorbed energy of the sunlight of all wave bands to obtain total transmitted energy, total reflected energy and total absorbed energy;
and S4, establishing a thermal analysis model according to all the calculation data in the S1-S3, performing thermal analysis in simulation software by adopting an energy equivalent method, and obtaining the on-orbit temperature of the sun filter mirror assembly of the solar space telescope.
Preferably, the sum of the total transmitted energy, the total reflected energy and the total absorbed energy is the total solar energy.
Preferably, the specific process of the energy equivalent method in S4 is as follows: and calculating to obtain equivalent radiation characteristic parameters according to the total transmission energy, the total reflection energy and the total absorption energy, and simulating according to the equivalent radiation characteristic parameters of each optical film system, wherein the energy distribution obtained by simulation is equivalent to the energy distribution in the real environment.
Compared with the prior art, the invention can obtain the following beneficial effects:
the invention discloses a spacecraft thermal analysis simulation software, which aims at complex optical film system parameters and multi-spectral bands and cannot effectively calculate the orbit thermal effect of a spacecraft component.
Drawings
FIG. 1 is a schematic diagram of a solar filter mirror assembly for a solar space telescope according to an embodiment of the present invention;
FIG. 2 is a graph of the energy spectral distribution of sunlight provided in accordance with an embodiment of the present invention;
fig. 3 is a graph of absorbance of a filter material provided in accordance with an embodiment of the invention.
Wherein the reference numerals include:
the device comprises a first optical filter 1, a second optical filter 2, a first optical film system 3, a second optical film system 4, a third optical film system 5, a mounting frame 6, a light shield 7, a mounting flexible joint 8 and a heat insulation pad 9.
Detailed Description
Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. In the following description, like modules are denoted by like reference numerals. In the case of the same reference numerals, their names and functions are also the same. Therefore, detailed description thereof will not be repeated.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention.
Fig. 1 shows the structure of a solar filter mirror assembly for a solar space telescope according to an embodiment of the present invention.
As shown in fig. 1, a description will be given below of a solar filter assembly and solar light transmission of a solar space telescope according to an embodiment of the present invention: a first optical filter 1 and a second optical filter 2 are sequentially arranged along the incident direction of sunlight, the two optical filters are lenses, the first optical filter 1 is directly irradiated by the sunlight, the sunlight respectively enters a telescope primary optical system through the first optical filter 1 and the second optical filter 2, two sides of the first optical filter 1 are plated with different optical film systems, the outer side of the first optical filter 1 is plated with a first optical film system 3, and the other side of the first optical filter 1 is plated with a second optical film system 4; the second optical filter 2 is only plated with a third optical film system 5 on the outer side, and is not plated with an optical film on the other side, and the first optical film system 3, the second optical film system 4 and the third optical film system 5 only reflect or transmit sunlight of a specific waveband. First light filter 1 and second light filter 2 all pass through both sides clamping ring fixed position, and connect in installation frame 6 through the glue, installation frame 6 adopts aluminum alloy or titanium alloy material, the outside of installation frame 6 is provided with lens hood 7, installation frame 6 is connected on the cabin board of the outside cabin board in satellite load cabin through installation flexible festival 8, still be provided with heat insulating mattress 9 between the cabin board of installation flexible festival 8 and the outside cabin board in satellite load cabin, be used for isolated heat-conduction between the cabin board of the outside cabin board in satellite load cabin and the solar space telescope's the solar filter mirror subassembly, heat insulating mattress 9 adopts the polyimide heat insulating mattress.
The embodiment of the invention provides a thermal analysis method for a sun filter component of a solar space telescope, which is used for obtaining the temperature of the filter component by calculating the spectrum thermal effect through simulation without directly inputting parameters of each optical film system in spacecraft thermal analysis simulation software and specifically comprises the following steps:
it should be noted that: the first optical filter 1 and the second optical filter 2 described below are collectively referred to as an optical filter, and the first optical film system 3, the second optical film system 4, and the third optical film system 5 are collectively referred to as an optical film system.
S1, spectral energy distribution of sunlight, light absorption rate of each optical filter material, and reflectivity and transmissivity of each optical film system to the sunlight which enters the optical film system can be determined by the prior art, which are only given by way of simple examples and are not described in detail.
Fig. 2 shows an energy spectral distribution curve of sunlight provided according to an embodiment of the present invention.
As shown in FIG. 2, the solar energy increases with the wavelength within the wavelength range of 200nm to 500nm, and the solar illumination reaches the maximum value and then gradually decreases with the increase of the wavelength.
Fig. 3 shows an absorbance curve of a filter material provided according to an embodiment of the invention.
Taking the example of the absorptivity of light by the material of the first filter 1 only, the thickness of the first filter 1 is 23mm. As shown in fig. 3, the absorption of the material is strong in the ultraviolet and infrared bands, and the transmittance of the filter material is high in the visible band.
The parameters of the first optical film system 3, the second optical film system 4 and the third optical film system 5 are as follows:
in this embodiment, the first optical film system 3 adopts a sectional reflection increasing film design, mainly reflects sunlight in ultraviolet and near infrared spectrum bands, and ensures transmission of sunlight in working bands, so as to effectively reduce energy absorption of window materials.
The second optical film system 4 adopts a band-pass anti-reflection film system to ensure the effective transmission of the sunlight in the working wave band, filter out the stray light and reflect the energy at the two sides of the working wave band.
The third optical film system 5 is an ultraviolet reflection increasing film, further blocks the energy of an ultraviolet band outside the system, and can add or reduce optical filters and optical film systems under the condition of other special requirements.
S2, tracking calculation is carried out on the transmission path of the energy of a single solar spectrum band in the counterglow filter assembly of the solar space telescope through tools such as Excel, a calculator and the like according to the spectral energy distribution of the sunlight, parameters of the optical film systems and the absorption rate curve of the optical filter material to the light, the energy distribution condition of the energy after the energy passes through the first optical filter 1, the second optical filter 2, the first optical film system 3, the second optical film system 4 and the third optical film system 5 is calculated, namely the energy distribution of the sunlight of each waveband passing through each optical film system is respectively calculated, and the transmission energy q of the sunlight of a single waveband passing through the counterglow filter assembly of the solar space telescope is obtained 1 Reflected energy q reflected back to the space environment by the solar space telescope's sun filter assembly 2 Absorbed energy q absorbed by a solar filter assembly of a solar space telescope 3 ，q 3 The solar energy q absorbed by the first filter 1 4 And the solar energy q absorbed by the second filter 2 5 And (4) forming.
S3, grouping and summing the transmitted energy, the reflected energy and the absorbed energy of the sunlight of all wave bands to obtain the following result:
the total transmission energy Q of the sunlight entering the main optical system through the sun filter assembly of the solar space telescope 1 ；
Total reflected energy Q reflected by the sun filter assembly of the solar space telescope back to the space cold environment 2 ；
Total energy absorbing Q of solar space telescope sun filter assembly 3 ；
The sum of the above energies is equal to the total sunlight energy Q directly irradiated by sunlight on a sun filter assembly of the solar space telescope 0 I.e. Q 0 =Q 1 +Q 2 +Q 3 。
Wherein the total energy Q of absorption 3 Equal to the total solar illumination energy Q absorbed by the first optical filter 1 4 And the total solar illumination energy Q absorbed by the second filter 2 5 Of (a) i.e. Q 3 =Q 4 +Q 5 。
S4, establishing a thermal analysis model according to all the calculation data in the S1-S3, performing thermal analysis in spacecraft thermal analysis simulation software by adopting an energy equivalent method, calculating to obtain equivalent radiation characteristic parameters according to total transmission energy, total reflection energy and total absorption energy as shown in the table 2, and performing simulation according to the equivalent radiation characteristic parameters of each optical film system, wherein the energy distribution obtained by simulation is equivalent to the energy distribution in a real environment. The on-orbit temperature of the on-orbit filter assembly of the solar space telescope can be obtained by a conventional simulation analysis means in the process, and the on-orbit temperature of the on-orbit filter assembly of the solar space telescope can be obtained, and the part belongs to the prior art and is not specifically introduced.
While embodiments of the present invention have been shown and described above, it should be understood that the above embodiments are exemplary and should not be taken as limiting the invention. Variations, modifications, substitutions and changes to the embodiments described above will occur to those skilled in the art and are intended to be within the scope of the present invention.
The above embodiments of the present invention should not be construed as limiting the scope of the present invention. Any other corresponding changes and modifications made according to the technical idea of the present invention should be included in the protection scope of the claims of the present invention.
Claims (6)
1. A solar space telescope's optical filter subassembly to sun, its characterized in that includes:
the solar space telescope solar light filter comprises N light filters, and is characterized in that N light filters are sequentially arranged in the incident direction of sunlight and are all lenses, wherein N is any positive integer, one side or two side mirror surfaces of each light filter are plated with different optical film systems, the optical film systems only reflect or transmit the sunlight of a specific waveband, the N light filters are fixedly connected into an installation frame, a light shield is arranged on the outer side of the installation frame, the installation frame is connected onto an outer cabin plate of a satellite load cabin through an installation flexible joint, and a heat insulation pad is further arranged between the installation flexible joint and the outer cabin plate of the satellite load cabin and used for isolating heat conduction between the outer cabin plate of the satellite load cabin and a solar space telescope solar light filter component.
2. The solar filter assembly of claim 1, wherein N of said filters are fixed to the mounting frame by clamping rings on both sides and are adhesively attached to the mounting frame.
3. The sun filter assembly of claim 1, wherein said mounting frame is made of aluminum alloy or titanium alloy.
4. A method of thermally analysing a solar filter mirror assembly of a solar space telescope according to claim 1, comprising the steps of:
s1, determining spectral energy distribution of sunlight, the light absorption rate of each optical filter material, and the reflectivity and the transmissivity of each optical film system to the sunlight which enters the optical film system;
s2, respectively calculating the energy distribution of the sunlight of each wave band passing through each optical film system and the optical filter, namely obtaining the transmission energy of the sunlight of each wave band penetrating through the solar space telescope counterglow filter assembly, the reflection energy reflected back to the space environment by the solar space telescope counterglow filter assembly and the absorption energy absorbed by the solar space telescope counterglow filter assembly;
s3, grouping and summing the transmitted energy, the reflected energy and the absorbed energy of the sunlight of all wave bands to obtain total transmitted energy, total reflected energy and total absorbed energy;
and S4, establishing a thermal analysis model according to all the calculation data in the S1-S3, performing thermal analysis in simulation software by adopting an energy equivalent method, and obtaining the on-orbit temperature of the sun filter mirror assembly of the solar space telescope.
5. The method for thermally analyzing a solar filter mirror assembly of a solar-space telescope of claim 4, wherein the sum of said total transmitted energy, said total reflected energy and said total absorbed energy is the total solar energy.
6. The method for thermal analysis of a solar-solar filter mirror assembly of a solar-space telescope as claimed in claim 4, wherein the energy equivalence method of S4 is embodied as: and calculating to obtain equivalent radiation characteristic parameters according to the total transmission energy, the total reflection energy and the total absorption energy, and simulating according to the equivalent radiation characteristic parameters of each optical film system, wherein the energy distribution obtained by simulation is equivalent to the energy distribution in a real environment.
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| CN202211587642.7A CN115598823B (en) | 2022-12-12 | 2022-12-12 | Solar-opposite filter lens component of solar space telescope and thermal analysis method thereof |
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| CN202211587642.7A CN115598823B (en) | 2022-12-12 | 2022-12-12 | Solar-opposite filter lens component of solar space telescope and thermal analysis method thereof |
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