CN117724222A - Precise temperature control device of space optical emission mirror - Google Patents
Precise temperature control device of space optical emission mirror Download PDFInfo
- Publication number
- CN117724222A CN117724222A CN202311748624.7A CN202311748624A CN117724222A CN 117724222 A CN117724222 A CN 117724222A CN 202311748624 A CN202311748624 A CN 202311748624A CN 117724222 A CN117724222 A CN 117724222A
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- mirror
- main
- emission
- secondary mirror
- temperature control
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- 230000003287 optical effect Effects 0.000 title claims abstract description 52
- 238000010438 heat treatment Methods 0.000 claims description 13
- 239000012774 insulation material Substances 0.000 claims description 8
- 239000003973 paint Substances 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 6
- 229920001721 polyimide Polymers 0.000 claims description 6
- 239000011248 coating agent Substances 0.000 claims description 5
- 238000000576 coating method Methods 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004642 Polyimide Substances 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 239000006234 thermal black Substances 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 4
- 230000010354 integration Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 230000031700 light absorption Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000005855 radiation Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000002310 reflectometry Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
Classifications
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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
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/40—Solar thermal energy, e.g. solar towers
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- Optical Elements Other Than Lenses (AREA)
Abstract
The invention provides a precise temperature control device of a space optical emission mirror, which comprises an emission lens barrel, an emission main mirror, a main mirror back plate, a main mirror chamber, an emission secondary mirror and a secondary mirror back plate.
Description
Technical Field
The invention relates to the technical field of thermal control of space satellite-borne optical loads, in particular to a precise temperature control device of a space optical emission mirror.
Background
The optical load carried on the spacecraft is more and more at present, and the optical load has very high index requirement on thermal control due to the characteristics and requirements of high precision and high stability. The stability of temperature plays a critical role in the thermal deformation of each main optical component in the optical load, and the traditional optical load adopts a mode of separating and independently controlling the temperature of each optical component, so that the relative position stability of each optical component cannot be ensured, and the high-precision temperature control of the optical component cannot be realized.
Patent document with publication number CN114546002a discloses that a high-precision temperature control device of a deep space optical load main mirror component controls temperature of a back plate in different areas, and controls temperature of a main mirror in a radiation mode. The technology only controls the temperature of the main mirror, the heat control implementation is required to be additionally carried out on the secondary mirror part, and a light shield is required to be additionally installed to shield stray light. The occupied weight resources are more, and the integration and the adaptability are insufficient.
Patent document publication No. CN115903207a discloses a temperature control system for a primary mirror of a large aperture solar telescope. The technology cools the main mirror through the cooling air nozzle of the backboard. The technology only plays a role in cooling the main mirror, cannot control the temperature, and is only applicable to the ground through an air convection method. For the field of space optical load temperature control, the technology is not applicable.
Patent document publication No. CN115189222B discloses a laser transceiver device and an optical telescope with a high-reliability temperature control structure. In the technology, outdoor air flows through a radiating chamber to cool an optical component, and a heating component in a heating chamber to heat the optical component. The technology is suitable for cooling only on the ground by an air convection method, has poor temperature control precision, and is not suitable for the field of space high-precision optical load temperature control.
Patent document publication No. CN110376704a discloses a temperature control cover for a spatial optical mirror. The technology is used for sticking a heating sheet to the temperature control cover, and controlling the temperature of the temperature control cover, so that the temperature of the reflecting mirror in the cover is controlled. The technology only plays a role in controlling the temperature of the optical component, and is suitable for solving the problem of insufficient adaptability of factors such as complicated external heat flow, stray light and the like in space.
Patent document with publication number CN115617096a discloses a precise temperature control device for a main reflector of a large-caliber space optical remote sensor. The technology controls the temperature of the main reflector by controlling the temperature of the cylinder wall temperature control cover and the back temperature control cover. The technology is only used as a temperature control scheme of a large-caliber main mirror, and the secondary mirror part needs to be additionally subjected to thermal control implementation, so that the technology is not suitable for the field of space load temperature control with smaller volume.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a precise temperature control device of a space optical emission mirror.
The invention provides a precise temperature control device of a space optical emission mirror, which comprises an emission lens cone, an emission main mirror, a main mirror back plate, a main mirror chamber, a secondary mirror mounting plate, an emission secondary mirror and a secondary mirror back plate, wherein the emission main mirror and the main mirror back plate are oppositely arranged at two sides of the main mirror chamber, and the main mirror chamber is fixedly arranged at one side of the emission lens cone;
the secondary mirror and the secondary mirror backboard are oppositely arranged on two sides of the secondary mirror mounting plate, the secondary mirror mounting plate is fixedly arranged on the other side of the emission lens cone, and the emission main mirror and the emission secondary mirror are arranged towards the inside of the emission lens cone, and the main mirror chamber, the emission lens cone, the main mirror backboard and the secondary mirror backboard are all provided with heating sheets.
Preferably, the main emission mirror and the main mirror back plate are fixed in the main mirror chamber through flange surface screws respectively;
the emission secondary mirror and the secondary mirror backboard are fixed on the secondary mirror mounting plate through screws;
the end face of the main lens chamber is fixedly connected with the end face of one side of the transmitting lens barrel through screws.
Preferably, the screw fixing modes of the emitting main mirror, the emitting secondary mirror, the main mirror back plate and the secondary mirror back plate are all fixed by adopting titanium alloy screws and polyimide gaskets.
Preferably, a first lightening groove is formed in the back surface of the emission main mirror, the position of the first lightening groove corresponds to that of the main mirror backboard, and a thermistor is arranged in the first lightening groove;
the back of the emission secondary mirror is provided with a second lightening groove, the position of the second lightening groove corresponds to the position of the secondary mirror backboard, and a thermistor is arranged in the second lightening groove;
and thermistors are arranged on the transmitting lens barrel and the main lens chamber.
Preferably, the main mirror backboard, the main mirror chamber, the transmitting lens cone and the secondary mirror backboard are all sprayed with thermal control black paint.
Preferably, the outer surface of the secondary mirror backboard is coated with a heat insulation material, and the heat insulation material is a carburized polyimide film.
Preferably, the main lens chamber and the emission lens barrel are made of carbon fiber materials;
the primary mirror backboard and the secondary mirror backboard are both made of aluminum-based silicon carbide materials.
Preferably, the cross-section of the launching tube is in a spindle shape, the launching main mirror is arranged in the middle of the spindle shape, and the launching secondary mirror is arranged at the tip of the spindle shape.
Preferably, the inner surface of the emission lens barrel is sprayed with a black light absorption coating.
Preferably, a plurality of heating plates are adhered to the main lens chamber and the transmitting lens barrel, and the heating plates are uniformly adhered along the circumferential directions of the main lens chamber and the transmitting lens barrel and are uniformly adhered along the length extension directions of the main lens chamber and the transmitting lens barrel.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention is different from the traditional mode of separating and independently controlling the temperature of each optical component by the optical load, ensures the high-precision temperature control of the optical component and the stable relative position of each optical component by integrating the main mirror, the secondary mirror, the back plate, the main mirror chamber and the lens barrel, and has the advantages of convenient carrying and installation on a spacecraft, simple process, high reliability and lower cost due to the high integration of the device.
2. The invention adopts the technical means that the black light absorption coating is sprayed on the inner surface of the transmitting lens barrel and the heat insulation material is coated on the outer surface of the secondary lens backboard, so that the influence of heat flow outside the space and stray light on a light path can be greatly reduced, a light shield is not required to be additionally arranged, the envelope of the whole device is reduced, and the weight is saved.
3. The invention adopts the technical means that the heating plates are uniformly distributed outside the main lens chamber and the transmitting lens barrel, and can increase the temperature uniformity of the whole device by a gridding temperature control mode.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic diagram of the structure of the primary mirror of the present invention;
FIG. 3 is a schematic view of the structure of the back plate of the main mirror according to the present invention;
FIG. 4 is a schematic diagram of a secondary mirror back plate according to the present invention;
FIG. 5 is a schematic diagram of the structure of the emission secondary mirror in the present invention.
The figure shows:
main lens backboard 5 of transmitting lens barrel 1
Mirror back plate 6 of primary mirror chamber 2 times
The sub-mirror mounting plate 3 emits a sub-mirror 7
Emission main mirror 4
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
The invention discloses a precise temperature control device of a space optical emission mirror, which is different from the traditional temperature control mode of separating and independent optical components, and can keep the relative positions of all parts stable by integrally designing all the optical components, thereby realizing precise temperature control, and simultaneously, the device is very convenient to mount on a spacecraft due to the high integration of the device.
The invention provides a precise temperature control device of a space optical emission mirror, which comprises an emission lens cone 1, an emission main mirror 4, a main mirror back plate 5, a main mirror chamber 2, an emission secondary mirror 7 and a secondary mirror back plate 6, wherein:
the main emission mirror 4 and the main mirror backboard 5 are fixed in the main mirror chamber 2 through screws on the flange surface;
the lightening groove surface of the emission main mirror 4 is arranged opposite to the position of the main mirror backboard 5;
the end face of the main lens chamber 2 is fixedly connected with the end face of one side of the transmitting lens barrel 1 through a screw;
the transmitting secondary mirror 7 is fastened on the other side of the transmitting lens barrel 1 through a secondary mirror mounting plate 3;
the secondary lens backboard 6 is fixed on the outermost surface of the emission lens cone 1 through screws;
the lightening groove surface of the emission secondary mirror 7 is arranged opposite to the secondary mirror backboard 6;
and the main mirror back plate 5 is stuck with a heater and a thermistor, and is sprayed with thermal control black paint.
The secondary mirror backboard 6 is adhered with a heater and a thermistor, the outer surface of the secondary mirror backboard is coated with a plurality of layers of heat insulation materials, the outer surface of the heat insulation materials adopts a carburized polyimide film, and the heat insulation materials have high absorptivity and high emissivity and surface optical properties, so that the influence of space stray light on an optical component can be reduced.
A heater and a thermistor are stuck to the transmitting lens barrel 1 and the main lens chamber 2, the thermal stability of the structure of the device is controlled, and the relative position change of the main lens and the secondary lens caused by temperature is reduced. The main lens chamber 2 and the lens barrel are made of carbon fiber materials, the surface optical properties of the main lens chamber and the lens barrel are high absorptivity and high emissivity, the thermal deformation coefficient is small, and the influence of stray light on an optical component is reduced, and meanwhile, the relative position change of the main lens and the secondary lens caused by temperature is reduced.
The emission lens barrel 1 is in a spindle shape, and according to the mirror surface angle, the emission main lens 4 is arranged at the wide part of the lens barrel, and the emission secondary lens 7 is arranged at the narrow part of the lens barrel. The main mirror back plate 5, the main mirror chamber 2, the transmitting lens cone 1 and the secondary mirror back plate 6 are stuck with heating plates and are sprayed with black paint; the main emission mirror 4, the main mirror chamber 2, the lens barrel 1 and the secondary mirror are stuck with thermistors and are sprayed with black paint;
the primary mirror back plate 5 and the secondary mirror back plate 6 are made of aluminum-based silicon carbide materials, so that the heating area is more uniform. The inner surface of the transmitting lens barrel 1 is coated with a black light absorption coating, so that reflection caused by stray light entering the lens barrel is reduced. The heating plates of the main lens chamber 2 and the emission lens barrel 1 are uniformly stuck along the circumferential direction and the axial direction, so that the thermal deformation of the main lens chamber 2 and the emission lens barrel 1 is reduced. Preferably, the thermistor adopts an MF61 thermistor, the sampling precision is high, and the high-precision temperature control requirement can be met. Preferably, the screw fixing mode of the primary mirror 4, the secondary mirror 7, the primary mirror back plate 5 and the secondary mirror back plate 6 adopts titanium alloy screws and polyimide gaskets, so that the temperature fluctuation of the primary mirror 4 and the secondary mirror 7 is further reduced.
Example 1
The present embodiment is a preferred example of the above basic embodiment, and as shown in fig. 1 to 5, the present embodiment provides an integrated high-precision temperature control device for a spatial optical emitter, which includes an emitter tube 1, a main mirror chamber 2, a secondary mirror mounting plate 3, an emitter main mirror 4, a main mirror back plate 5, a secondary mirror back plate 6, and an emitter secondary mirror 7.
The main emission mirror 4 and the main mirror back plate 5 are fixed in the main mirror chamber 2 through screws on flange surfaces, a lightening groove is formed in the back of the main emission mirror 4, the lightening groove surface is installed opposite to the position of the main mirror back plate 5, a thermistor is stuck in the lightening groove after the main emission mirror 4 is backed, an electric heater is stuck on the main mirror back plate 5, and thermal control black paint E51-M is sprayed to control temperature fluctuation and temperature gradient of the main emission mirror 4 through radiation. The end face of the main lens chamber 2 is fixedly connected with the end face of one side of the transmitting lens barrel 1 through screws.
The transmitting secondary mirror 7 is fastened on the other side of the transmitting lens barrel 1 through a secondary mirror mounting plate. The sub-mirror back plate 6 is fixed on the outermost surface of the emission barrel 1 by screws. The back of the secondary mirror 7 is provided with a lightening groove, the lightening groove surface and the back of the main mirror back plate 6 are oppositely arranged, a thermistor is stuck in the lightening groove after the secondary mirror 7 is in back of the secondary mirror, an electric heater is stuck on the back plate 6 of the secondary mirror, and thermal control black paint E51-M is sprayed to control the temperature fluctuation and the temperature gradient of the secondary mirror 7 through radiation. The outer surface of the secondary mirror backboard 6 is coated with a multi-layer heat insulation component, the multi-layer outer surface film is a F46 silver-plated secondary surface mirror, the outer heat flow is shielded, and the influence of the outer heat flow on the temperature fluctuation of the emission secondary mirror 7 is reduced.
Lightening grooves are uniformly distributed on the main lens chamber 2 and the transmitting lens cone 1 for lightening, thermistors and electric heaters are stuck in the lightening grooves, temperature fluctuation and temperature gradient of the main lens chamber 2 and the transmitting lens cone 1 are controlled, and thermal control black paint E51-M is sprayed. The low-reflectivity thermal control coating is sprayed inside the emission lens cone 1, so that the influence of stray light on the emission lens cone 1 is reduced. The embodiment couples the primary emission mirror 4, the secondary emission mirror 7, the primary mirror chamber 2 and the emission lens barrel 1, reduces the influence of heat flow and stray light outside the space on the optical component through the integrated design of active and passive thermal control, and ensures the temperature fluctuation and gradient of the optical component.
The space optical emission mirror integrated high-precision temperature control device integrates the temperature control of the main mirror and the secondary mirror with the stray light shielding and anti-reflection component, ensures the high-precision temperature control of the optical component and the stability of the relative positions of the optical components, and is very convenient to mount on a spacecraft due to the high integration of the device.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. The precise temperature control device of the space optical emission mirror is characterized by comprising an emission lens barrel (1), an emission main mirror (4), a main mirror back plate (5), a main mirror chamber (2), a secondary mirror mounting plate (3), an emission secondary mirror (7) and a secondary mirror back plate (6), wherein the emission main mirror (4) and the main mirror back plate (5) are oppositely arranged at two sides of the main mirror chamber (2), and the main mirror chamber (2) is fixedly arranged at one side of the emission lens barrel (1);
the secondary mirror (7) and the secondary mirror backboard (6) are oppositely arranged on two sides of the secondary mirror mounting plate (3), the secondary mirror mounting plate (3) is fixedly arranged on the other side of the emission lens cone (1), and the emission main mirror (4) and the emission secondary mirror (7) are arranged towards the inside of the emission lens cone (1) respectively and are provided with heating plates on the main mirror chamber (2), the emission lens cone (1), the main mirror backboard (5) and the secondary mirror backboard (6).
2. The precision temperature control device of the space optical emitter according to claim 1, wherein the emitting main mirror (4) and the main mirror back plate (5) are fixed in the main mirror chamber (2) through flange surface screws respectively;
the emission secondary mirror (7) and the secondary mirror backboard (6) are fixed on the secondary mirror mounting plate (3) through screws;
the end face of the main lens chamber (2) is fixedly connected with the end face of one side of the transmitting lens barrel (1) through screws.
3. The precise temperature control device of the space optical emitter according to claim 2, wherein the screw fixing modes of the emitting main mirror (4), the emitting secondary mirror (7), the main mirror back plate (5) and the secondary mirror back plate (6) are all fixed by adopting titanium alloy screws and polyimide gaskets.
4. The precise temperature control device of the space optical emitter according to claim 1, wherein a first lightening groove is formed in the back surface of the emitter main mirror (4), the position of the first lightening groove corresponds to the position of the main mirror back plate (5), and a thermistor is arranged in the first lightening groove;
a second lightening groove is formed in the back surface of the emission secondary mirror (7), the position of the second lightening groove corresponds to the position of the secondary mirror backboard (6), and a thermistor is arranged in the second lightening groove;
thermistors are arranged on the transmitting lens cone (1) and the main lens chamber (2).
5. The precise temperature control device of the space optical emitter according to claim 1, wherein the main mirror back plate (5), the main mirror chamber (2), the emitter tube (1) and the secondary mirror back plate (6) are all coated with thermal black paint.
6. The precise temperature control device of the space optical emitter according to claim 1, wherein the outer surface of the secondary mirror back plate (6) is coated with a heat insulation material, and the heat insulation material adopts a carburized polyimide film.
7. The precise temperature control device of the space optical emitter according to claim 1, wherein the main lens chamber (2) and the emitter tube (1) are made of carbon fiber materials;
the main mirror back plate (5) and the secondary mirror back plate (6) are made of aluminum-based silicon carbide materials.
8. The precise temperature control device of the space optical emitter according to claim 1, wherein the cross section of the emitter tube (1) is in a spindle shape, the emitter main mirror (4) is arranged in the middle of the spindle shape, and the emitter sub mirror (7) is arranged at the tip of the spindle shape.
9. The precise temperature control device of the space optical emitter according to claim 1, wherein the inner surface of the emitter tube (1) is sprayed with a black light absorbing coating.
10. The precision temperature control device of the space optical emitter according to claim 1, wherein a plurality of heating plates are adhered to the main lens chamber (2) and the emitter tube (1), and the plurality of heating plates are uniformly adhered along the circumferential directions of the main lens chamber (2) and the emitter tube (1) and are uniformly adhered along the length extension directions of the main lens chamber (2) and the emitter tube (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311748624.7A CN117724222A (en) | 2023-12-18 | 2023-12-18 | Precise temperature control device of space optical emission mirror |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311748624.7A CN117724222A (en) | 2023-12-18 | 2023-12-18 | Precise temperature control device of space optical emission mirror |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117724222A true CN117724222A (en) | 2024-03-19 |
Family
ID=90203074
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311748624.7A Pending CN117724222A (en) | 2023-12-18 | 2023-12-18 | Precise temperature control device of space optical emission mirror |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117724222A (en) |
-
2023
- 2023-12-18 CN CN202311748624.7A patent/CN117724222A/en active Pending
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