CN113497360A - High-precision profile control thermal control structure of zero-transmission solar screen and satellite-borne antenna reflector - Google Patents
High-precision profile control thermal control structure of zero-transmission solar screen and satellite-borne antenna reflector Download PDFInfo
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- CN113497360A CN113497360A CN202110566702.6A CN202110566702A CN113497360A CN 113497360 A CN113497360 A CN 113497360A CN 202110566702 A CN202110566702 A CN 202110566702A CN 113497360 A CN113497360 A CN 113497360A
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- 239000002131 composite material Substances 0.000 claims abstract description 20
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- 229920001721 polyimide Polymers 0.000 claims description 21
- 239000004642 Polyimide Substances 0.000 claims description 17
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- 229910052732 germanium Inorganic materials 0.000 claims description 8
- GNPVGFCGXDBREM-UHFFFAOYSA-N germanium atom Chemical compound [Ge] GNPVGFCGXDBREM-UHFFFAOYSA-N 0.000 claims description 8
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 2
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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
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- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Aerials With Secondary Devices (AREA)
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Abstract
星载天线反射器高精度型面控制热控结构可对天线反射器在轨进行高型面精度控制，包含零透射太阳屏、低吸收低发射热控涂层、复合热控多层结构。零透射太阳屏布置在天线反射器射频口面，实现既可透射通信用电磁波、又可隔绝空间太阳辐射热流的功能；具有加热功能的多层隔热组件铺设在反射器非射频工作面，实现既可隔绝空间冷黑环境又可对反射器进行热量补偿的功能；低吸收低发射热控涂层用于调节反射器的表面属性，进一步削弱反射器通过与太阳屏热交换向空间冷黑环境的热量损失。该复合热控结构可将星载天线反射器的在轨温度由现阶段的‑160℃～+115℃缩窄至‑40℃～+60℃，大幅度减小反射器在轨热变形进而实现高型面精度控制。
The spaceborne antenna reflector high-precision profile control thermal control structure can control the antenna reflector on-orbit with high profile precision, including zero transmission solar screen, low absorption and low emission thermal control coating, and composite thermal control multilayer structure. The zero-transmission solar screen is arranged on the RF port surface of the antenna reflector to achieve the function of transmitting electromagnetic waves for communication and isolating the heat flow of solar radiation in space; It can not only isolate the cold and dark environment of the space, but also perform heat compensation for the reflector; the low absorption and low emission thermal control coating is used to adjust the surface properties of the reflector, which further weakens the reflector to the cool and dark space of the space through heat exchange with the solar screen. heat loss. The composite thermal control structure can narrow the on-orbit temperature of the spaceborne antenna reflector from -160℃～+115℃ at the current stage to -40℃～+60℃, and greatly reduce the on-orbit thermal deformation of the reflector to realize High profile precision control.
Description
Technical Field
The invention relates to a zero-transmission solar screen and a thermal control structure capable of realizing on-orbit high-profile precision control of an antenna reflector, and belongs to the technical field of space equipment.
Background
The high-flux satellite has higher and higher requirements on the on-track profile precision of the multi-beam antenna reflector, and the profile change can cause the problems of antenna gain loss, directional diagram change and the like. The profile accuracy of the solid reflector is influenced by two factors of production, manufacturing and assembly errors and on-track thermal deformation. Along with technical improvements of materials, processes and the like, errors caused by production, manufacturing and assembly are smaller and smaller, thermal deformation becomes a main factor causing the profile change of the antenna on-track reflector, and the size of the thermal deformation of the antenna reflector is positively correlated with the temperature range of the antenna on the track.
The composite material reflector at the present stage has the rail temperature range of-160-115 ℃, and the temperature difference between the highest temperature and the lowest temperature of the reflector compared with the normal temperature is 95 ℃ and 180 ℃. The profile change caused by thermal deformation in the temperature range cannot meet the requirement of the high-precision multi-beam antenna, and the problem is more and more serious along with the improvement of the communication frequency band. The solar radiation heat flow is the main reason of the temperature rise of the spacecraft on the orbit, and the reason of the high temperature of the reflector on the orbit is that the isolation degree of the antenna thermal control measures to the orbit solar radiation heat flow is insufficient. The space environment can be equivalently regarded as a black body with the temperature of 3K, and when the antenna is not irradiated by the sun in orbit, the heat leakage of the antenna to the space environment causes the temperature of the antenna to be lower; if the isolation degree of the antenna thermal control to the space cold and black environment is insufficient, the temperature of the antenna in the in-orbit non-illuminated arc section will drop too fast to be too low. In addition, if the isolation degree of the space cold and black environment and the space external heat flow is insufficient, the on-track non-uniform irradiation causes the temperature gradient inside the antenna to be large, and further causes the profile to change too much.
Disclosure of Invention
The technical problem solved by the invention is as follows: the solar screen can completely isolate solar electromagnetic radiation in a thermal effect spectrum range, and radio waves for on-orbit spacecraft communication can freely pass through the solar screen. Therefore, the zero-transmission solar screen can be used for a radio frequency working surface of aerospace communication equipment, and the situation that the temperature is too high due to the fact that orbital solar heat flow directly reaches the equipment is prevented. On the basis, the thermal control structure for the on-orbit high-precision profile control of the antenna reflector is provided, the antenna reflector is isolated from the space cold and black environment and the space solar external heat flow to the maximum extent by the thermal control structure, and the thermal control structure has a certain temperature compensation function.
The technical solution adopted by the invention is as follows: a zero-transmission solar screen comprises a black polyimide base film and a germanium-plated layer; when the solar energy radio wave transmission device is used, the germanium plating layer faces to the space environment, and the germanium plating layer and the black polyimide film isolate energy transmission with heat effect in solar electromagnetic radiation and allow radio wave transmission for communication.
The thickness of the black polyimide-based film is 25-100 mu m.
The thickness of the germanium-plated layer is less than 6 μm.
A thermal control structure for high-precision profile control of a satellite-borne antenna reflector comprises a zero-transmission solar screen, a composite thermal control multilayer structure, a fixed structure and a low-absorption low-emission thermal control coating; the zero-transmission solar screen is arranged on the radio frequency port surface of the antenna reflector; the composite thermal control multilayer structure is arranged on the non-radio frequency port surface of the antenna reflector through a fixing structure; spraying a low-absorption low-emission thermal control coating on the radiation opening surface of the antenna reflector; the composite thermally controlled multilayer structure achieves thermal compensation of the antenna reflector through infrared radiation.
The composite heat control multilayer structure comprises a flexible heating film group and a heat control multilayer; the flexible heating film group faces the antenna emitter.
The flexible heating module comprises a polyimide heating layer and upper and lower polyimide insulating layers.
The low-absorption low-emission thermal control coating adopts a low-absorption low-emission SAL-1 thermal control coating and comprises an organic silicon binder and metal aluminum powder.
Compared with the prior art, the invention has the advantages that:
(1) the solar screen has high isolation degree to solar radiation heat flow: the zero-transmission solar screen can completely isolate partial energy with thermal effect in solar electromagnetic radiation, and well solves the problem of high temperature of the space equipment caused by solar heat flow in the direction of a radio frequency channel.
(2) The thermal control structure of the invention makes the on-track temperature range of the reflector narrower: because the zero-transmission solar screen isolates the space solar radiation heat flow, and simultaneously, the radiation heat resistance of the reflector and the space cold and black space is very large, the comprehensive effect of the reflector and the space cold and black space narrows the on-rail temperature range of the reflector in a large range.
(3) The thermal control structure of the invention ensures that the temperature stability of the reflector is good and the uniformity is high: because the thermal control structure greatly isolates the influence of heat flow outside the space and cold and black environment of the space on the reflector, the temperature fluctuation rate of the reflector on the rail is small, and the temperature stability is high; meanwhile, the local temperature of the reflector is slightly influenced by factors such as local illumination or shielding, and the temperature uniformity of the reflector is good.
(4) The thermal control structure of the invention ensures that the precision of the reflector on the rail profile is high: the thermal deformation is in direct proportion to the deviation degree of the on-track temperature of the reflector and the ground normal temperature, and the on-track temperature range of the reflector is narrowed by the thermal control structure, so that the on-track profile precision of the reflector is higher. Meanwhile, the temperature stability and the temperature uniformity of the reflector under the thermal control structure are better than those of the prior art, and the on-orbit high-profile precision of the reflector is favorably maintained.
(5) The invention ensures that the low-temperature profile precision of the antenna reflector is controllable: under the thermal control structure, the deviation degree of the reflector at the rail limit low temperature compared with the ground normal temperature is the largest, and the limit low temperature level and the limit low temperature profile variable quantity of the reflector can be controlled by adjusting the working temperature threshold range of the heating film group. Because the heating film group uniformly carries out heat compensation on the reflector through infrared radiation, no additional temperature gradient is caused.
Drawings
FIG. 1 is a schematic diagram of a zero transmission solar panel;
FIG. 2 is a schematic diagram of a high-precision profile control thermal control structure of a satellite-borne antenna reflector;
FIG. 3 shows the result of the measurement of the transmittance of electromagnetic waves in the spectral range of 250nm to 2500nm of the zero-transmission solar panel;
FIG. 4 shows the insertion loss test result of the zero-transmission solar screen in the range of 18 GHz-24 GHz;
FIG. 5 shows the insertion loss test result in the range of 28 GHz-35 GHz for the zero-transmission solar panel.
Detailed Description
The present invention will be described with reference to the accompanying drawings.
As shown in fig. 1, a zero transmission solar panel 3 comprises a black polyimide base film 1 and a germanium-plated layer 2. The thickness of the black polyimide base film 1 is 25-100 mu m, and the black polyimide base film can be selected according to the mechanical property requirement; the thickness of the germanium-plated layer 2 is less than 6 microns, and the main function is to change the surface thermo-optical property of the black polyimide base film 1 on the premise of not influencing the penetrating performance of electromagnetic waves for spacecraft communication.
When the zero-transmission solar screen 3 is used, the germanium-plated layer 2 faces to the space environment, and the sequential combined action of the germanium-plated layer 2 and the black polyimide film 1 isolates energy transmission with thermal effect in solar electromagnetic radiation, but radio waves for communication can freely transmit.
As shown in fig. 2, the high-precision profile-controlled thermal control structure of the satellite-borne antenna reflector comprises a zero-transmission solar screen 3, a composite thermal control multilayer structure 5, a fixed structure 6 and a low-absorption low-emission thermal control coating;
the zero transmission solar screen 3 is arranged at the radio frequency port face of the antenna reflector 4: the zero-transmission solar screen 3 isolates the solar radiation heat flow in the direction of the working surface (namely the radio frequency port surface) of the antenna reflector 4, and meanwhile, the transmission of working radio waves of the frequency band antenna such as Ku, Ka and QV is not influenced.
The composite thermally controlled multilayer structure 5 is arranged on the non-radio frequency aperture side of the antenna reflector 4 by means of a fixing structure 6: the composite thermal control multilayer structure 5 can prevent the antenna reflector 4 from being heated by solar radiation heat flow in the direction of the non-working surface (namely, the non-radio frequency port surface) of the antenna reflector 4, and simultaneously, the temperature reduction of the antenna reflector 4 caused by the space cold and black environment is avoided in the direction of the non-working surface of the antenna reflector 4.
The heat exchange of the antenna reflector 4 with the space environment is mainly due to the radiative heat exchange of its working face with the zero transmission solar screen 3; in order to weaken the radiation heat transfer between the antenna reflector 4 and the zero-transmission solar screen 3, the working surface of the antenna reflector 4 is sprayed with a low-absorption low-emission thermal control coating, so that the radiation heat exchange thermal resistance between the antenna reflector 4 and the zero-transmission solar screen 3 is increased. The low-absorption low-emission thermal control coating adopts a low-absorption low-emission SAL-1 thermal control coating and consists of an organic silicon binder and metal aluminum powder.
In order to prevent the antenna reflector 4 from being low in rail temperature, the flexible heating film group and the heat control multilayer are combined to form the composite heat control multilayer structure 5, and when the composite heat control multilayer structure is used, the flexible heating film group faces the antenna emitter 4, and the heat control multilayer faces outwards. The flexible heating module consists of a polyimide heating layer and an upper polyimide insulating layer and a lower polyimide insulating layer. The flexible heating film group and the thermal control multilayer are designed, manufactured and implemented simultaneously, and uniform heat compensation of the antenna reflector 4 is realized through infrared radiation on the premise of not influencing the isolation effect between the flexible heating film group and the space environment.
A composite thermal control structure based on a zero-transmission solar screen 3 can perform high-profile precision control on an antenna reflector 4 in orbit, and comprises the zero-transmission solar screen 3, a low-absorption low-emission thermal control coating and a composite thermal control multilayer structure 5. The zero-transmission solar screen 3 is arranged on the radio frequency opening surface of the antenna reflector 4, so that the function of transmitting electromagnetic waves for communication and isolating space solar radiation heat flow is realized; the composite thermal control multilayer structure 5 is laid on a non-radio frequency working surface of the reflector, so that the function of isolating a space cold and black environment and performing heat compensation on the reflector is realized; the low absorption low emission thermal control coating is used to adjust the surface properties of the antenna reflector 4, further attenuating the heat loss of the antenna reflector 4 to the cold black environment of the space through heat exchange with the zero transmission solar screen 3. The composite thermal control structure can narrow the on-track temperature of the satellite-borne antenna reflector 4 from minus 160 ℃ to plus 115 ℃ at the present stage to minus 40 ℃ to plus 60 ℃, greatly reduce the on-track thermal deformation of the reflector and further realize high-profile precision control.
The performance test result of the zero-transmission solar screen 3 is as follows:
in order to verify the performance of the zero-transmission solar screen 3, the electromagnetic wave isolation performance of the zero-transmission solar screen 3 with a thermal effect spectrum band in solar electromagnetic radiation and the radio wave penetration performance for satellite communication are tested. Fig. 3 shows the result of the transmission performance test of the zero-transmission solar screen 3 on electromagnetic waves in the range of 250nm to 2500nm, and the isolation degree of the zero-transmission solar screen 3 on the electromagnetic waves in the wave band range reaches more than 99.5%. Fig. 4 and 5 are insertion loss test results of the zero-transmission solar screen 3 in Ku, Ka, and Qv communication frequency bands, and the maximum insertion loss is less than 0.2 dB.
The high-precision molded surface of the satellite-borne antenna reflector controls the thermal control structure performance:
the antenna reflector 4 is subjected to a limit low-temperature heat balance test under the condition of using the high-precision profile control thermal control structure of the satellite-borne antenna reflector disclosed by the invention, and the supplementary heat flux density is 50W/m2The limit low temperature of the antenna reflector 4 is above-40 ℃.
The temperature of the antenna reflector 4 in the rail is simulated and calculated by using the test data, and the maximum temperature of the antenna reflector 4 is lower than 60 ℃.
Parts of the invention not described in detail are well known to the person skilled in the art.
Claims (10)
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| US5373305A (en) * | 1992-05-19 | 1994-12-13 | Martin Marietta Corporation | RF-transparent antenna sunshield membrane |
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2021
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Application publication date: 20211012 |