CN111930163B - Satellite-borne single machine differential temperature control system and method - Google Patents
Satellite-borne single machine differential temperature control system and method Download PDFInfo
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- CN111930163B CN111930163B CN202010823444.0A CN202010823444A CN111930163B CN 111930163 B CN111930163 B CN 111930163B CN 202010823444 A CN202010823444 A CN 202010823444A CN 111930163 B CN111930163 B CN 111930163B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/30—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature
- G05D23/32—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature with provision for adjustment of the effect of the auxiliary heating device, e.g. a function of time
Abstract
The invention provides a satellite-borne single machine differential temperature control system and a method, which comprises the following steps: a first stand-alone module configured to conduct heat with a spacecraft mounting plate; a second stand-alone module configured to conduct heat between the radiator and the closed-loop conduction module; the maximum normal working temperature of the components of the second single-machine module is lower than that of the components of the first single-machine module; and the minimum normal working temperature of the components of the second single machine module is greater than the minimum normal working temperature of the components of the first single machine module.
Description
Technical Field
The invention relates to the technical field of aerospace application, in particular to a satellite-borne single-machine differential temperature control system and method.
Background
The satellite thermal control technology aims to control the heat exchange process of the internal environment and the external environment of a satellite and achieve the purpose that the thermal balance temperature of equipment on the satellite is in a required range. The thermal control technology is an important component of the aerospace technology, and the design level and quality of the thermal control technology affect the working state, service life and reliability of the whole satellite. With the continuous development of the aerospace technology, the application range of the satellite is gradually expanded, and the effective load on the satellite varies greatly due to different functions, so that the satellite thermal control technology continuously faces new challenges.
In the process of designing the satellite-borne single machine of the spacecraft, temperature design needs to be carried out on different modules in the single machine, and due to the limitation of functional requirements, heat consumption and temperature requirements of all the modules in the spacecraft, the thermal control requirements of the different functional modules need to be comprehensively considered in the design process.
In the aspect of the on-rail temperature control technology of the spacecraft satellite-borne single machine, the method is generally adopted to control the temperature of the mounting surface of the satellite-borne single machine. With the continuous development and progress of the aerospace technology, the functions of a single machine for assembling spacecrafts such as satellites and the like are diversified day by day, and because different components in the single machine have different temperature requirements, the single machine is generally designed by adopting the maximum envelope of the working, starting and storing temperature ranges of the components in the design process of the single machine. The general electronics device can bear comparatively abominable temperature range, if carry some components and parts that have special temperature control demand in the unit, comparatively special temperature control demand such as lower operating temperature upper limit, start and storage temperature lower limit, temperature stability, temperature homogeneity and temperature rising and falling speed. According to the existing single-machine thermal control design concept, the temperature control strategy of the whole single machine is strict, and unnecessary resource waste is caused to temperature control.
The conventional satellite-borne single-machine thermal control design mode is that structural layout among modules in a single machine is carried out according to different module temperature requirements carried by the single machine, the module with high heat consumption needs to be installed near a single machine installation surface, an optimal heat dissipation path is provided for the module, the module with special temperature requirements generally adopts good thermal contact with a heat exchange surface, and the temperature of the modules in the single machine is controlled by controlling the boundary temperature of the heat exchange surface. The main defects of the design mode are that the temperature control of a single machine interface is limited by a temperature sensitive device, and all single machines are required to be controlled in a more severe temperature range. Most of the conventional satellite-borne single machines are electronic components, and the components can bear higher working temperature and lower storage temperature. According to the law of thermodynamics and the thermal control design principle of the spacecraft, the stricter the boundary temperature control requirement is, the more thermal control resources are needed, including heat dissipation channel resources, power resources and the like. This results in an increase in the overall demand due to the local demand, resulting in unnecessary waste of resources.
Disclosure of Invention
The invention aims to provide a satellite-borne single machine differential temperature control system and method, and aims to solve the problem that the on-orbit temperature control efficiency of the existing spacecraft satellite-borne single machine is low.
In order to solve the above technical problem, the present invention provides a satellite-borne single-machine differential temperature control system, which comprises:
a first stand-alone module configured to conduct heat with a spacecraft mounting plate;
a second stand-alone module configured to conduct heat between the radiator and the closed-loop conduction module;
the maximum normal working temperature of the components of the second single-machine module is lower than that of the components of the first single-machine module;
and the minimum normal working temperature of the components of the second single machine module is greater than the minimum normal working temperature of the components of the first single machine module.
Optionally, in the satellite-borne standalone differentiated temperature control system, the method includes:
a thermal insulation device disposed between the first stand-alone module and the second stand-alone module, configured to conduct or insulate heat between the first stand-alone module and the second stand-alone module;
and the heat conductivity coefficient of the material of the heat insulation device is set according to the heat exchange quantity requirement between the first single machine module and the second single machine module.
Optionally, in the system for controlling the differential temperature of the satellite-borne stand-alone unit, the closed-loop conducting module is configured to adjust the temperature of the second stand-alone unit according to a normal operating temperature range of components of the second stand-alone unit, and includes:
heat transfer means arranged to be connected between said second stand-alone module and said radiator;
a temperature measuring device disposed on the heat transfer device configured to measure a temperature of the heat transfer device;
a heating device disposed on the heat transfer device configured to heat the heat transfer device according to a measurement result of the temperature measuring device.
Optionally, in the satellite-borne single-machine differential temperature control system, the heat transfer device penetrates through the spacecraft mounting plate;
the spacecraft mounting plate is provided with a heat transfer hole, and the heat transfer device extends out of the cold black space from the heat transfer hole.
Optionally, in the satellite-borne single-machine differential temperature control system, the radiator is arranged at one end of the heat transfer device, which is located outside the cold and black space; the radiator is the metal sheet, and the surface spraying of metal sheet is hanged down to absorb high emissivity thermal control coating material, the radiator is used for to cold black space heat dissipation consumption.
Optionally, in the satellite-borne single-machine differential temperature control system,
the installation mode between the first single-machine module and the spacecraft installation plate is adjusted according to the normal working temperature range of components of the first single-machine module;
and the installation mode between the second single machine module and the heat transfer device is adjusted according to the normal working temperature range of the components of the second single machine module.
Optionally, in the satellite-borne single-machine differential temperature control system, the first single-machine module and the spacecraft mounting plate are filled with heat-conducting silicone grease or a heat-conducting pad, and the second single-machine module and the heat transfer device are mounted in a complete thermal contact manner.
The invention also provides a satellite-borne single machine differential temperature control method, which comprises the following steps:
heat is conducted between the first single-machine module and the spacecraft mounting plate;
the second single machine module conducts heat with the radiator through the closed-loop conduction module;
the maximum normal working temperature of the components of the second single-machine module is lower than that of the components of the first single-machine module;
and the minimum normal working temperature of the components of the second single machine module is greater than the minimum normal working temperature of the components of the first single machine module.
According to the satellite-borne single-machine differential temperature control system and method, heat is conducted between the first single-machine module and the spacecraft mounting plate, the second single-machine module conducts heat between the closed-loop conduction module and the radiator, the maximum normal working temperature of components of the second single-machine module is lower than the maximum normal working temperature of the components of the first single-machine module, the minimum normal working temperature of the components of the second single-machine module is higher than the minimum normal working temperature of the components of the first single-machine module, the second single-machine module which is more sensitive to temperature is independently subjected to temperature control on the premise that constraint conditions such as single-machine mounting space are not increased, and control accuracy is improved; the invention can reduce the thermal control resource requirement of the first single machine module in the thermal control design process, eliminate the influence of the second single machine module which is locally sensitive to the temperature on the thermal design of the whole machine, greatly reduce the thermal control resource requirement of the conventional thermal design method on two single machines and a spacecraft platform, and can more directly and respectively control the temperature levels of the two single machines.
Drawings
FIG. 1 is a schematic front view of a satellite-borne single-machine differential temperature control system according to an embodiment of the present invention;
FIG. 2 is a schematic side view of a satellite-borne single-machine differential temperature control system according to an embodiment of the present invention;
shown in the figure: 1-a second stand-alone module; 2-a heat transfer device; 3-a first stand-alone module; 4-a spacecraft mounting plate; 5-heat transfer holes; 6-a radiator; 7-a thermal insulation device; 8-a temperature measuring device; 9-heating device.
Detailed Description
The satellite-borne single-machine differential temperature control system and method provided by the invention are further described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
The core idea of the invention is to provide a system and a method for controlling the on-orbit temperature of a satellite borne single machine, so as to solve the problem of low on-orbit temperature control efficiency of the existing spacecraft satellite borne single machine.
According to the law of thermodynamics and the principle of single-machine thermal design of a spacecraft, the main constraint of single-machine thermal control design is the working temperature index of a device. In the field of spacecraft single machine thermal control design, a single machine mounting surface is generally used as a single machine heat dissipation channel. Taking the maximum temperature working index of the module as an example, assuming that the upper limit of the working temperature of a common conventional electronic module is A, if a temperature sensitive unit exists in a single machine or the upper limit of the working temperature of the module is B, the temperature of the whole machine is required to be controlled not to exceed B in the thermal design process of the single machine. According to the heat radiation principle, the lower the temperature control target is, the lower the radiation heat dissipation capacity thereof is, the larger heat dissipation area needs to be provided by the spacecraft platform, and unnecessary resource waste of the spacecraft platform is caused. (other special temperature requirements can be known in the same way, such as low-temperature storage temperature, temperature stability, temperature rise and fall rate and the like). the satellite-borne single-machine differential temperature control method is a new single-machine heat control and design method provided on the basis of a conventional single-machine heat control design method, can greatly reduce unnecessary waste caused by the single machine of the spacecraft with the temperature requirement difference on heat control resources, and can more accurately and directly control the temperature of the temperature sensitive module.
In order to realize the idea, the invention provides a satellite-borne single-machine differential temperature control system and a method, wherein the system is shown in fig. 1-2 and comprises the following steps: a first single-machine module 3 configured to conduct heat with the spacecraft mounting plate 4; a second stand-alone module 1 configured to conduct heat between the radiator 6 and the closed-loop conduction module; the maximum normal working temperature of the components of the second single-machine module 1 is lower than the maximum normal working temperature of the components of the first single-machine module 3; the minimum normal working temperature of the components of the second single-machine module 1 is greater than the minimum normal working temperature of the components of the first single-machine module 3.
Specifically, in the satellite-borne single-machine differential temperature control system, the method includes: a thermal insulation means 7, arranged between said first stand-alone module 3 and said second stand-alone module 1, configured to conduct or insulate heat between said first stand-alone module 3 and said second stand-alone module 1; the thermal conductivity of the material of the thermal insulation means 7 is set according to the heat exchange capacity requirement between the first single-machine module 3 and the second single-machine module 1.
Further, in the satellite-borne single-machine differential temperature control system, the closed-loop conduction module is configured to adjust the temperature of the components of the second single-machine module 1 according to the normal working temperature range thereof, and includes: heat transfer means 2 arranged to be connected between said second stand-alone module 1 and said radiator 6; a temperature measuring device 8 arranged on the heat transfer device 2, configured to measure a temperature of the heat transfer device 2; a heating device 9 arranged on the heat transfer device 2, configured to heat the heat transfer device 2 according to the measurement result of the temperature measuring device 8.
In addition, in the satellite-borne single-machine differential temperature control system, the heat transfer device 2 penetrates through the spacecraft mounting plate 4; the spacecraft mounting plate 4 is provided with a heat transfer hole 5, and the heat transfer device 2 extends out of the cold black space from the heat transfer hole 5. The radiator 6 is arranged at one end of the heat transfer device 2 outside the cold black space; the radiator 6 is a metal plate, the surface of the metal plate is sprayed with a low-absorption high-emissivity thermal control coating material, and the radiator 6 is used for discharging heat dissipation to a cold black space.
In an embodiment of the invention, in the satellite-borne single-machine differential temperature control system, the installation manner between the first single-machine module 3 and the spacecraft mounting plate 4 is adjusted according to the normal working temperature range of components of the first single-machine module 3; the installation mode between the second single machine module 1 and the heat transfer device 2 is adjusted according to the normal working temperature range of the components of the second single machine module 1. Specifically, in the satellite-borne single-machine differential temperature control system, the first single-machine module 3 and the spacecraft mounting plate 4 are filled with heat-conducting silicone grease or heat-conducting pads, and the second single-machine module 1 and the heat transfer device 2 are mounted in a complete thermal contact manner.
The invention also provides a satellite-borne single machine differential temperature control method, which comprises the following steps: heat is conducted between the first single-machine module 3 and the spacecraft mounting plate 4; the second single machine module 1 conducts heat with the radiator 6 through the closed-loop conduction module; the maximum normal working temperature of the components of the second single-machine module 1 is lower than the maximum normal working temperature of the components of the first single-machine module 3; the minimum normal working temperature of the components of the second single-machine module 1 is greater than the minimum normal working temperature of the components of the first single-machine module 3.
The invention relates to a satellite-borne single machine differential temperature control method, which mainly comprises a first single machine module, a second single machine module, a heat insulation device, a heat transfer module and a radiator module. The heat-insulating device can be a full-heat-insulating material or a semi-heat-insulating material, is positioned between the second single-machine module sensitive to the thermal control requirement and the first single-machine module so as to realize that the second single-machine module is incompatible with the temperature of other equipment, adjusts the heat exchange quantity between the heat-insulating device and the first single-machine module and between the heat-insulating device and the second single-machine module in a way of partially changing the heat conduction coefficient of the installation material or the thermal contact surface, is a heat pipe or other metal materials with good heat conduction performance, is mainly used for transferring heat to a radiator, and is a metal plate sprayed with a specified surface property coating and used for discharging heat loss to a cold and black space. The heat dissipation method has the characteristics of high reliability, high space utilization rate, simple installation, safety, reliability, heat control design resource saving and the like.
In the satellite-borne single-machine differential temperature control system and method provided by the invention, through heat conduction between the first single-machine module 3 and the spacecraft mounting plate 4, the second single-machine module 1 is through heat conduction between the closed-loop conduction module and the radiator 6, the maximum normal working temperature of the components of the second single-machine module 1 is less than the maximum normal working temperature of the components of the first single-machine module 3, and the minimum normal working temperature of the components of the second single-machine module 1 is greater than the minimum normal working temperature of the components of the first single-machine module 3, so that the second single-machine module 1 which is more sensitive to temperature is independently subjected to temperature control on the premise of not increasing constraint conditions such as single-machine mounting space and the like, and the control precision is improved; the invention can reduce the thermal control resource requirement of the first single machine module 3 in the thermal control design process, eliminate the influence of the second single machine module 1 which is locally sensitive to the temperature on the thermal design of the whole machine, greatly reduce the thermal control resource requirement of the conventional thermal design method for two single machines and a spacecraft platform, and can more directly and respectively control the temperature levels of the two single machines.
In one implementation, the first stand-alone module is required to be installed in a heat-conducting manner with the heat-dissipating surface of the spacecraft mounting plate, and serves as a heat-dissipating path for the conventional electronics module inside the first stand-alone module.
In a specific implementation process, the installation mode of the second single-machine module can be determined as a thermal insulation installation (thermal insulation cushion block), a semi-thermal insulation installation (metal cushion block), a direct contact installation or the like according to thermal simulation analysis.
In one embodiment, the heat transfer device may be installed by thermally coupling a heat pipe or a high thermal conductivity metal to the second stand-alone module, so as to transfer the heat thereof to the radiator outside the cabin.
In a specific implementation process, the heat transfer device is installed on the first single machine module in a heat insulation installation mode except for being installed with the second single machine module in a heat conduction mode, so that the mechanical condition is met.
In a specific implementation process, a heat transfer device penetration hole is required to be formed in a single aircraft installation surface, so that the heat transfer device is convenient.
In one embodiment, the surface of the radiator outside the cabin can be pasted with a cerium glass silvered secondary surface mirror or a thermal white paint, so as to dissipate heat consumption to the space environment.
In conclusion, the method has the advantages of strong temperature control capability, small occupied space, simple process, good stability, safety, reliability and the like. The heat dissipation device can be widely used for solving the heat dissipation problem of a high-power density single machine carried on spacecrafts such as navigation satellites, communication satellites, high-power density microsatellites, manned spacecrafts, space stations and the like in a long-time full-power working state.
According to the invention, the temperature-sensitive module (second single machine module 1) in the main single machine (first single machine module 3) is used as an auxiliary module of the main single machine (first single machine module 3) for independent thermal design, the thermal coupling relation between the main single machine and the temperature-sensitive module can be designed and determined through simulation analysis, the heat-radiating channel of the temperature-sensitive module 1 is expanded into a way of directly exchanging heat with the space environment outside a cabin by using the heat-transfer device 2 and the heat-transfer holes 5, the radiator 6 can be more provided with the heat consumption of the temperature-sensitive module and the temperature control target for area design, a cerium glass silver-plated secondary surface mirror or thermal white paint is pasted on the two sides of the radiator to increase the heat-radiating efficiency of the radiator, and the temperature measuring device 8 and the heating component control the temperature of the heat-sensitive module 1 through the closed.
In summary, the above embodiments describe in detail different configurations of the satellite-borne standalone differentiated temperature control system, and it goes without saying that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications based on the configurations provided in the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (7)
1. A satellite-borne single machine differential temperature control system is characterized by comprising:
a first stand-alone module configured to conduct heat with a spacecraft mounting plate;
a second stand-alone module configured to conduct heat between the radiator and the closed-loop conduction module;
the maximum normal working temperature of the components of the second single-machine module is lower than that of the components of the first single-machine module;
the minimum normal working temperature of the components of the second single-machine module is greater than the minimum normal working temperature of the components of the first single-machine module;
a thermal insulation device disposed between the first stand-alone module and the second stand-alone module, configured to conduct or insulate heat between the first stand-alone module and the second stand-alone module;
and the heat conductivity coefficient of the material of the heat insulation device is set according to the heat exchange quantity requirement between the first single machine module and the second single machine module.
2. The on-board stand-alone differential temperature control system according to claim 1, wherein the closed-loop conduction module is configured to adjust the temperature of the components of the second stand-alone module according to their normal operating temperature range, and comprises:
heat transfer means arranged to be connected between said second stand-alone module and said radiator;
a temperature measuring device disposed on the heat transfer device configured to measure a temperature of the heat transfer device;
a heating device disposed on the heat transfer device configured to heat the heat transfer device according to a measurement result of the temperature measuring device.
3. The on-board stand-alone differential temperature control system according to claim 2, wherein the heat transfer device penetrates through the spacecraft mounting plate;
the spacecraft mounting plate is provided with a heat transfer hole, and the heat transfer device extends out of the cold black space from the heat transfer hole.
4. The on-board stand-alone differential temperature control system according to claim 3, wherein the radiator is disposed at an end of the heat transfer device located outside the cold-black space; the radiator is the metal sheet, and the surface spraying of metal sheet is hanged down to absorb high emissivity thermal control coating material, the radiator is used for to cold black space heat dissipation consumption.
5. The on-board stand-alone differential temperature control system according to claim 2,
the installation mode between the first single-machine module and the spacecraft installation plate is adjusted according to the normal working temperature range of components of the first single-machine module;
and the installation mode between the second single machine module and the heat transfer device is adjusted according to the normal working temperature range of the components of the second single machine module.
6. The on-board stand-alone differential temperature control system according to claim 5, wherein the first stand-alone module is filled with a heat-conducting silicone grease or a heat-conducting pad, and the second stand-alone module is installed in complete thermal contact with a heat transfer device.
7. A satellite-borne single machine differential temperature control method is characterized by comprising the following steps:
heat is conducted between the first single-machine module and the spacecraft mounting plate;
the second single machine module conducts heat with the radiator through the closed-loop conduction module;
the maximum normal working temperature of the components of the second single-machine module is lower than that of the components of the first single-machine module;
the minimum normal working temperature of the components of the second single-machine module is greater than the minimum normal working temperature of the components of the first single-machine module;
arranging a heat insulation device between the first stand-alone module and the second stand-alone module to conduct or insulate heat between the first stand-alone module and the second stand-alone module;
and the heat conductivity coefficient of the material of the heat insulation device is set according to the heat exchange quantity requirement between the first single machine module and the second single machine module.
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| CN202110655017.0A CN113359908B (en) | 2020-08-17 | 2020-08-17 | Spacecraft satellite-borne single machine on-orbit temperature control system and method |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103458657A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Heat dissipation system of large-power consumption stand-along device on satellite |
| CN104816839A (en) * | 2015-04-22 | 2015-08-05 | 上海微小卫星工程中心 | Satellite platform modular thermal control device |
| CN105346737A (en) * | 2015-11-30 | 2016-02-24 | 中国空间技术研究院 | Heat control method of laser device of GEO satellite |
| CN105383714A (en) * | 2015-11-27 | 2016-03-09 | 上海卫星工程研究所 | Satellite borne active temperature control system |
| CN105744804A (en) * | 2016-03-29 | 2016-07-06 | 上海卫星工程研究所 | Temperature control system of high-heat consumption and high-stability single machine |
| CN109324648A (en) * | 2018-12-07 | 2019-02-12 | 银河航天(北京)通信技术有限公司 | A kind of method of temperature control system, spacecraft and spacecraft temperature control |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE1007977A6 (en) * | 1994-01-05 | 1995-11-28 | Verhaert Paul | Modular radiator system for heat transmission in space |
| CN104369876B (en) * | 2014-10-31 | 2016-04-27 | 上海卫星工程研究所 | Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus |
| CN106184825B (en) * | 2016-09-18 | 2018-04-06 | 电子科技大学 | A kind of method for improving fast respone space moonlet thermal control ability |
| CN108146660B (en) * | 2017-12-01 | 2019-09-17 | 北京空间技术研制试验中心 | A kind of spacecraft thermal control management system |
-
2020
- 2020-08-17 CN CN202010823444.0A patent/CN111930163B/en active Active
- 2020-08-17 CN CN202110655017.0A patent/CN113359908B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103458657A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Heat dissipation system of large-power consumption stand-along device on satellite |
| CN104816839A (en) * | 2015-04-22 | 2015-08-05 | 上海微小卫星工程中心 | Satellite platform modular thermal control device |
| CN105383714A (en) * | 2015-11-27 | 2016-03-09 | 上海卫星工程研究所 | Satellite borne active temperature control system |
| CN105346737A (en) * | 2015-11-30 | 2016-02-24 | 中国空间技术研究院 | Heat control method of laser device of GEO satellite |
| CN105744804A (en) * | 2016-03-29 | 2016-07-06 | 上海卫星工程研究所 | Temperature control system of high-heat consumption and high-stability single machine |
| CN109324648A (en) * | 2018-12-07 | 2019-02-12 | 银河航天(北京)通信技术有限公司 | A kind of method of temperature control system, spacecraft and spacecraft temperature control |
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| CN113359908B (en) | 2022-06-28 |
| CN111930163A (en) | 2020-11-13 |
| CN113359908A (en) | 2021-09-07 |
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