CN108791961B - GEO satellite large-span heat pipe configuration - Google Patents
GEO satellite large-span heat pipe configuration Download PDFInfo
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- CN108791961B CN108791961B CN201810616044.5A CN201810616044A CN108791961B CN 108791961 B CN108791961 B CN 108791961B CN 201810616044 A CN201810616044 A CN 201810616044A CN 108791961 B CN108791961 B CN 108791961B
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- heat pipe
- connecting end
- span
- radiating surface
- star sensor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/506—Heat pipes
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- Environmental & Geological Engineering (AREA)
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- General Health & Medical Sciences (AREA)
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- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The invention discloses a GEO satellite large-span heat pipe structure, which has a U-shaped structure in two dimensions, wherein the two U-shaped spans are 1375mm and 925mm respectively; the large-span heat pipe is characterized in that the two ends of the large-span heat pipe are respectively a bracket connecting end and a radiating surface connecting end, the bracket connecting end and the radiating surface connecting end are not on the same plane, and the mounting surfaces of the two connecting ends form an included angle of 90 degrees. The total length of the large-span heat pipe is 3000mm, the ratio of the length to the maximum size of the cross section of the heat pipe is 75, the linear length of the connecting end of the support is 185mm, and the linear length of the connecting end of the radiating surface is 625 mm. The invention reduces the influence of the star sensor on the installation precision of the star sensor from the aspects of mechanical environment and on-orbit thermal environment and improves the stability of the on-orbit installation reference of the star sensor.
Description
Technical Field
The invention relates to a large-span heat pipe configuration and connection design of a GEO satellite, in particular to a large-span heat pipe configuration for heat dissipation of a GEO satellite star sensor.
Background
The star sensors are widely applied to space missions as attitude measurement devices with the highest precision at present, and the configuration quantity of the star sensors is not less than 2 for realizing high-precision measurement of the three-axis attitude of the satellite.
In order to meet the measurement accuracy of the star sensor, on one hand, the star sensor is required to work in a constant temperature environment, the star sensor is maintained in a stable temperature range through precise temperature control, and a heat pipe is required to transfer the heat of the star sensor to a radiation radiating surface; on the other hand, the star sensor pointing direction is not affected by the heat pipe under the condition of rail temperature change.
The illumination condition under the GEO orbit environment is complex, the sunlight alternately irradiates the star sensor every day, and the sunlight incident angles are different all the year round. In order to meet the measurement precision requirement of the star sensor and reduce the influence of the large-span heat pipe for heat dissipation of the star sensor on the precision of the star sensor, the invention provides a heat pipe configuration and a connection design which are suitable for reducing the influence of thermal deformation and are suitable for a mechanical environment.
At present, no description or report of similar technologies to the invention is found, and similar data in China is not collected.
Disclosure of Invention
The invention provides a GEO satellite large-span heat pipe configuration, aiming at improving the measurement precision of a star sensor and reducing the influence of the configuration and connection design of a large-span heat pipe for heat dissipation of the star sensor on the precision of the large-span heat pipe.
In order to achieve the above object, the present invention is specifically realized by the following technical scheme:
a GEO satellite large-span heat pipe configuration, the large-span heat pipe has "U" style of calligraphy configuration in two dimensions, two "U" style of calligraphy spans are 1375mm and 925mm respectively; the large-span heat pipe is characterized in that the two ends of the large-span heat pipe are respectively a bracket connecting end and a radiating surface connecting end, the bracket connecting end and the radiating surface connecting end are not on the same plane, and the mounting surfaces of the two connecting ends form an included angle of 90 degrees.
Preferably, the total length of the large-span heat pipe is 3000mm, the ratio of the length to the maximum size of the cross section of the heat pipe is 75, the linear length of the connecting end of the bracket is 185mm, and the linear length of the connecting end of the radiating surface is 625 mm.
Preferably, the support connecting end is rigidly connected with the star sensor support through a screw, and the radiating surface connecting end is connected with the radiating surface through a screw, so that a complete heat transfer path for transferring heat from the star sensor to the star sensor support and then to the radiating surface through a heat pipe is realized.
Preferably, the large-span heat pipe establishes a connection relationship between the heat pipe and the star structure through a flexible connection device at a position close to the star sensitive support.
The invention has the following beneficial effects:
1) the influence of the star sensor on the installation accuracy of the star sensor is reduced from the aspects of mechanical environment and on-orbit thermal environment, and the stability of the on-orbit installation reference of the star sensor is improved;
2) according to the invention, two ends of the heat pipe are directly and fixedly connected with the star sensor support or the radiating surface, and the thermal deformation is released through the flexible connecting device, so that the vibration energy of the heat pipe transmitted to the star sensor in a mechanical environment is reduced.
Drawings
Fig. 1 is a schematic diagram of a specific application example of a GEO satellite large-span heat pipe configuration according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a large-span heat pipe configuration of a GEO satellite according to an embodiment of the present invention.
FIG. 3 is a schematic view of a "U" configuration in an embodiment of the present invention.
Detailed Description
The invention is explained in detail below with reference to the figures and examples.
As shown in fig. 2-3, an embodiment of the invention provides a GEO satellite large-span heat pipe configuration, the large-span heat pipe 3 has a U-shaped configuration 9 in two dimensions, and the two U-shaped spans are 1375mm and 925mm respectively, so that on one hand, the rigidity of the heat pipe structure is weakened, and the structural thermal deformation of a heat dissipation surface is reduced by 2-3 orders of magnitude when being transmitted to a satellite-sensitive support; meanwhile, the deformation transmitted to the star sensor support is further weakened through the flexible connecting device. The two ends of the large-span heat pipe 3 are respectively a bracket connecting end 6 and a radiating surface connecting end 8, the bracket connecting end and the radiating surface connecting end are not on the same plane, and the mounting surfaces of the two connecting ends form an included angle of 90 degrees.
In this embodiment, the total length of the large-span heat pipe 3 is 3000mm, the ratio of the length to the maximum size length of the cross section of the heat pipe is 75, the linear length of the connecting end of the bracket is 185mm, and the linear length of the connecting end of the heat dissipation surface is 625mm, and the detailed configuration is shown in fig. 2.
As shown in figure 1, the support connecting end is rigidly connected with the star sensor support 2 through not less than 4 screws, and the radiating surface connecting end is connected with the radiating surface 4 through not less than 6 screws, so that a complete heat transfer path for transferring heat from the star sensor 1 to the star sensor support and then to the radiating surface through the heat pipe is realized. The large-span heat pipe 3 is close to the star sensor support 2, the heat pipe and the star body structure 7 are connected through the flexible connecting device 5, and the installation area 10 of the flexible connecting device is arranged close to the U-shaped structure of the support connecting end 6.
In the flight process of the satellite active section, the main vibration energy of the heat pipe is transmitted to the satellite body structure from the connection part of the flexible connection device and the radiating surface, and a small part of energy is transmitted through the satellite sensitive support. Under the condition of an orbital thermal environment, thermal deformation of the star body structure is isolated through the flexible connecting device.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (3)
1. A GEO satellite large-span heat pipe configuration which characterized in that: the large-span heat pipe (3) has a U-shaped configuration in two dimensions, and the two U-shaped spans are 1375mm and 925mm respectively; the two ends of the large-span heat pipe (3) are respectively a bracket connecting end and a radiating surface connecting end, the bracket connecting end and the radiating surface connecting end are not on the same plane, and the mounting surfaces of the two connecting ends form an included angle of 90 degrees;
the support connecting end is rigidly connected with the star sensor support (2) through at least 4 screws, and the radiating surface connecting end is connected with the radiating surface (4) through at least 6 screws, so that a complete heat transfer path for transferring heat from the star sensor to the star sensor support and then to the radiating surface through the heat pipe is realized.
2. The GEO satellite large-span heat pipe configuration of claim 1, wherein: the total length of the large-span heat pipe (3) is 3000mm, the ratio of the length to the maximum size length of the cross section of the heat pipe is 75, the linear length of the connecting end of the support is 185mm, and the linear length of the connecting end of the radiating surface is 625 mm.
3. The GEO satellite large-span heat pipe configuration of claim 1, wherein: the large-span heat pipe (3) establishes a connection relation between the heat pipe and a star body structure (7) through a flexible connection device (5) at a position close to the star sensitive support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810616044.5A CN108791961B (en) | 2018-06-14 | 2018-06-14 | GEO satellite large-span heat pipe configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810616044.5A CN108791961B (en) | 2018-06-14 | 2018-06-14 | GEO satellite large-span heat pipe configuration |
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| Publication Number | Publication Date |
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| CN108791961A CN108791961A (en) | 2018-11-13 |
| CN108791961B true CN108791961B (en) | 2020-03-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810616044.5A Active CN108791961B (en) | 2018-06-14 | 2018-06-14 | GEO satellite large-span heat pipe configuration |
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Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5735489A (en) * | 1995-12-22 | 1998-04-07 | Hughes Electronics | Heat transport system for spacecraft integration |
| CN103448925A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | High-precision temperature control device for star sensors for satellites |
| US11009297B2 (en) * | 2015-04-15 | 2021-05-18 | Worldvu Satellites Limited | Fluidicially coupled heat pipes and method therefor |
| CN205221138U (en) * | 2015-09-21 | 2016-05-11 | 上海卫星工程研究所 | Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft |
| CN107792400B (en) * | 2017-09-19 | 2021-06-29 | 上海卫星工程研究所 | Satellite external-pasting heat pipe mounting structure with deformation isolation function |
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