CN108791961A - A kind of GEO satellite large span heat pipe configuration - Google Patents
A kind of GEO satellite large span heat pipe configuration Download PDFInfo
- Publication number
- CN108791961A CN108791961A CN201810616044.5A CN201810616044A CN108791961A CN 108791961 A CN108791961 A CN 108791961A CN 201810616044 A CN201810616044 A CN 201810616044A CN 108791961 A CN108791961 A CN 108791961A
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- heat pipe
- connecting pin
- large 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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- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Geophysics And Detection Of Objects (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The invention discloses a kind of GEO satellite large span heat pipe configuration, which has " U " font configuration on two dimensions, and two " U " font spans are respectively 1375mm and 925mm；Large span heat pipe both ends are respectively holder connecting pin and radiating surface connecting pin, the holder connecting pin and radiating surface connecting pin not in the same plane, the mounting surface angle in 90 ° of two connecting pins.The large span heat pipe overall length is 3000mm, and length is 75 with heat pipe cross section full-size lenth ratio, and holder connecting pin straight length is 185mm, and radiating surface connecting pin straight length is 625mm.The present invention reduces its influence to star sensor installation accuracy in terms of mechanical environment and On orbit thermal environment, improves the stability of the in-orbit reference for installation of star sensor.
Description
Technical field
The present invention relates to a kind of GEO satellite large span heat pipe configuration and connection design, more particularly to a kind of GEO satellite star are quick
The configuration of sensor heat transmission large span heat pipe.
Background technology
Star sensor is widely applied as the highest attitude measurement device of current precision in space mission, is real
The high-acruracy survey of existing satellite three-axis attitude, star sensor configuration quantity are no less than 2.
To meet the measurement accuracy of star sensor, on the one hand need to ensure that star sensor is operated in stationary temperature environment
In, it is maintained by precise temperature control within the scope of stable temperature, needs heat pipe by the heat transfer of star sensor to heat loss through radiation
Face；On the other hand, need to ensure that heat pipe does not influence star sensor direction under in-orbit temperature variations.
Illumination condition is complicated under GEO orbital environments, and sunlight irradiates star sensor in turn daily, and sunlight enters throughout the year
Firing angle is also not quite similar.To meet the measurement accuracy requirement of star sensor, star sensor heat transmission large span heat pipe is reduced to it
The influence of precision, invented it is a kind of be suitable for reduce influence of thermal deformation and be adapted to mechanical environment heat pipe configuration and connection set
Meter.
Currently without the explanation or report for finding technology similar to the present invention, it is also not yet collected into domestic similar data.
Invention content
To improve the measurement accuracy of star sensor, the configuration and connection for reducing star sensor heat transmission large span heat pipe design
The technical problems such as the influence to its precision, the present invention provide a kind of GEO satellite large span heat pipe configuration.
To realize that upper purpose, the present invention are realized especially by following technical scheme：
A kind of GEO satellite large span heat pipe configuration, the large span heat pipe on two dimensions have " U " font configuration, two
A " U " font span is respectively 1375mm and 925mm；Large span heat pipe both ends are respectively that holder connecting pin and radiating surface connect
Connect end, the holder connecting pin and radiating surface connecting pin not in the same plane, the mounting surface folder in 90 ° of two connecting pins
Angle.
Preferably, the large span heat pipe overall length is 3000mm, and length is with heat pipe cross section full-size lenth ratio
75, holder connecting pin straight length is 185mm, and radiating surface connecting pin straight length is 625mm.
Preferably, the holder connecting pin is rigidly connected by screw and star sensor'support, and radiating surface connecting pin passes through screw
It is connect with radiating surface, heat is transferred to star sensor support by star sensor and is transferred to the complete of radiating surface by heat pipe again by realization
Whole heat transfer path.
Preferably, the large span heat pipe at the star sensor'support by flexible connecting device by heat pipe and celestial body structure
It establishes a connection.
The invention has the advantages that：
1) present invention reduces its influence to star sensor installation accuracy in terms of mechanical environment and On orbit thermal environment, improves
The stability of the in-orbit reference for installation of star sensor；
2) heat pipe both ends are directly fixedly connected with star sensor'support or radiating surface in the present invention, will be hot by flexible connecting device
Deformation is discharged, and the heat pipe vibrational energy of star sensor is transferred to when reducing mechanical environment.
Description of the drawings
Fig. 1 is a kind of schematic diagram of one concrete application example of GEO satellite large span heat pipe configuration of the embodiment of the present invention.
Fig. 2 is a kind of structural schematic diagram of GEO satellite large span heat pipe configuration of the embodiment of the present invention.
Fig. 3 is the schematic diagram of " U " font configuration in the embodiment of the present invention.
Specific implementation mode
The present invention will be described in detail with reference to the accompanying drawings and examples.
As shown in Fig. 2-Fig. 3, an embodiment of the present invention provides a kind of GEO satellite large span heat pipe configuration, large span heat
It is respectively 1375mm and 925mm that pipe 3 has " U " font configuration 9, two " U " font spans on two dimensions, is on the one hand weakened
The rigidity of heat pipe structure reduces by 2~3 orders of magnitude when the structure heat distortion amount of radiating surface is transferred to star sensor'support；Meanwhile it is logical
Cross the deflection decrease that flexible connecting device further will be transmitted to star sensor'support.3 both ends of large span heat pipe are respectively branch
Frame connecting pin 6 and radiating surface connecting pin 8, the holder connecting pin and radiating surface connecting pin not in the same plane, two companies
Connect the mounting surface angle in 90 ° at end.
In the present embodiment, 3 overall length of large span heat pipe is 3000mm, length and heat pipe cross section full-size length ratio
Value is 75, and holder connecting pin straight length is 185mm, and radiating surface connecting pin straight length is 625mm, and detailed configuration is shown in attached drawing 2.
As shown in Figure 1, the holder connecting pin is rigidly connected by being no less than 4 screws with star sensor'support 2, radiating surface connects
It connects end to connect with radiating surface 4 by being no less than 6 screws, realizes and heat is transferred to star sensor support again by star sensor 1
The complete heat transfer path of radiating surface is transferred to by heat pipe.The large span heat pipe 3 is being connected at star sensor'support 2 by flexibility
Connection device 5 establishes a connection heat pipe and celestial body structure 7, and the installation region 10 of flexible connecting device is close to holder connecting pin 6
" U " font configuration arrangement.
During satellite boosting flight, the principal vibration energy of heat pipe is by flexible connecting device and radiating surface junction
It is transferred to celestial body structure, few portion of energy is transmitted by star sensor'support.Under the conditions of On orbit thermal environment, the thermal deformation of celestial body structure
Thermal deformation " isolation " is carried out by flexible connecting device.
More than, only it is presently preferred embodiments of the present invention, is not intended to limit the present invention in any form, although this
Invention is disclosed above with preferred embodiment, and however, it is not intended to limit the invention, any person skilled in the art,
It does not depart within the scope of technical solution of the present invention, when the technology contents using the disclosure above make a little change or are modified to equivalent
The equivalent embodiment of variation, as long as being without departing from technical solution of the present invention content, according to the technical essence of the invention to above real
Any simple modification, equivalent variations and modification made by example are applied, in the range of still falling within technical solution of the present invention.
Claims (4)
1. a kind of GEO satellite large span heat pipe configuration, it is characterised in that：The large span heat pipe (3) has " U " on two dimensions
Font configuration, two " U " font spans are respectively 1375mm and 925mm；Large span heat pipe (3) both ends are respectively that holder connects
Connect end and radiating surface connecting pin, the holder connecting pin and radiating surface connecting pin not in the same plane, two connecting pins
Mounting surface angle in 90 °.
2. a kind of GEO satellite large span heat pipe configuration as described in claim 1, it is characterised in that：The large span heat pipe (3)
Overall length is 3000mm, and length is 75 with heat pipe cross section full-size lenth ratio, and holder connecting pin straight length is 185mm,
Radiating surface connecting pin straight length is 625mm.
3. a kind of GEO satellite large span heat pipe configuration as described in claim 1, it is characterised in that：The holder connecting pin is logical
Screw and star sensor'support (2) is crossed to be rigidly connected, radiating surface connecting pin is connect by screw with radiating surface (4), realization by heat by
Star sensor is transferred to the complete heat transfer path that star sensor support is transferred to radiating surface by heat pipe again.
4. a kind of GEO satellite large span heat pipe configuration as described in claim 1, it is characterised in that：The large span heat pipe (3)
Heat pipe and celestial body structure (7) are being established a connection by flexible connecting device (5) at star sensor'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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108791961A true CN108791961A (en) | 2018-11-13 |
| CN108791961B CN108791961B (en) | 2020-03-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810616044.5A Active CN108791961B (en) | 2018-06-14 | 2018-06-14 | GEO satellite large-span heat pipe configuration |
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Citations (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 |
| 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 |
| US20160305714A1 (en) * | 2015-04-15 | 2016-10-20 | Worldvu Satellites Limited | Fluidicially Coupled Heat Pipes and Method Therefor |
| CN107792400A (en) * | 2017-09-19 | 2018-03-13 | 上海卫星工程研究所 | Satellite outer patch heat pipe mounting structure with distortion isolation function |
-
2018
- 2018-06-14 CN CN201810616044.5A patent/CN108791961B/en active Active
Patent Citations (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 |
| US20160305714A1 (en) * | 2015-04-15 | 2016-10-20 | 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 |
| CN107792400A (en) * | 2017-09-19 | 2018-03-13 | 上海卫星工程研究所 | Satellite outer patch heat pipe mounting structure with distortion isolation function |
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| Publication number | Publication date |
|---|---|
| CN108791961B (en) | 2020-03-06 |
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