CN107792400B - Satellite external-pasting heat pipe mounting structure with deformation isolation function - Google Patents
Satellite external-pasting heat pipe mounting structure with deformation isolation function Download PDFInfo
- Publication number
- CN107792400B CN107792400B CN201710852789.7A CN201710852789A CN107792400B CN 107792400 B CN107792400 B CN 107792400B CN 201710852789 A CN201710852789 A CN 201710852789A CN 107792400 B CN107792400 B CN 107792400B
- Authority
- CN
- China
- Prior art keywords
- heat pipe
- externally
- support
- flexible connector
- screw
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Environmental & Geological Engineering (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Mechanical Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Remote Sensing (AREA)
- Mattresses And Other Support Structures For Chairs And Beds (AREA)
- Supports For Pipes And Cables (AREA)
Abstract
The invention discloses a satellite externally-attached heat pipe mounting structure with a deformation isolation function, which comprises a flexible connector, a heat pipe support, a heat insulation pad, a flat gasket, a spring gasket, a screw and a load mounting plate, wherein one end of an externally-attached heat pipe is connected with a star sensor support, the other end of the externally-attached heat pipe is connected with a radiating surface mounting plate, the flexible connector is mounted between the externally-attached heat pipe and the heat pipe support, the heat pipe support and the heat insulation pad are fixed on the load mounting plate, the screw is connected with the flexible connector, and the flat gasket and the spring gasket are positioned between the heat pipe support and the screw. The invention can solve the problems of the temperature control design of the star sensor outside the star sensor and the support thereof and the influence of the thermal deformation of the externally-attached heat pipe on the star sensor, and adopts the flexible connector to inhibit the displacement change of the externally-attached heat pipe caused by the deformation of the heat dissipation panel, thereby avoiding the influence of the thermal deformation of the heat dissipation panel on the stability of the installation precision of the support of the star sensor, namely realizing the isolation of the thermal deformation while realizing the temperature control.
Description
Technical Field
The invention relates to a satellite externally-attached heat pipe mounting structure, in particular to a satellite externally-attached heat pipe mounting structure with a deformation isolation function.
Background
At present, a large satellite platform structure is developing towards high precision and high stability, which puts higher and higher requirements on precision stability and thermal deformation performance of the satellite structure. The star sensor on the satellite is used for realizing the attitude positioning of the satellite in space, and the small out-of-tolerance of the installation precision of the star sensor can bring adverse influence on the accuracy of the attitude positioning. In space, the thermal environment experienced by the satellite is severe and complex, the satellite structure can generate corresponding thermal stress and thermal deformation, the star sensor and the support thereof are used as an important single machine for positioning the satellite attitude, and the thermal deformation control design is the key point of the current large satellite platform design.
The conventional satellite structure thermal deformation control design mainly adopts a heat pipe to realize isothermal design of a cabin plate in a pre-buried or externally-attached mode and the like, a star sensor support is also subjected to heat dissipation in an externally-attached heat pipe mode, the other end of the externally-attached heat pipe is connected to a heat dissipation plate with a large heat dissipation area, and the heat dissipation plate is mounted on a satellite top plate, so that thermal deformation generated by severe temperature change of the heat dissipation plate acts on the externally-attached heat pipe, the heat pipe generates displacement and stress, the mounting precision of the star sensor support is influenced, and the difficulty is increased for the temperature control design of the star sensor support.
Disclosure of Invention
The invention aims to provide a satellite externally-attached heat pipe mounting structure with a deformation isolation function, which can solve the problems of temperature control design of an extraterrestrial star sensor and a support thereof and influence of thermal deformation of an externally-attached heat pipe on the extraterrestrial star sensor.
The invention solves the technical problems through the following technical scheme: the utility model provides a satellite pastes heat pipe mounting structure outward with warp isolation function, its characterized in that, it includes flexible connector, heat pipe support, heat insulating mattress, plain washer, spring washer, screw, load mounting panel, pastes a star sensor support is connected to a outer heat pipe one end, pastes a cooling surface mounting panel is connected to the other end of heat pipe outward, flexible connector installs between outer heat pipe and the heat pipe support, heat insulating mattress are all fixed on a load mounting panel, and the screw is connected with flexible connector, and plain washer, spring washer all are located between heat pipe support and the screw.
Preferably, the thermal insulation pad separates the heat pipe support and a load mounting plate.
Preferably, the flexible connector is a spiral groove structure.
Preferably, the total length of the flexible connector is 33.5 mm; the internal diameter of helicla flute structure is 5mm, and the external diameter is 18mm, and the groove interval is 1.5mm, and the groove thickness is 1.7mm, and the number of turns is 4.75 circles, and the material is 2A14T6 type aluminium material, adopts the screw connection mode to install between outer subsides heat pipe and heat pipe support.
The positive progress effects of the invention are as follows:
firstly, the traditional externally-attached heat pipe only has the function of realizing temperature control, and the externally-attached heat pipe with the deformation isolation function can avoid the influence of thermal deformation on the structure of an important single machine while realizing the temperature control, thereby providing guarantee for the installation precision and the stability of the important single machine.
The flexible connector of the externally-attached heat pipe with the deformation isolation function adopts a spiral groove-shaped structure, the rigidity of the spring is designed through parameters such as groove spacing, groove thickness, number of turns, inner and outer diameters of spiral grooves and the like, and the flexible connector with corresponding size and rigidity can be designed for externally-attached heat pipes of different specifications, so that the thermal deformation inhibition isolation is effectively realized.
The invention can be used for heat dissipation and thermal deformation isolation of important single machines or structures of spacecrafts such as satellites and the like, and enables the on-orbit thermal deformation to be slightly controllable, thereby providing better temperature and mechanical environment.
Drawings
FIG. 1 is a schematic diagram of the present invention.
Fig. 2 is a schematic diagram of a flexible support structure of an externally attached heat pipe.
Fig. 3 is a schematic structural diagram of a flexible connector, a heat pipe support, a heat insulation pad, and the like.
Detailed Description
The following provides a detailed description of the preferred embodiments of the present invention with reference to the accompanying drawings.
As shown in fig. 1 to 3, the satellite external heat pipe mounting structure with deformation isolation function of the present invention includes a flexible connector 1, a heat pipe support 2, a heat insulation pad 3, a flat gasket 4, a spring gasket 5, a screw 6, and a load mounting plate 8, wherein one end of an external heat pipe 7 is connected to a star sensor support, the other end of the external heat pipe is connected to a heat dissipation surface mounting plate, the flexible connector is mounted between the external heat pipe and the heat pipe support, the heat pipe support and the heat insulation pad are both fixed to the load mounting plate 8, the screw 6 is connected to the flexible connector 1, and the flat gasket 4 and the spring gasket 5 are both located between the heat pipe support 2 and the screw 6.
The heat insulating pad 3 separates the heat pipe support 2 from the load mounting plate, which can avoid the influence of thermal deformation.
The flexible connector 1 is of a spiral groove structure, so that thermal deformation inhibition and isolation can be realized for externally-attached heat pipes of different specifications.
In the present embodiment, the external heat pipe is a conventional satellite external heat pipe. The total length of the flexible connector is 33.5 mm; the internal diameter of helicla flute structure is 5mm, and the external diameter is 18mm, and the groove interval is 1.5mm, and the groove thickness is 1.7mm, and the number of turns is 4.75 circles, and the material is 2A14T6 type aluminium material, adopts the screw connection mode to install between outer subsides heat pipe and heat pipe support. The heat pipe support is used for mounting and fixing the flexible connector and a load mounting plate, and simultaneously plays a supporting role for an external heat pipe, and is made of 2A14T6 type aluminum material; the heat insulation pad is arranged between the heat pipe support and a load mounting plate, the thickness of the heat insulation pad is 4mm, and the heat insulation pad is made of 3240 epoxy glass cloth laminated board.
The flexible connector is adopted to inhibit the displacement change of the externally-attached heat pipe caused by the deformation of the heat dissipation panel, so that the influence of the thermal deformation of the heat dissipation panel on the stability of the installation precision of the star sensor support is avoided, namely, the thermal deformation isolation is realized while the temperature control is realized.
The above embodiments are described in further detail to solve the technical problems, technical solutions and advantages of the present invention, and it should be understood that the above embodiments are only examples of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A satellite externally-adhered heat pipe mounting structure with a deformation isolation function is characterized by comprising a flexible connector, a heat pipe support, a heat insulation pad, a flat gasket, a spring gasket, a screw and a load mounting plate, wherein one end of an externally-adhered heat pipe is connected with a star sensor support, the other end of the externally-adhered heat pipe is connected with a radiating surface mounting plate, the flexible connector is mounted between the externally-adhered heat pipe and the heat pipe support, the heat pipe support and the heat insulation pad are fixed on the load mounting plate, the screw is connected with the flexible connector, and the flat gasket and the spring gasket are located between the heat pipe support and the screw;
the heat insulation pad separates heat pipe support and load mounting panel, flexible connector is the helicla flute structure, outer subsides heat pipe can avoid the influence of heat altered shape to spacecraft single-machine structure when realizing temperature control, makes the thermal deformation controllable in orbit.
2. The satellite attached heat pipe installation structure with deformation isolation function according to claim 1, wherein the total length of the flexible connector is 33.5 mm; the internal diameter of helicla flute structure is 5mm, and the external diameter is 18mm, and the groove interval is 1.5mm, and the groove thickness is 1.7mm, and the number of turns is 4.75 circles, and the material is 2A14T6 type aluminium material, adopts the screw connection mode to install between outer subsides heat pipe and heat pipe support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710852789.7A CN107792400B (en) | 2017-09-19 | 2017-09-19 | Satellite external-pasting heat pipe mounting structure with deformation isolation function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710852789.7A CN107792400B (en) | 2017-09-19 | 2017-09-19 | Satellite external-pasting heat pipe mounting structure with deformation isolation function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107792400A CN107792400A (en) | 2018-03-13 |
| CN107792400B true CN107792400B (en) | 2021-06-29 |
Family
ID=61532490
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710852789.7A Active CN107792400B (en) | 2017-09-19 | 2017-09-19 | Satellite external-pasting heat pipe mounting structure with deformation isolation function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107792400B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791961B (en) * | 2018-06-14 | 2020-03-06 | 上海卫星工程研究所 | GEO satellite large-span heat pipe configuration |
| CN110906527B (en) * | 2019-11-01 | 2021-05-11 | 上海卫星工程研究所 | Fixing device for heat pipe in satellite cabin |
| CN112357127B (en) * | 2020-11-13 | 2022-06-03 | 航天东方红卫星有限公司 | Compressing device suitable for installation of satellite internal externally-attached heat pipe |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101327848A (en) * | 2008-06-20 | 2008-12-24 | 郑钢铁 | Damping flexible connecting method for spacecraft |
| CN102079386A (en) * | 2009-11-30 | 2011-06-01 | 上海卫星工程研究所 | Simply constructed heat transfer device for stand-alone radiating of space vehicle |
| CN104691790A (en) * | 2015-02-13 | 2015-06-10 | 上海卫星工程研究所 | High-accuracy micro deformation star sensor mounting bracket |
| CN104743138A (en) * | 2015-02-13 | 2015-07-01 | 上海卫星工程研究所 | High-precision micro-deformation attitude control instrument installing structure for spaceflight |
| CN106184821A (en) * | 2016-08-12 | 2016-12-07 | 上海卫星工程研究所 | The remote sensing instrument of a kind of high precision high stability configuration integrated with star sensor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2972714B1 (en) * | 2011-03-17 | 2014-01-17 | Thales Sa | STRUCTURAL SATELLITE PANEL WITH INTEGRATED THERMAL EXCHANGERS |
-
2017
- 2017-09-19 CN CN201710852789.7A patent/CN107792400B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101327848A (en) * | 2008-06-20 | 2008-12-24 | 郑钢铁 | Damping flexible connecting method for spacecraft |
| CN102079386A (en) * | 2009-11-30 | 2011-06-01 | 上海卫星工程研究所 | Simply constructed heat transfer device for stand-alone radiating of space vehicle |
| CN104691790A (en) * | 2015-02-13 | 2015-06-10 | 上海卫星工程研究所 | High-accuracy micro deformation star sensor mounting bracket |
| CN104743138A (en) * | 2015-02-13 | 2015-07-01 | 上海卫星工程研究所 | High-precision micro-deformation attitude control instrument installing structure for spaceflight |
| CN106184821A (en) * | 2016-08-12 | 2016-12-07 | 上海卫星工程研究所 | The remote sensing instrument of a kind of high precision high stability configuration integrated with star sensor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107792400A (en) | 2018-03-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107792400B (en) | Satellite external-pasting heat pipe mounting structure with deformation isolation function | |
| CN108910090B (en) | Star sensor and thermal control device integrated mounting bracket | |
| US9243736B2 (en) | Structure of vacuum insulator with assembly reciprocating support | |
| CN104443435A (en) | Star sensor mounting structure for thermal deformation isolation and control | |
| CN103662088A (en) | Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite | |
| CN107284690B (en) | Truss support device suitable for vertical layout of SGCMG (Square pyramid control graph) pentagonal pyramid | |
| CN103486183B (en) | For the large damping isolator of satellite sensitive load | |
| CN104071354B (en) | A kind of satellite shell and use the satellite of this housing | |
| CN111322213B (en) | Piezoelectric grid with variable spacing | |
| CN102720801B (en) | Novel flywheel support structure for spacecraft | |
| CN107444677B (en) | Optical-mechanical-thermal integrated structure for multi-load high-precision splicing | |
| CN104691790B (en) | High accuracy Light deformation star sensor mounting bracket | |
| CN103486177B (en) | For the New Type Vibration Isolator Using of satellite sensitive load | |
| CN111830655A (en) | Kinematic supporting structure for space optical load | |
| CN108791959B (en) | Star sensor lightweight thermal control device based on structure mounting plate | |
| IL163918A (en) | Control moment gyro for attitude control of spacecraft | |
| CN103197396B (en) | Device fixed by picture frame | |
| CN102781163B (en) | Damping support structure between printed circuit boards of satellite-bone electronic equipment | |
| CN104743138B (en) | High-precision micro-deformation attitude control instrument installing structure for spaceflight | |
| CN104879414A (en) | Viscoelastic damping truss vibration isolator | |
| CN109975830B (en) | In-orbit thermal deformation suppression system for GEO satellite optical remote sensing instrument | |
| CN210799278U (en) | Compressor callus on sole, compressor and air conditioner | |
| CN204985501U (en) | A support damping structure for sensor installation | |
| CN209787663U (en) | Satellite controller installing frame | |
| US8987579B2 (en) | Power converter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |