CN102788137B - Attemperator for labyrinth rotating part - Google Patents
Attemperator for labyrinth rotating part Download PDFInfo
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- CN102788137B CN102788137B CN201210278917.9A CN201210278917A CN102788137B CN 102788137 B CN102788137 B CN 102788137B CN 201210278917 A CN201210278917 A CN 201210278917A CN 102788137 B CN102788137 B CN 102788137B
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- insulation cover
- circular
- circular insulation
- supporting part
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Abstract
The invention discloses an attemperator for a labyrinth rotating part and relates to the technical field of spacecraft thermal control. The invention aims to solve the problem that a thermal control measure for the relative rotating part on a spacecraft cannot meet the normal working requirements. The attemperator comprises a support component, a rotating shaft, a rotating component, a first multilayer heat insulation assembly and a second multilayer heat insulation assembly, wherein the rotating shaft is inserted into the support component; the rotating component is mutually connected with the rotating shaft; the first multilayer heat insulation assembly is coated outside the support component; and the second multilayer heat insulation assembly is coated outside the rotating component. A heat holding cover coated near the outer surface of the rotating shaft is arranged at the position between the rotating component and the support component. The first multilayer heat insulation assembly and/or the second multilayer heat insulation assembly are/is coated outside the heat holding cover. According to the attemperator disclosed by the invention, the heat insulation assemblies can be effectively prevented from being mechanically damaged or twined, thereby, most of heat loss is reduced, and the reliability of the thermal control measure for the relative rotating part is enhanced.
Description
Technical field
The present invention relates to astrovehicle Evolution of Thermal Control Technique field, be specifically related to a kind of mazy type rotary part thermal insulation apparatus.
Background technique
In recent years, China's aerospace industry is quick, fast development constantly, the astrovehicle quantity of flying in-orbit is increasing, complexity and its corresponding energy requirement of astrovehicle are also increasing, and for the requirement of the life and reliability of astrovehicle also in continuous enhancing, sufficiently and reasonably to utilize and manage the spaceborne energy, reduce unnecessary heat loss on astrovehicle be also the effective way alleviating astrovehicle energy demand burden.
Astrovehicle can experience very severe thermal environment in the process of space flight, for ensureing that astrovehicle reliably to work in cosmic space long-term safety and to complete set each task, the position that relatively rotates to astrovehicle being exposed in space is needed to carry out special thermal design.
Usually the principle of " based on passive thermal control, Active thermal control is auxiliary " is adopted in astrovehicle thermal design.As shown in Figure 1, mainly rotatingshaft 2 and bearing is relied on to realize the transmission being connected and moving between spaceborne supporting part 1 with its rotatable parts 3.When being thought of as structure shown in Fig. 1 and carrying out thermal design, first consider to use passive thermal control measure, but there is relative movement due to space between supporting part 1 and rotatable parts 3, be difficult to directly use multilayer insulation assembly to carry out effectively coated at such rotary part, also likely cause multilayer insulation assembly to be destroyed or some parts of astrovehicle can not normally work if dealt with improperly; According to the temperature levels that Active thermal control ensures herein, power consumption will certainly be increased again, if but do not do corresponding thermal control measure, it is directly exposed in cosmic space, energy can be made again to relatively rotate position be lost continuously, therefore be difficult to take effective measure to stop scattering and disappearing of energy herein.
Summary of the invention
The problem of normal job requirement can not be met to solve thermal control measure astrovehicle relatively rotating position, the invention provides a kind of mazy type rotary part thermal insulation apparatus.
The technological scheme that the present invention adopts for technical solution problem is as follows:
Mazy type rotary part thermal insulation apparatus, comprising:
Supporting part;
Be inserted into the rotatingshaft in described supporting part;
The rotatable parts be connected with described rotatingshaft;
Be coated on the first multilayer insulation assembly of described supporting part outside; With
Be coated on the second multilayer insulation assembly of described rotatable parts outside;
Position between described supporting part and described rotatable parts, is provided with the insulation cover be coated near described rotatingshaft outer surface;
Described insulation cover comprises: be connected to the first semi-circular insulation cover on described supporting part and the second semi-circular insulation cover, described first semi-circular insulation cover is relative with described second semi-circular insulation cover snaps onto described rotatingshaft outer surface, and described first multilayer insulation assembly is coated on the outside of described first semi-circular insulation cover and described second semi-circular insulation cover;
And/or,
Described insulation cover comprises: be connected to the 3rd semi-circular insulation cover on described rotatable parts and the 4th semi-circular insulation cover, described 3rd semi-circular insulation cover is relative with described 4th semi-circular insulation cover snaps onto described rotatingshaft outer surface, and described second multilayer insulation assembly is coated on the outside of described 3rd semi-circular insulation cover and described 4th semi-circular insulation cover;
Described first multilayer insulation assembly and/or described second multilayer insulation assembly are coated on the outside of described insulation cover.
Described first semi-circular insulation cover is connected on the supporting member by set screw with the second semi-circular insulation cover.
Described first semi-circular insulation cover is identical with the second semi-circular heat insulation cover structure, and one end is provided with the flange plate for being connected on described supporting part, and the other end is semi-circular opening.
Flange plate both sides on described first semi-circular insulation cover and the second semi-circular insulation cover are provided with thermal insulating pad.
Described 3rd semi-circular insulation cover and the 4th semi-circular insulation cover are connected on rotatable parts by set screw.
Described 3rd semi-circular insulation cover is identical with the 4th semi-circular heat insulation cover structure, and one end is provided with the flange plate for being connected on described rotatable parts, and the other end is semi-circular opening.
Flange plate both sides on described 3rd semi-circular insulation cover and the 4th semi-circular insulation cover are provided with thermal insulating pad.
The invention has the beneficial effects as follows: the position of thermal insulation apparatus of the present invention between supporting part and rotatable parts, be provided with the insulation cover be coated near rotatingshaft outer surface, insulation cover outside is coated upper multilayer insulation assembly again, because insulation cover can make multilayer insulation assembly and relatively rotate between position to keep apart, can effectively prevent multilayer insulation assembly that the mutual winding of the drive because relatively rotating position or multilayer insulation inter-module causes by mechanical damage, effectively can prevent again astrovehicle relatively rotating position and leak the hot heat loss caused, keep temperature constant herein, astrovehicle is enable reliably to work in cosmic space long-term safety and complete set each task, improve the reliability relatively rotating position thermal control measure.
Accompanying drawing explanation
Fig. 1 is simplified structure schematic diagram astrovehicle relatively rotating position;
Fig. 2 is the structural representation that the first semi-circular insulation cover and the second semi-circular insulation cover install on the supporting member;
Fig. 3 is the structural representation that the 3rd semi-circular insulation cover and the 4th semi-circular insulation cover are arranged on rotatable parts;
Fig. 4 is that the first semi-circular insulation cover and the second semi-circular insulation cover are installed on the supporting member, the 3rd semi-circular insulation cover and the 4th semi-circular insulation cover are arranged on structural representation on rotatable parts;
Fig. 5 is the plan view of the first semi-circular insulation cover;
Fig. 6 is the left view of the first semi-circular insulation cover;
Fig. 7 is the plan view of the 3rd semi-circular insulation cover;
Fig. 8 is the left view of the 3rd semi-circular insulation cover;
Fig. 9 is the plan view of the 3rd semi-circular insulation cover.
In figure: 1, supporting part, 2, rotatingshaft, 3, rotatable parts, the 41, first multilayer insulation assembly, the 42, second multilayer insulation assembly, 5, the first semi-circular insulation cover, 6, the second semi-circular insulation cover, 7, thermal insulating pad, 8, set screw, 9, the 3rd semi-circular insulation cover, the 10, the 4th semi-circular insulation cover.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Mazy type rotary part thermal insulation apparatus of the present invention, for astrovehicle relatively rotating position to design, as shown in Figure 1, astrovehicle relatively rotates position and is made up of three parts: supporting part 1, rotatingshaft 2 and rotatable parts 3; Rotatingshaft 2 is inserted in supporting part 1 central through bore, there is relative movement between supporting part 1 and rotatingshaft 2; Rotatable parts 3 are fixedly connected with rotatingshaft 2, therefore there is relative movement between supporting part 1 and rotatable parts 3; First multilayer insulation assembly 41 is coated on supporting part 1 side and periphery, second multilayer insulation assembly 42 is coated on rotatable parts 3 side and periphery, therefore also there is relative movement between the first multilayer insulation assembly 41 and the second multilayer insulation assembly 42.
The present invention to thermal design astrovehicle as shown in Figure 1 relatively rotating position is:
As shown in Figure 2, on the side of supporting part 1, by set screw 8, the first identical semi-circular insulation cover 5 and the second semi-circular insulation cover 6 of structure is installed, as shown in Figure 5 and Figure 6, first semi-circular insulation cover 5 one end is provided with the flange plate for being connected on supporting part 1 side, the other end is semi-circular opening, described flange plate is provided with three through holes, first semi-circular insulation cover 5 is fixed on supporting part 1 side through three through holes by set screw 8, the both sides of three through holes are also provided with thermal insulating pad 7, snap together relative with two semi-circular openings of the second semi-circular insulation cover 6 of first semi-circular insulation cover 5 forms cylindrical shape insulation cover, it is also free to rotate therein that rotatingshaft 2 is positioned at cylindrical shape insulation cover, after the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 installation, all coated first multilayer insulation assembly 41 on its outside and supporting part 1 side and periphery, simultaneously, coated second multilayer insulation assembly 42 on rotatable parts 3 side and periphery.
Described " it is outside " refers to the insulation cover outer surface corresponding with the cylindrical shape insulation cover internal surface that the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 are formed and flange plate outer surface sum, is referred to as the outside of the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6.
Above-mentioned situation for: when the lateral dimension of supporting part 1 is much larger than the semi-circular insulation cover flange plate maximum outside diameter that will install, the lateral dimension of rotatable parts 3 is less than the lateral dimension of supporting part 1 simultaneously, semi-circular insulation cover can be conveniently installed, the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 can be selected to be arranged on supporting part 1 side;
When the lateral dimension of rotatable parts 3 is much larger than the semi-circular insulation cover flange plate maximum outside diameter that will install, the lateral dimension of supporting part 1 is less than the lateral dimension of rotatable parts 3 simultaneously, semi-circular insulation cover can be conveniently installed, the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 can be selected to be arranged on rotatable parts 3 side.
Two semi-circular flange dishes that described " flange plate maximum outside diameter " refers to the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 are combined formed a complete circle flange plate diameter.
As shown in Figure 3, on the periphery of rotatable parts 3, by set screw 8, the 3rd identical semi-circular insulation cover 9 of structure and the 4th semi-circular insulation cover 10 are installed, as Fig. 7, shown in Fig. 8 and Fig. 9, 3rd semi-circular insulation cover 9 one end is provided with the flange plate for being connected on rotatable parts 3 periphery, the other end is semi-circular opening, described flange plate is provided with three through holes, 3rd semi-circular insulation cover 9 is fixed on supporting part 1 side through three through holes by set screw 8, the both sides of three through holes are also provided with thermal insulating pad 7, snap together relative with two semi-circular openings of the 4th semi-circular insulation cover 10 of 3rd semi-circular insulation cover 9 forms cylindrical shape insulation cover, it is inner and free to rotate therein that rotatingshaft 2 is positioned at cylindrical shape insulation cover, when rotatingshaft 2 rotates, 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 rotate with it simultaneously, after the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 installation, all coated second multilayer insulation assembly 42 on its outside and rotatable parts 3 periphery, simultaneously, coated first multilayer insulation assembly 41 on supporting part 1 side and periphery.
Described " it is outside " refers to the insulation cover outer surface corresponding with the cylindrical shape insulation cover internal surface that the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 are formed and flange plate outer surface sum, is referred to as the outside of the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10.
Above-mentioned situation is: when the lateral dimension of rotatable parts 3 is less than the lateral dimension of supporting part 1, and distance between supporting part 1 and rotatable parts 3 side less time, the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 can be selected to be arranged on rotatable parts 3 periphery;
When the lateral dimension of supporting part 1 is less than the lateral dimension of rotatable parts 3, and distance between supporting part 1 and rotatable parts 3 side less time, the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 can be selected to be arranged on supporting part 1 periphery.
As shown in Figure 4, the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 are arranged on supporting part 1 side, the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 are arranged on rotatable parts 3 periphery simultaneously.
Above-mentioned situation for: when the lateral dimension of supporting part 1 is much larger than the semi-circular insulation cover flange plate maximum outside diameter that will install, simultaneously the lateral dimension of rotatable parts 3 be less than the lateral dimension of supporting part 1 and distance between supporting part 1 and rotatable parts 3 side is larger time, the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 can be selected to be arranged on supporting part 1 side, and the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 are arranged on rotatable parts 3 periphery;
When the lateral dimension of described rotatable parts 3 is much larger than the semi-circular insulation cover flange plate maximum outside diameter that will install, simultaneously the lateral dimension of supporting part 1 be less than the lateral dimension of rotatable parts 3 and distance between supporting part 1 and rotatable parts 3 side is larger time, described first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 can be selected to be arranged on rotatable parts 3 side, and the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 are arranged on supporting part 1 periphery.
Described " distance is less ", " distance is larger " are fixed according to the spacing between supporting part 1 and rotatable parts 3 side, when one group of semi-circular insulation cover can only be installed when between supporting part 1 and rotatable parts 3, can be referred to as " distance between supporting part 1 and rotatable parts 3 side is less "; When two groups of different semi-circular insulation covers can be installed when between supporting part 1 from rotatable parts 3, can be referred to as " distance between supporting part 1 and rotatable parts 3 side is larger ".
Clearance requirement between described first multilayer insulation assembly 41 and described second multilayer insulation assembly 42 is greater than 1mm, and the distance between the first multilayer insulation assembly 41 and rotatable parts 3 side and the required distance between the second multilayer insulation assembly 42 and supporting part 1 side are greater than 1mm, prevent between multilayer insulation assembly destroyed because being wound around.
After the design of described semi-circular insulation cover mainly considers that relatively rotating position on astrovehicle completes assembling, then implement thermal control measure, be convenient to the assembling of part.
As follows for the thermal control measure implementation methods relatively rotating position as shown in Figure 1 on astrovehicle:
First, according to specific features and the requirement of supporting part 1 and rotatable parts 3, determine to select semi-circular insulation cover is installed;
Then, to can not the surface of effective coated multilayer insulation assembly, namely the cylindrical shape insulation cover internal surface that supporting part 1 side, rotatingshaft 2 outer surface, rotatable parts 3 side, the first semi-circular insulation cover 5 and the second semi-circular insulation cover 6 are formed cylindrical shape insulation cover internal surface, the 3rd semi-circular insulation cover 9 and the 4th semi-circular insulation cover 10 are formed all carries out subsides aluminium film or polishing treatment, makes skin emissivity lower than 0.1;
Finally, semi-circular insulation cover is installed, thermal insulating pad 7 must be installed, afterwards at supporting part 1 outer surface, all coated multilayer insulation assembly of rotatable parts 3 outer surface and each semi-circular insulation cover outside in each through hole both sides on the semi-circular insulation cover flange plate installed.
Described supporting part 1 outer surface comprises supporting part 1 side and periphery, and described rotatable parts 3 outer surface comprises rotatable parts 3 side and periphery.
Above-mentioned embodiment is just astrovehicle shown in Fig. 1 to relatively rotate position simplified structure schematic diagram, and the spaceborne position that relatively rotates can also for removing other similar structure shown in Fig. 1.
Claims (7)
1. mazy type rotary part thermal insulation apparatus, comprising:
Supporting part (1);
Be inserted into the rotatingshaft (2) in described supporting part (1);
The rotatable parts (3) be connected with described rotatingshaft (2);
Be coated on the first multilayer insulation assembly (41) that described supporting part (1) is outside; With
Be coated on the second multilayer insulation assembly (42) that described rotatable parts (3) are outside;
It is characterized in that,
Position between described supporting part (1) and described rotatable parts (3), is provided with the insulation cover be coated near described rotatingshaft (2) outer surface;
Described insulation cover comprises: be connected to the first semi-circular insulation cover (5) on described supporting part (1) and the second semi-circular insulation cover (6), described first semi-circular insulation cover (5) is relative with described second semi-circular insulation cover (6) snaps onto described rotatingshaft (2) outer surface, and described first multilayer insulation assembly (41) is coated on the outside of described first semi-circular insulation cover (5) and described second semi-circular insulation cover (6);
And/or,
Described insulation cover comprises: be connected to the 3rd semi-circular insulation cover (9) on described rotatable parts (3) and the 4th semi-circular insulation cover (10), described 3rd semi-circular insulation cover (9) is relative with described 4th semi-circular insulation cover (10) snaps onto described rotatingshaft (2) outer surface, and described second multilayer insulation assembly (42) is coated on the outside of described 3rd semi-circular insulation cover (9) and described 4th semi-circular insulation cover (10);
Described first multilayer insulation assembly (41) and/or described second multilayer insulation assembly (42) are coated on the outside of described insulation cover.
2. mazy type rotary part thermal insulation apparatus according to claim 1, it is characterized in that, described first semi-circular insulation cover (5) and the second semi-circular insulation cover (6) are connected on supporting part (1) by set screw (8).
3. mazy type rotary part thermal insulation apparatus according to claim 2, it is characterized in that, described first semi-circular insulation cover (5) is identical with the second semi-circular insulation cover (6) structure, one end is provided with the flange plate for being connected on described supporting part (1), and the other end is semi-circular opening.
4. mazy type rotary part thermal insulation apparatus according to claim 3, is characterized in that, the flange plate both sides on described first semi-circular insulation cover (5) and the second semi-circular insulation cover (6) are provided with thermal insulating pad (7).
5. mazy type rotary part thermal insulation apparatus according to claim 1, it is characterized in that, described 3rd semi-circular insulation cover (9) and the 4th semi-circular insulation cover (10) are connected on rotatable parts (3) by set screw (8).
6. mazy type rotary part thermal insulation apparatus according to claim 5, it is characterized in that, described 3rd semi-circular insulation cover (9) is identical with the 4th semi-circular insulation cover (10) structure, one end is provided with the flange plate for being connected on described rotatable parts (3), and the other end is semi-circular opening.
7. mazy type rotary part thermal insulation apparatus according to claim 6, is characterized in that, the flange plate both sides on described 3rd semi-circular insulation cover (9) and the 4th semi-circular insulation cover (10) are provided with thermal insulating pad (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210278917.9A CN102788137B (en) | 2012-08-07 | 2012-08-07 | Attemperator for labyrinth rotating part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210278917.9A CN102788137B (en) | 2012-08-07 | 2012-08-07 | Attemperator for labyrinth rotating part |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102788137A CN102788137A (en) | 2012-11-21 |
| CN102788137B true CN102788137B (en) | 2014-12-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210278917.9A Expired - Fee Related CN102788137B (en) | 2012-08-07 | 2012-08-07 | Attemperator for labyrinth rotating part |
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| Country | Link |
|---|---|
| CN (1) | CN102788137B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113532116B (en) * | 2021-06-15 | 2023-05-02 | 西安交通大学 | High-temperature rotary material table air pressure furnace |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85100515A (en) * | 1985-04-01 | 1986-08-13 | 中国科学院上海硅酸盐研究所 | Automatically regulate the compound temperature control film and the manufacture method of temperature |
| CN2648191Y (en) * | 2003-09-18 | 2004-10-13 | 王松青 | Hot End Center Sealing Device of Rotary Air Preheater |
| CN2663784Y (en) * | 2003-11-07 | 2004-12-15 | 沈阳华威隔热隔声有限公司 | Radiation shield casing |
| CN101571194A (en) * | 2009-06-02 | 2009-11-04 | 上海师范大学 | Shaft hole heat insulation sealing device |
| CN102261477A (en) * | 2010-05-28 | 2011-11-30 | 江都印染机械有限公司 | Labyrinth air choke device for printing and dyeing industry |
| US20120133126A1 (en) * | 2009-06-02 | 2012-05-31 | Kitano Seiki Co., Ltd. | Cryo-rotary joint |
-
2012
- 2012-08-07 CN CN201210278917.9A patent/CN102788137B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85100515A (en) * | 1985-04-01 | 1986-08-13 | 中国科学院上海硅酸盐研究所 | Automatically regulate the compound temperature control film and the manufacture method of temperature |
| CN2648191Y (en) * | 2003-09-18 | 2004-10-13 | 王松青 | Hot End Center Sealing Device of Rotary Air Preheater |
| CN2663784Y (en) * | 2003-11-07 | 2004-12-15 | 沈阳华威隔热隔声有限公司 | Radiation shield casing |
| CN101571194A (en) * | 2009-06-02 | 2009-11-04 | 上海师范大学 | Shaft hole heat insulation sealing device |
| US20120133126A1 (en) * | 2009-06-02 | 2012-05-31 | Kitano Seiki Co., Ltd. | Cryo-rotary joint |
| CN102261477A (en) * | 2010-05-28 | 2011-11-30 | 江都印染机械有限公司 | Labyrinth air choke device for printing and dyeing industry |
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| Publication number | Publication date |
|---|---|
| CN102788137A (en) | 2012-11-21 |
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Granted publication date: 20141224 Termination date: 20160807 |