CN211442821U - Folding multi-layer heat shield for spacecraft - Google Patents
Folding multi-layer heat shield for spacecraft Download PDFInfo
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- CN211442821U CN211442821U CN201921986322.2U CN201921986322U CN211442821U CN 211442821 U CN211442821 U CN 211442821U CN 201921986322 U CN201921986322 U CN 201921986322U CN 211442821 U CN211442821 U CN 211442821U
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- thermal
- movable rod
- fixedly connected
- insulated
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Abstract
The utility model discloses a folding multilayer heat shield for spacecraft, which belongs to the field of heat shields, and comprises a mounting wall, wherein a mounting groove is drilled on the mounting wall, the two ends of the mounting groove are respectively connected with a transparent glass plate and a radiation shield main body, the inner wall of the mounting groove is fixedly connected with a pair of guide rails, a threaded rod is connected in one guide rail in a rotating way, a slide bar is fixedly connected in the other guide rail, a motor matched with the threaded rod is fixedly connected in the mounting wall, the threaded rod penetrates through the guide rails and is fixedly connected with the power output end of the motor, a pair of first movable bar and a plurality of second movable bars are arranged between the pair of guide rails, the first movable bar and the second movable bars are straight bars with heat shields, the straight bars are sleeved with the first heat shields, each first movable bar comprises an inner threaded block and a first sliding block, and the inner, the heat shield can be freely unfolded and folded, and the heat dissipation capacity of the heat dissipation surface can be conveniently controlled.
Description
Technical Field
The utility model relates to a heat shield field, more specifically say, relate to a foldable multilayer heat shield for spacecraft.
Background
The radiation type active thermal control technology controls the heat dissipation capacity by adjusting radiation parameters such as the surface absorptivity and emissivity of the spacecraft so as to achieve the purpose of controlling the temperature of the spacecraft. With the development of modern spaceflight, the requirements of multi-attitude, variable orbit, multi-load, multi-function and multi-mode complex-task spacecrafts such as inclined orbit, deep space exploration, planet landing and the like are increasing day by day, the spacecrafts face more and more complex thermal environments, all side surfaces are illuminated alternately, no ideal radiating surface is provided, the radiation type active thermal control technology can effectively solve the thermal control problem of the spacecrafts, and the radiation type active thermal control technology is widely researched and applied. The radiation type active thermal control technology mainly comprises a thermal control shutter, a thermal control rotating disc and an electric control heat shield, and the principle is that a low-emissivity component shields a high-emissivity radiation surface to different degrees to obtain different equivalent emissivity, so that the heat dissipation capacity of the radiation surface is controlled.
The thermal control shutter generally adopts a plurality of rotatable blades as a low-emissivity component, when the blades rotate to a position parallel to the radiating bottom plate, the high-emissivity radiating bottom plate is completely shielded by the low-emissivity blades, the combined emissivity of the radiating surface is the lowest, and the radiating amount is the smallest; when the blades rotate to the position vertical to the radiating bottom plate, the combined emissivity of the radiating surface is highest, and the radiating capacity is maximum. The disadvantages are that: the blades shield the heat dissipation surface more, so that the utilization rate of the heat dissipation surface is reduced; when the blade is closed, the frame leaks heat, and the blade leaks heat.
SUMMERY OF THE UTILITY MODEL
1. Technical problem to be solved
To the problem that exists among the prior art, the utility model aims to provide a foldable multilayer heat shield for spacecraft, it changes the heat radiating area of radiating surface through setting up a folding heat shield to this realizes that the heat shield can freely expand and draw in, conveniently controls the heat dissipation capacity of radiating surface.
2. Technical scheme
In order to solve the above problems, the utility model adopts the following technical proposal.
A folding multi-layer heat shield for a spacecraft comprises an installation wall, wherein the installation wall is provided with an installation groove, two ends of the installation groove are respectively connected with a transparent glass plate and a radiation shield main body, the inner wall of the installation groove is fixedly connected with a pair of guide rails, one guide rail is internally and rotatably connected with a threaded rod, the other guide rail is internally and fixedly connected with a slide rod, the installation wall is internally and fixedly connected with a motor matched with the threaded rod, the threaded rod penetrates through the guide rails and is fixedly connected with the power output end of the motor, a pair of first movable rods and a plurality of second movable rods are arranged between the pair of guide rails, the first movable rods and the second movable rods are straight rods with heat insulation plates, the heat insulation plates are sleeved on the straight rods, the first movable rods comprise inner thread blocks and first sliding blocks, the inner thread blocks are in threaded connection with the threaded rods, the first sliding blocks, the first thermal-insulated unit of fixedly connected with between internal thread piece and the first slider is shielded, the second movable rod includes a pair of second slider, and is a pair of the second slider cup joints respectively on threaded rod and slide bar, and is a pair of be connected with the thermal-insulated unit of second between the second slider and shield, adjacent two be connected with thermal-insulated weaving cloth between the thermal-insulated unit of second screen, be connected through thermal-insulated weaving cloth between first movable rod and the second movable rod, can realize that the heat screen can freely expand and draw in, the convenient heat dissipation capacity of control cooling surface.
Further, thermal-insulated weaving cloth includes thermal-insulated cloth, be connected with the glass fiber layer on the thermal-insulated cloth, thermal-insulated weaving cloth all sews up with first movable rod and second movable rod and is connected, improves the toughness and the intensity of thermal-insulated weaving cloth.
Furthermore, fixedly connected with a pair of and first movable rod assorted sideboard on the inner wall of mounting groove easily seals the space between first movable rod and the mounting groove inner wall.
Furthermore, the upper end and the lower end of the heat insulation plate are respectively attached to the pair of guide rails, so that the heat discharged from a gap between the heat insulation plate and the heat insulation plate is easily reduced.
3. Advantageous effects
Compared with the prior art, the utility model has the advantages of:
(1) the heat dissipation area of the radiating surface is changed by arranging the foldable heat shield, so that the heat shield can be freely unfolded and folded, and the heat dissipation capacity of the radiating surface can be conveniently controlled.
(2) Thermal-insulated weaving cloth is connected with the glass fiber layer including thermal-insulated cloth on the thermal-insulated cloth, and thermal-insulated weaving cloth all sews up with first movable rod and second movable rod and is connected, improves the toughness and the intensity of thermal-insulated weaving cloth.
(3) Fixedly connected with on the inner wall of mounting groove a pair of and first movable rod assorted sideboard easily seal the space between first movable rod and the mounting groove inner wall.
(4) The upper and lower ends of the heat insulation plate are respectively attached to a pair of guide rails, so that the heat discharged from the gap between the heat insulation plate and the heat insulation plate is easily reduced.
Drawings
FIG. 1 is a perspective view of the transparent glass plate removed when the utility model is folded;
FIG. 2 is a top sectional view of the present invention when folded;
FIG. 3 is a schematic view of the structure at A in FIG. 2;
FIG. 4 is a top sectional view of the present invention when it is deployed;
fig. 5 is a front sectional view of the present invention.
The reference numbers in the figures illustrate:
the radiation screen comprises a mounting wall 1, a transparent glass plate 2, a guide rail 3, a motor 4, a threaded rod 5, a first movable rod 6, a second movable rod 7, a sliding rod 8, a first heat insulation unit screen 9, a second heat insulation unit screen 10, heat insulation woven cloth 11, a side plate 12 and a radiation screen body 13.
Detailed Description
The technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiment of the present invention; obviously, the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention based on the embodiments of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top/bottom", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "sleeved/connected", "connected", and the like are to be understood in a broad sense, such as "connected", which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected with each other or indirectly through an intermediate medium, or they may be connected with each other through the inside of two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1:
referring to fig. 1-3, a folding multi-layer heat shield for a spacecraft comprises a mounting wall 1, wherein a mounting groove is formed in the mounting wall 1, two ends of the mounting groove are respectively connected with a transparent glass plate 2 and a radiation shield main body 13, a pair of guide rails 3 are fixedly connected to the inner wall of the mounting groove, a threaded rod 5 is rotatably connected to one guide rail 3, a slide bar 8 is fixedly connected to the other guide rail 3, a motor 4 matched with the threaded rod 5 is fixedly connected to the mounting wall 1, the threaded rod 5 penetrates through the guide rails 3 and is fixedly connected with the power output end of the motor 4, a pair of guide rails 3 are arranged between each pair of guide rails, a pair of first movable rods 6 and a plurality of second movable rods 7 form a folding heat shield, the first movable rods 6 and the second movable rods 7 are straight rods with heat shields sleeved on the straight rods, the upper and lower ends of the, easily reduce from the heat insulating board and 3 between the exhaust heat in space, fixedly connected with on the inner wall of mounting groove a pair of and first movable rod 6 assorted sideboard 12, easily seal the space between first movable rod 6 and the mounting groove inner wall.
Referring to fig. 2-5, the first movable rod 6 includes an internal thread block and a first sliding block, the internal thread block is in threaded connection with the threaded rod 5, the first sliding block is slidably connected to the sliding rods 8, a through hole is drilled on the internal thread block at the lower end of one of the first movable rods 6, and both the upper and lower ends of the first movable rod 6 are fixedly connected to the guide rail 3, so that the threaded rod 5 only drives one first movable rod 6 to move when rotating, a first thermal insulation unit screen 9 is fixedly connected between the internal thread block and the first sliding block, the second movable rod 7 includes a pair of second sliding blocks, the pair of second sliding blocks are respectively sleeved on the threaded rod 5 and the sliding rods 8, a second thermal insulation unit screen 10 is connected between the pair of second sliding blocks, a thermal insulation textile fabric 11 is connected between two adjacent second thermal insulation unit screens 10, the thermal insulation textile fabric 11 includes a thermal insulation fabric, a glass fiber layer is connected to the thermal insulation textile fabric 11, and the first movable rod 6 and the second movable rod 7 are both connected, the toughness and the strength of the heat insulation textile cloth 11 are improved, and the first movable rod 6 is connected with the second movable rod 7 through the heat insulation textile cloth 11.
When the folding screen is used, a user controls the motor 4 to drive the threaded rod 5 to rotate clockwise, so that the first movable rod 6 moves along the length direction of the guide rail 3, the first movable rod 6 drives the second movable rod 7 to move until the first movable rod 6 is attached to the side plates 12, the first movable rod 6 and the second movable rod 7 are unfolded completely, the unfolded first movable rod 6 and the unfolded second movable rod 7 completely cover the mounting groove, heat insulation is carried out through the action of the first movable rods 6 and the second movable rods 7, a gap between the first movable rod 6 and the inner wall of the mounting groove is sealed through the action of the side plates 12, heat passing through the mounting groove is reduced, the heat insulation effect is realized, when the folding screen needs to be folded, the motor 4 is controlled to drive the threaded rod 5 to rotate anticlockwise, the first movable rod 6 is reset, the first movable rod 6 drives the second movable rod 7 to move in the resetting process, the first movable rod 6 and the second movable rod 7 are folded, the heat shield is folded and folded, the radiation shield main body 13 is shielded and insulated by controlling the overall folding degree of the heat shield, and therefore the heat dissipation area of the radiation shield main body 13 is changed, and the heat dissipation capacity of the radiation shield main body 13 is controlled.
The above description is only the preferred embodiment of the present invention; the scope of the present invention is not limited thereto. Any person skilled in the art should also be able to cover the technical scope of the present invention by replacing or changing the technical solution and the improvement concept of the present invention with equivalents and modifications within the technical scope of the present invention.
Claims (4)
1. A folding multilayer heat shield for a spacecraft comprises a mounting wall (1), and is characterized in that: the mounting wall (1) is provided with a mounting groove, two ends of the mounting groove are respectively connected with a transparent glass plate (2) and a radiation screen main body (13), a pair of guide rails (3) are fixedly connected on the inner wall of the mounting groove, a threaded rod (5) is rotationally connected in one guide rail (3), a sliding rod (8) is fixedly connected in the other guide rail (3), a motor (4) matched with the threaded rod (5) is fixedly connected in the mounting wall (1), the threaded rod (5) penetrates through the guide rails (3) and is fixedly connected with the power output end of the motor (4), a pair of first movable rods (6) and a plurality of second movable rods (7) are arranged between the pair of guide rails (3), the first movable rod (6) and the second movable rod (7) are straight rods with heat insulation plates, and the heat insulation plates are sleeved on the straight rods;
first movable rod (6) include internal thread piece and first slider, internal thread piece and threaded rod (5) threaded connection, first slider sliding connection is on slide bar (8), the first thermal-insulated unit of fixedly connected with between internal thread piece and the first slider screen (9), second movable rod (7) are including a pair of second slider, and are a pair of the second slider cup joints respectively on threaded rod (5) and slide bar (8), and is a pair of be connected with the thermal-insulated unit of second between the second slider screen (10), adjacent two be connected with thermal-insulated weaving cloth (11) between the thermal-insulated unit of second screen (10), be connected through thermal-insulated weaving cloth (11) between first movable rod (6) and second movable rod (7).
2. The foldable multi-layer heat shield for a spacecraft of claim 1, wherein: thermal-insulated weaving cloth (11) is including thermal-insulated cloth, be connected with the glass fiber layer on the thermal-insulated cloth, thermal-insulated weaving cloth (11) are all sewed up with first movable rod (6) and second movable rod (7) and are connected.
3. The foldable multi-layer heat shield for a spacecraft of claim 1, wherein: the inner wall of the mounting groove is fixedly connected with a pair of side plates (12) matched with the first movable rod (6).
4. The foldable multi-layer heat shield for a spacecraft of claim 1, wherein: the upper end and the lower end of the heat insulation plate are respectively attached to the pair of guide rails (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921986322.2U CN211442821U (en) | 2019-11-18 | 2019-11-18 | Folding multi-layer heat shield for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921986322.2U CN211442821U (en) | 2019-11-18 | 2019-11-18 | Folding multi-layer heat shield for spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211442821U true CN211442821U (en) | 2020-09-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921986322.2U Expired - Fee Related CN211442821U (en) | 2019-11-18 | 2019-11-18 | Folding multi-layer heat shield for spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211442821U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112634672A (en) * | 2020-12-28 | 2021-04-09 | 安徽文香信息技术有限公司 | Foldable retractable anti-reflection device for electronic blackboard |
-
2019
- 2019-11-18 CN CN201921986322.2U patent/CN211442821U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112634672A (en) * | 2020-12-28 | 2021-04-09 | 安徽文香信息技术有限公司 | Foldable retractable anti-reflection device for electronic blackboard |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20201222 Address after: 110000 No.37, Daoyi South Street, Shenbei New District, Shenyang City, Liaoning Province Patentee after: SHENYANG AEROSPACE University Address before: Shenyang University of Aeronautics and Astronautics Patentee before: Wang Beichao |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200908 Termination date: 20211118 |