CN109484678A - A kind of flower-shape unit radiant type thermal control mechanism - Google Patents
A kind of flower-shape unit radiant type thermal control mechanism Download PDFInfo
- Publication number
- CN109484678A CN109484678A CN201811560708.7A CN201811560708A CN109484678A CN 109484678 A CN109484678 A CN 109484678A CN 201811560708 A CN201811560708 A CN 201811560708A CN 109484678 A CN109484678 A CN 109484678A
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- thermal control
- flower
- shape piece
- bottom plate
- control mechanism
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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
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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)
- Cultivation Receptacles Or Flower-Pots, Or Pots For Seedlings (AREA)
Abstract
The present invention provides a kind of flower-shape unit radiant type thermal control mechanism, the thermal control mechanism is made of several Thermal control units, and each Thermal control units are made of top plate, flower-shape piece, bottom plate；Thermal control window is opened on top plate, the flower-shape piece is located in thermal control window；The material of the flower-shape piece is temperature sensitive deformable material, and has deformation restorability.Flower-shape piece surface has low infrared emissivity and low sunlight absorptivity, and bottom plate has high IR emissivity.It is affected by temperature, the deformation of flower-shape piece, the RADIATION ANGLE COEFFICIENT of bottom plate and space changes, thus the effective thermal emissivity of changing mechanism.Flower-shape unit radiant type thermal control mechanism structure of the invention is simple, not power consumption, high reliablity, effective infrared emittance energy autonomous control of each unit, and then flexibly, effectively controls the temperature field of satellite.
Description
Technical field
The present invention relates to spacecraft thermal control technical field more particularly to a kind of radiant type thermal control mechanisms.
Background technique
The thermal control mechanism of spacecraft is mainly used to the structure member for guaranteeing spacecraft and instrument and equipment under space environment
In a suitable temperature range, mechanism so that they can work normally.The thermal control mode being widely used on current spacecraft is big
Cause is divided into passive type and active two major classes.
Passive type thermal control is a kind of open loop type control, and relying primarily on rational deployment and selecting has appropriate thermophysical property
Material and thermal controls apparatus relatively simple for structure carry out tissue heat transfer process, this passive type thermal control mechanism is simple and easy, performance can
It leans on and long working life, but does not have the ability of automatic adjustment temperature generally.
Passive radiation type Active thermal control mechanism is to adjust heat loss through radiation using temperature sensitive driver drives action component
Ability and control temperature.There is the radiation thermal control mechanism of application to have Thermal Control Shutter, thermal control turntable and soft on spacecraft at present
Property blade thermal control mechanism etc..This active thermal control mechanism can be controlled in the case where Orbital heat flux and inner heat source change greatly
Control equipment temperature, and it is simple and reliable for structure, temperature control precision is high, therefore using relatively wide on spacecraft.But it is this kind of active
Thermal control mechanism it is more complicated, necessarily increase the quality of heat control system, power consumption is bigger.
Summary of the invention
In order to solve the problems in the prior art, the present invention provides a kind of flower-shape unit radiant type thermal control mechanism, pass through
Control the thermal radiation property control that each Thermal control units flower-shape plate shape realizes entire mechanism.The present invention is especially by following technology
Scheme is realized:
A kind of flower-shape unit radiant type thermal control mechanism, the thermal control mechanism are made of several Thermal control units, each thermal control list
Member is made of top plate, flower-shape piece, bottom plate；Top plate and bottom plate thermal conductive contact are installed, the opened round thermal control window on top plate, the flower-shape
Piece is located in thermal control window, and flower-shape piece is made of the petal limb of several radiating helicals；The material of the flower-shape piece is quick to temperature
Feel deformable material, and there is deformation restorability.
As a further improvement of the present invention, all limbs are identical, and limb top is interconnected in thermal control window center,
It is connected to end section on thermal control window circumference.
As a further improvement of the present invention, flower-shape piece surface has low infrared emissivity and low sunlight absorptivity, described
Bottom plate has high IR emissivity.
As a further improvement of the present invention, when the object temperature that Thermal control units are controlled increases, flower-shape piece temperature
Increase, the deformation of every limb of flower-shape piece, limb and bottom plate angle increase so that on bottom plate high emissivity surface and space spoke
Firing angle coefficient increases, and is conducive to the outside dissipation of heat.
As a further improvement of the present invention, when the object temperature that Thermal control units are controlled reduces, every valve of flower-shape piece
Piece deformation, limb and bottom plate angle reduce so that high emissivity surface reduces the RADIATION ANGLE COEFFICIENT of space on bottom plate, reduce to
The heat of outer dissipation.
The beneficial effects of the present invention are: flower-shape unit radiant type thermal control mechanism structure of the invention is simple, not power consumption, reliably
Property high, effective infrared emittance energy autonomous control of each unit, and then flexibly, the temperature field of effectively control satellite.
Detailed description of the invention
Fig. 1 is the Thermal control units composition schematic diagram of flower-shape unit radiant type thermal control mechanism of the invention.
Specific embodiment
The present invention is further described for explanation and specific embodiment with reference to the accompanying drawing.
Flower-shape unit radiant type thermal control mechanism of the invention is made of several Thermal control units, and each Thermal control units are a flowers
Shape thermal control window, as shown in Figure 1.
Each Thermal control units are made of top plate (1), flower-shape piece (3), bottom plate (2).Top plate (1) and bottom plate (2) thermal conductive contact
Installation, the opened round thermal control window on top plate (1), the flower-shape piece (3) are located in thermal control window.
Flower-shape piece (3) is made of the petal limb of several radiating helicals.All limbs are identical, and limb top is mutually connected
It connects in thermal control window center, is connected to end section on thermal control window circumference.
The material of flower-shape piece (3) is temperature sensitive deformable material, and has deformation restorability.Flower-shape piece (3)
Surface has low infrared emissivity and low sunlight absorptivity, and bottom plate has high IR emissivity.
When the object temperature that Thermal control units are controlled increases, flower-shape piece temperature is also increased, and every limb of flower-shape piece becomes
Shape, limb and bottom plate angle increase, so that the RADIATION ANGLE COEFFICIENT of high emissivity surface and space increases on bottom plate, are conducive to heat
Outside dissipation.When the object temperature that Thermal control units are controlled reduces, every limb deformation of flower-shape piece, limb subtracts with bottom plate angle
It is small, so that high emissivity surface reduces the RADIATION ANGLE COEFFICIENT of space on bottom plate, reduce the heat of outside dissipation.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all utilizations
Equivalent structure or equivalent flow shift made by description of the invention and accompanying drawing content is applied directly or indirectly in other correlations
Technical field, be included within the scope of the present invention.
For those of ordinary skill in the art, without departing from the inventive concept of the premise, if can also make
Simple deduction or replace are done, all shall be regarded as belonging to protection scope of the present invention.
Claims (5)
1. a kind of flower-shape unit radiant type thermal control mechanism, it is characterised in that: the thermal control mechanism is made of several Thermal control units, often
A Thermal control units are made of top plate, flower-shape piece, bottom plate；Top plate and bottom plate thermal conductive contact are installed, the opened round thermal control window on top plate,
The flower-shape piece is located in thermal control window, and flower-shape piece is made of the petal limb of several radiating helicals；The material of the flower-shape piece is
Temperature sensitive deformable material, and there is deformation restorability.
2. thermal control mechanism according to claim 1, it is characterised in that: all limbs are identical, and limb top is mutually connected
It connects in thermal control window center, is connected to end section on thermal control window circumference.
3. thermal control mechanism according to claim 1, it is characterised in that: flower-shape piece surface have low infrared emissivity and it is low too
Positive absorptivity, the bottom plate have high IR emissivity.
4. thermal control mechanism according to claim 1-3, it is characterised in that: when the object temperature that Thermal control units are controlled
When degree increases, flower-shape piece temperature is also increased, and the every limb deformation of flower-shape piece, limb and bottom plate angle increase, so that on bottom plate
The RADIATION ANGLE COEFFICIENT of high emissivity surface and space increases, and is conducive to the outside dissipation of heat.
5. thermal control mechanism according to claim 1-3, it is characterised in that: when the object temperature that Thermal control units are controlled
When degree reduces, the every limb deformation of flower-shape piece, limb and bottom plate angle reduce, so that high emissivity surface is to space on bottom plate
RADIATION ANGLE COEFFICIENT reduces, and reduces the heat of outside dissipation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811560708.7A CN109484678B (en) | 2018-12-20 | 2018-12-20 | Flower-shaped unit radiation type thermal control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811560708.7A CN109484678B (en) | 2018-12-20 | 2018-12-20 | Flower-shaped unit radiation type thermal control mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109484678A true CN109484678A (en) | 2019-03-19 |
| CN109484678B CN109484678B (en) | 2021-11-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811560708.7A Active CN109484678B (en) | 2018-12-20 | 2018-12-20 | Flower-shaped unit radiation type thermal control mechanism |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4813476A (en) * | 1987-10-21 | 1989-03-21 | The United States Of America As Represented By The Secretary Of The Air Force | Expandable pulse power spacecraft radiator |
| CN102249009A (en) * | 2011-05-12 | 2011-11-23 | 南京理工大学 | Thermochromism emittance-variable thermal control device for spacecrafts |
| CN103448924A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Mechanical and thermal integrated device of high-power-consumption solar array drive mechanism for satellite |
| CN105059528A (en) * | 2015-07-23 | 2015-11-18 | 致导科技（北京）有限公司 | Foldable unmanned aerial vehicle |
| CN106553773A (en) * | 2016-10-28 | 2017-04-05 | 深圳航天东方红海特卫星有限公司 | A kind of reversible locking radiation thermal control mechanism |
| CN106742077A (en) * | 2016-11-29 | 2017-05-31 | 深圳航天东方红海特卫星有限公司 | A kind of thermal control mechanism of iris component and its iris formula |
| CN107628275A (en) * | 2017-07-27 | 2018-01-26 | 上海卫星工程研究所 | A kind of outer rotating mechanism relative motion face thermal controls apparatus of star |
| US20180134418A1 (en) * | 2016-11-15 | 2018-05-17 | United States Of America As Represented By The Administrator Of Nasa | In-Situ Passivation and Insulation Layer for a Flexible Thermal Protection System (FTPS) |
-
2018
- 2018-12-20 CN CN201811560708.7A patent/CN109484678B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4813476A (en) * | 1987-10-21 | 1989-03-21 | The United States Of America As Represented By The Secretary Of The Air Force | Expandable pulse power spacecraft radiator |
| CN102249009A (en) * | 2011-05-12 | 2011-11-23 | 南京理工大学 | Thermochromism emittance-variable thermal control device for spacecrafts |
| CN103448924A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Mechanical and thermal integrated device of high-power-consumption solar array drive mechanism for satellite |
| CN105059528A (en) * | 2015-07-23 | 2015-11-18 | 致导科技（北京）有限公司 | Foldable unmanned aerial vehicle |
| CN106553773A (en) * | 2016-10-28 | 2017-04-05 | 深圳航天东方红海特卫星有限公司 | A kind of reversible locking radiation thermal control mechanism |
| US20180134418A1 (en) * | 2016-11-15 | 2018-05-17 | United States Of America As Represented By The Administrator Of Nasa | In-Situ Passivation and Insulation Layer for a Flexible Thermal Protection System (FTPS) |
| CN106742077A (en) * | 2016-11-29 | 2017-05-31 | 深圳航天东方红海特卫星有限公司 | A kind of thermal control mechanism of iris component and its iris formula |
| CN107628275A (en) * | 2017-07-27 | 2018-01-26 | 上海卫星工程研究所 | A kind of outer rotating mechanism relative motion face thermal controls apparatus of star |
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| CN109484678B (en) | 2021-11-23 |
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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Applicant after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd. Address before: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Applicant before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. |
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