CN107628275A - A kind of outer rotating mechanism relative motion face thermal controls apparatus of star - Google Patents
A kind of outer rotating mechanism relative motion face thermal controls apparatus of star Download PDFInfo
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- CN107628275A CN107628275A CN201710625254.6A CN201710625254A CN107628275A CN 107628275 A CN107628275 A CN 107628275A CN 201710625254 A CN201710625254 A CN 201710625254A CN 107628275 A CN107628275 A CN 107628275A
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- buckle
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- relative motion
- star
- rotating mechanism
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Abstract
The invention discloses rotating mechanism relative motion face thermal controls apparatus outside a kind of star, including the buckle that is in the light, built-in multilayer insulation component, thermal control coating and installation fixing fitting, the buckle that is in the light is fixed on the surface of moving component structural body by installing fixing fitting, cover moving component structure irradiated area, built-in multilayer insulation component is assemblied in the inner surface for the buckle that is in the light, positioned at moving component structural body and it is in the light between buckle, thermal control coating is coated on buckle outer surface of being in the light, related specifications of the spraying method according to space thermal control coating.Present invention accomplishes the temperature requirements of rotating mechanism relative motion face component outside star; simultaneously on the basis of assurance mechanism motion is reliable; the advantages of by way of the buckle combination multilayer insulation component that is locally in the light to take into account thermal control protection effect and anti-hooking, good reliability, strong adaptability, flexible design.
Description
Technical field
The present invention relates to space flight and aviation technical field, the outer rotating mechanism relative motion face thermal controls apparatus of specifically a kind of star.
Background technology
Number biography/relay antenna of current spacecraft configuration either other have multidimensional rotate or the star of sweep mechanism outside carry
Lotus, the space heat flux of its rotatable parts is relative complex, the different parts of synchronization rotating mechanism by according to situation difference can
Can be very big, if thermal control design is improper, the temperature difference of rotating mechanism may reach to a certain degree so that rotating mechanism is stuck or property
It can decline.Traditional Thermal design is to be coated with the uneven influence of isolation space heat flux by rotatable parts entirety thermal control, so
And motion of the overall thermal control method for coating for mechanism itself introduces very big hook risk.
The content of the invention
The invention provides rotating mechanism relative motion face thermal controls apparatus outside a kind of star, pass through the buckle that is in the light, thermal control coating
The thermal control comprehensive Design combined with built-in insulating assembly, there will be the control of the part temperatures in relative motion face in the reasonable scope；
The hook between relative motion face is avoided to influence by way of the buckle that is in the light simultaneously.
The purpose of the present invention is achieved through the following technical solutions：A kind of outer rotating mechanism relative motion face thermal control dress of star
Put, including the buckle that is in the light, built-in multilayer insulation component, thermal control coating and installation fixing fitting, the buckle that is in the light pass through installation
Fixing fitting is fixed on the surface of moving component structural body, covers moving component structure irradiated area, built-in multilayer insulation
Component is assemblied in the inner surface for the buckle that is in the light, between moving component structural body and the buckle that is in the light, thermal control coating coating
In buckle outer surface of being in the light, related specifications of the spraying method according to space thermal control coating.
Preferably, the buckle that is in the light is made up of nonmetallic materials such as polyimide materials, using plastic forming.
Preferably, the built-in multilayer insulation component is made up of the multilayer insulation component of N units, and N can be according to moving component
Choose in the gap in relative motion face.
Preferably, described one unit of multilayer insulation component is separately made up of one layer of reflecting layer and an interlayer interlayer.
Preferably, the thermal control coating species can be according to the rail conditions (low orbit, middle orbit, high rail etc.) of spacecraft
Choose.
Preferably, the installation fixing fitting is the screw of specific standard, and that will be in the light, buckle is fixed on moving component
In structural body.
Present invention accomplishes the temperature requirements of rotating mechanism relative motion face component outside star, while can in assurance mechanism motion
On the basis of leaning on, being locally in the light by way of buckle combination multilayer insulation component to take into account thermal control protection effect and anti-hooking
Advantage, good reliability, strong adaptability, flexible design.
Compared with prior art, the present invention has following beneficial effects：
(1) influence of the space heat flux to rotating mechanism can largely be reduced, the thermograde of reducing mechanism is full
Different temperatures demand during the in-orbit storage of the outer rotating mechanism part of sufficient star or work；
(2) be in the light buckle presence can effectively avoid thermal control design and measure status to the hook risk of rotating mechanism and
The risk of mechanism kinematic is hindered, prevents the release failure of heat-control multilayer, reliability is high；
(3) Thermal design reasonable, material source is abundant, and technique is realized simple and reliable, and cost is relatively low.
Brief description of the drawings
Fig. 1 is the thermal controls apparatus schematic diagram of the outer two-dimensional rotation mechanism moving surface of star of the embodiment of the present invention.
Fig. 2 is the arrangement schematic diagram of buckle and built-in multilayer insulation component of being in the light in the embodiment of the present invention.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in figure 1, the embodiments of the invention provide rotating mechanism relative motion face thermal controls apparatus outside a kind of star, including gear
Light buckle 1, built-in multilayer insulation component 2, thermal control coating 3 and installation fixing fitting, the buckle that is in the light are attached by installing fixation
Part is fixed on the surface of moving component structural body, covers moving component structure irradiated area, built-in multilayer insulation component dress
The inner surface for the buckle that is in the light is fitted over, between moving component structural body and the buckle that is in the light, thermal control coating, which is coated on, to be in the light
Buckle outer surface, related specifications of the spraying method according to space thermal control coating.
The buckle that is in the light is made up of nonmetallic materials such as polyimide materials, using plastic forming.The built-in multilayer
Insulating assembly is made up of the multilayer insulation component of N units, and N can choose according to the gap in moving component relative motion face, typically build
View is between 3~20.Described one unit of multilayer insulation component is separately made up of one layer of reflecting layer and an interlayer interlayer.It is described
Thermal control coating species can be chosen according to the rail conditions (low orbit, middle orbit, high rail etc.) of spacecraft.The installation fixing fitting
For the screw of specific standard, that will be in the light, buckle is fixed in moving component structural body.
Antenna rotation mechanism 5 can carry out the rotational action of two dimension, and U-shaped support both ends have relative motion face, relative fortune
Dynamic face has carried out Thermal design of the present invention and measure processing.
Using above thermal control design method and apparatus, the two-dimensional rotation mechanisms that antennas are passed to number outside certain Satellite have been carried out point
Analysis calculates, and model has carried out necessary simplification and it is assumed that satellite basic parameter, such as track, posture require according to general technical
It is configured；The thermal physical property parameter of satellite thermal control coating and material is chosen to be provided to set by by general technical requirement.Defended according to certain
Star number passes antenna, and data are understood in orbit, using the temperature of two-dimensional rotation mechanism after Thermal design of the present invention and measure
In rational level, number passes the two-dimensional rotation mechanism working stability of antenna for degree control, and performance meets to require.Demonstrate this hair simultaneously
Bright described Thermal design and validity, the reasonability of measure.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (6)
1. the outer rotating mechanism relative motion face thermal controls apparatus of a kind of star, it is characterised in that including the buckle that is in the light, built-in multilayer insulation
Component, thermal control coating and installation fixing fitting, the buckle that is in the light are fixed on moving component structure sheet by installing fixing fitting
On the surface of body, moving component structure irradiated area is covered, built-in multilayer insulation component is assemblied in the inner surface for the buckle that is in the light,
Between moving component structural body and the buckle that is in the light, thermal control coating is coated on buckle outer surface of being in the light.
2. the outer rotating mechanism relative motion face thermal controls apparatus of star as claimed in claim 1, it is characterised in that the buckle that is in the light
It is made up of nonmetallic materials, using plastic forming.
3. the outer rotating mechanism relative motion face thermal controls apparatus of star as claimed in claim 1, it is characterised in that the built-in multilayer
Insulating assembly is made up of the multilayer insulation component of N units, and N can choose according to the gap in moving component relative motion face.
4. the outer rotating mechanism relative motion face thermal controls apparatus of star as claimed in claim 1, it is characterised in that the multilayer insulation
One unit of component is separately made up of one layer of reflecting layer and an interlayer interlayer.
5. the outer rotating mechanism relative motion face thermal controls apparatus of star as claimed in claim 1, it is characterised in that the thermal control coating
Species can be chosen according to the rail conditions of spacecraft.
6. the outer rotating mechanism relative motion face thermal controls apparatus of star as claimed in claim 1, it is characterised in that the installation is fixed
Annex is the screw of specific standard, and that will be in the light, buckle is fixed in moving component structural body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710625254.6A CN107628275B (en) | 2017-07-27 | 2017-07-27 | Relative motion surface thermal control device of extraterrestrial rotating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710625254.6A CN107628275B (en) | 2017-07-27 | 2017-07-27 | Relative motion surface thermal control device of extraterrestrial rotating mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107628275A true CN107628275A (en) | 2018-01-26 |
| CN107628275B CN107628275B (en) | 2020-11-10 |
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ID=61099483
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710625254.6A Active CN107628275B (en) | 2017-07-27 | 2017-07-27 | Relative motion surface thermal control device of extraterrestrial rotating mechanism |
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| Country | Link |
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| CN (1) | CN107628275B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484678A (en) * | 2018-12-20 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of flower-shape unit radiant type thermal control mechanism |
| CN109927940A (en) * | 2019-02-19 | 2019-06-25 | 上海卫星工程研究所 | Solar array driving mechanism temperature barrier |
| CN110775304A (en) * | 2019-11-04 | 2020-02-11 | 深圳航天东方红海特卫星有限公司 | Controllable reciprocating motion thermal control mechanism |
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| RU2014128727A (en) * | 2014-07-11 | 2016-01-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Combined temperature-controlled coating and method of its formation |
| CN105346737A (en) * | 2015-11-30 | 2016-02-24 | 中国空间技术研究院 | Heat control method of laser device of GEO satellite |
| CN205168942U (en) * | 2015-10-23 | 2016-04-20 | 上海利正卫星应用技术有限公司 | Automatic regulation formula heat insulating board |
| CN205366109U (en) * | 2015-08-04 | 2016-07-06 | 上海卫星工程研究所 | Control outer thermal current barn door device |
| CN106467177A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | Substitute the method for satellite side plate and be applied to the multiple structure substituting satellite side plate |
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| RU2014128727A (en) * | 2014-07-11 | 2016-01-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Combined temperature-controlled coating and method of its formation |
| CN104290924A (en) * | 2014-09-17 | 2015-01-21 | 上海卫星工程研究所 | Star sensor temperature control device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484678A (en) * | 2018-12-20 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of flower-shape unit radiant type thermal control mechanism |
| CN109927940A (en) * | 2019-02-19 | 2019-06-25 | 上海卫星工程研究所 | Solar array driving mechanism temperature barrier |
| CN110775304A (en) * | 2019-11-04 | 2020-02-11 | 深圳航天东方红海特卫星有限公司 | Controllable reciprocating motion thermal control mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107628275B (en) | 2020-11-10 |
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