CN107264843A - The outer unit temperature protective device of light special-shaped star - Google Patents
The outer unit temperature protective device of light special-shaped star Download PDFInfo
- Publication number
- CN107264843A CN107264843A CN201710354826.1A CN201710354826A CN107264843A CN 107264843 A CN107264843 A CN 107264843A CN 201710354826 A CN201710354826 A CN 201710354826A CN 107264843 A CN107264843 A CN 107264843A
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- Prior art keywords
- star
- light
- heat
- multilayer
- outer unit
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Classifications
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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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses unit outside unit temperature protective device, including integral light framework, heat-insulated multilayer, star outside a kind of light special-shaped star, integral light framework is arranged on the periphery of the outer unit of star, and heat-insulated multilayer is wrapped in the outside of integral light framework.Light weight of the present invention, simple in construction, manufacturing cost are low; it is mainly used in unit or the space protection and heat-insulated multilayer coating structure demand of important feature outside satellite; ensure that the support that multilayer is coated to unit appearance is protected; the requirement of Satellite Payloads visual field and satellite platform mechanical property is met simultaneously; structure design is convenient, effective utilization space, with higher versatility.
Description
Technical field
The present invention relates to a kind of temperature protective device, the outer unit temperature protection dress of more particularly to a kind of light special-shaped star
Put.
Background technology
At present, politics, economy, national defence etc. propose higher and higher requirement to satellite so that satellite is towards high stable, height
Precision, high-resolution direction are developed.Because satellite high-precision attitude information is provided by star sensor, this installation to star sensor
Precision, operating ambient temperature etc. propose harsher requirement.Satellite star sensor is arranged on effective load by star sensor'support
He Anzhuanjiaochu, belongs to the outer unit of star, and the high-precision requirement and complex appearance of star sensor'support, star sensor are not easy to directly
Multilayer coating structure is thermally shielded, therefore, it is current high-precision design of satellites research that Design of Temperature Control is carried out to unit outside special-shaped star
Emphasis.
Conventional structural framing design often uses hardware and screw connecting mode, and to the limit of satellite quality
System is extremely harsh, and traditional construction design method can not meet the demand of New Satellite development, and satellite is in emission process in addition
Extremely complex mechanical environment is faced with, this rigidity property to multistory frame, stability it is also proposed requirement.
Therefore, for satellite sensor and its support, design one kind had both considered heat-insulated multilayer coating structure manufacturability, easily implemented
Property, it is further contemplated that the light heat-proof device of structural system load, light weight, urgent problem to be solved is developed as satellite.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of outer unit temperature protective device of light special-shaped star, its matter
Light, the simple in construction, manufacturing cost of amount is low, is mainly used in unit or the space protection and heat-insulated multilayer of important feature outside satellite
There is provided preferably temperature protection and support stiffness for cladding demand, it is ensured that the support that multilayer is coated to unit appearance is protected, simultaneously full
Sufficient Satellite Payloads visual field and the requirement of satellite platform mechanical property, structure design is convenient, effective utilization space, with higher
Versatility, it is adaptable to the harsh temperature control needs of the outer special-shaped unit of Large-scale satellite platform star.
The present invention is to solve above-mentioned technical problem by following technical proposals：A kind of outer unit temperature of light special-shaped star
Protection device is spent, it includes the outer unit of integral light framework, heat-insulated multilayer, star, integral light framework is arranged on single outside star
The periphery of machine, heat-insulated multilayer is wrapped in the outside of integral light framework.
Preferably, the thickness of the integral light framework is 2mm, and material is T800 type carbon fibers, using integral chemical conversion
Type structure, frame shape is designed according to special-shaped unit external envelope.
Preferably, there are two threading holes on each moulding of the integral light framework.
Preferably, the thickness of the heat-insulated multilayer is not less than 4mm, and multilayer suture is polyester-cotton blend line.
Preferably, the heat-insulated multilayer uses the low temperature multilevel-cell of 20 layer units, operating temperature control -196~+
120℃。
Preferably, each multilevel-cell of the heat-insulated multilayer is by one layer of polyamide fibre silk screen and one layer of two-sided aluminized mylar
Composition.
The positive effect of the present invention is：The present invention can provide preferably temperature protection and support stiffness, it is adaptable to
The harsh temperature control needs of the outer special-shaped unit of Large-scale satellite platform star.Compared to prior art, with following progress effect：
One, traditional heat-insulated mode is coated using heat-insulated multilayer to conventional structure profile, and complex appearance is difficult to carry out
Multilayer insulation, the device is covered on the outer unit of star using integral light framework, then carried out on the surface of integral light framework
The cladding of heat-insulated multilayer, solves special-shaped unit and implements the problem of temperature control difficulty is big, serves good insulation and heat-insulated
Effect.
Two, traditional structure framework is assembled using hardware and screw connecting mode, and the integration of the device is light
Matter framework carries out integrated forming technique using composite, and portable construction is suitable for defend extremely strict to quality requirement
On star.
Three, the integral light framework of the device uses T800 type carbon fibre materials, not only reduces architecture quality, it is ensured that
Enough strength and stiffness, the displacement deformation under the complicated mechanical environment of satellite launch powered phase is small, it is to avoid with outside star
Payload is interfered.
Brief description of the drawings
Fig. 1 is the scheme of installation of the outer unit temperature protective device of the light special-shaped star of the present invention.
Fig. 2 is the structural representation before the outer unit temperature protective device wrapped multiple of the light special-shaped star of the present invention.
Fig. 3 is the structural representation after the outer unit temperature protective device wrapped multiple of the light special-shaped star of the present invention.
Embodiment
Present pre-ferred embodiments are provided below in conjunction with the accompanying drawings, to describe technical scheme in detail.
As shown in Figure 1 to Figure 3, the outer unit temperature protective device of the light special-shaped star of the present invention includes integral light framework
1st, the outer unit 3 of heat-insulated multilayer 2, star, integral light framework 1 is arranged on the periphery of the outer unit 3 of star, and heat-insulated multilayer 2 is wrapped in one
The outside of body lightweight frame 1.
The thickness of integral light framework 1 is 2mm, and material is T800 type carbon fibers, using integrated molding structure, framework
Shape is designed according to special-shaped unit external envelope.
There are two threading holes on each moulding of integral light framework 1.
The thickness of heat-insulated multilayer 2 is not less than 4mm, and multilayer suture is polyester-cotton blend line.
Heat-insulated multilayer 2 is using the low temperature multilayer of 20 layer units, and operating temperature control is at -196~+120 DEG C.
Each multilevel-cell of heat-insulated multilayer 2 is made up of one layer of polyamide fibre silk screen and one layer of two-sided aluminized mylar.
A kind of outer unit temperature protective device of light special-shaped star that the present invention is provided, its use integral light framework for
Heat-insulated multilayer is provided a supporting role, while meeting the complicated mechanical environment requirement of satellite powered phase, heat-insulated multilayer passes through suture
Suture is coated on lightweight frame surface, so as to carry out temperature control to unit outside star.
In summary, the present invention can provide preferably temperature protection and support stiffness, it is adaptable to outside Large-scale satellite platform star
The harsh temperature control needs of special-shaped unit.Compared to prior art, with following progress effect：
One, traditional heat-insulated mode is coated using heat-insulated multilayer to conventional structure profile, and complex appearance is difficult to carry out
Multilayer insulation, the device is covered on the outer unit of star using integral light framework, then carried out on the surface of integral light framework
The cladding of heat-insulated multilayer, solves special-shaped unit and implements the problem of temperature control difficulty is big, serves good insulation and heat-insulated
Effect.
Two, traditional structure framework is assembled using hardware and screw connecting mode, and the integration of the device is light
Matter framework carries out integrated forming technique using composite, and portable construction is suitable for defend extremely strict to quality requirement
On star.
Three, the integral light framework of the device uses T800 type carbon fibre materials, not only reduces architecture quality, it is ensured that
Enough strength and stiffness, the displacement deformation under the complicated mechanical environment of satellite launch powered phase is small, it is to avoid with outside star
Payload is interfered.
Particular embodiments described above, technical problem, technical scheme and beneficial effect to the solution of the present invention are carried out
It is further described, should be understood that the specific embodiment that the foregoing is only of the invention, be not limited to
The present invention, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc. should be included in this
Within the protection domain of invention.
Claims (6)
1. a kind of outer unit temperature protective device of light special-shaped star, it is characterised in that it includes integral light framework, heat-insulated
The outer unit of multilayer, star, integral light framework is arranged on the periphery of the outer unit of star, and heat-insulated multilayer is wrapped in integral light framework
Outside.
2. the outer unit temperature protective device of light special-shaped star as claimed in claim 1, it is characterised in that the integration is light
The thickness of matter framework is 2mm, and material is T800 type carbon fibers, and using integrated molding structure, frame shape is according to special-shaped unit
External envelope is designed.
3. the outer unit temperature protective device of light special-shaped star as claimed in claim 1, it is characterised in that the integration is light
There are two threading holes on each moulding of matter framework.
4. the outer unit temperature protective device of light special-shaped star as claimed in claim 1, it is characterised in that the heat-insulated multilayer
Thickness be not less than 4mm, multilayer suture be polyester-cotton blend line.
5. the outer unit temperature protective device of light special-shaped star as claimed in claim 1, it is characterised in that the heat-insulated multilayer
Using the low temperature multilevel-cell of 20 layer units, operating temperature is controlled at -196~+120 DEG C.
6. the outer unit temperature protective device of light special-shaped star as claimed in claim 5, it is characterised in that the heat-insulated multilayer
Each multilevel-cell be made up of one layer of polyamide fibre silk screen and one layer of two-sided aluminized mylar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354826.1A CN107264843A (en) | 2017-05-18 | 2017-05-18 | The outer unit temperature protective device of light special-shaped star |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354826.1A CN107264843A (en) | 2017-05-18 | 2017-05-18 | The outer unit temperature protective device of light special-shaped star |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107264843A true CN107264843A (en) | 2017-10-20 |
Family
ID=60064032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710354826.1A Pending CN107264843A (en) | 2017-05-18 | 2017-05-18 | The outer unit temperature protective device of light special-shaped star |
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| CN (1) | CN107264843A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN112366438A (en) * | 2020-10-22 | 2021-02-12 | 西安空间无线电技术研究所 | Satellite-borne antenna multilayer composite temperature control cover |
| CN114180104A (en) * | 2021-12-30 | 2022-03-15 | 中国科学院长春光学精密机械与物理研究所 | High-precision temperature control device of space optical remote sensing satellite star sensor |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020096601A1 (en) * | 2001-01-24 | 2002-07-25 | Myers Franklin K. | Large thermal protection system panel |
| US20030025040A1 (en) * | 2001-08-06 | 2003-02-06 | Kawasaki Jukogyo Kabushiki Kaisha | Thermal protection structure |
| CN104554822A (en) * | 2014-12-31 | 2015-04-29 | 哈尔滨工业大学 | Multilayer hollow interlayer inflated cabin |
| CN106428642A (en) * | 2016-08-16 | 2017-02-22 | 北京空间飞行器总体设计部 | Open type circular truncated cone-shaped thermal insulation devices for spacecraft thrusters |
-
2017
- 2017-05-18 CN CN201710354826.1A patent/CN107264843A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020096601A1 (en) * | 2001-01-24 | 2002-07-25 | Myers Franklin K. | Large thermal protection system panel |
| US20030025040A1 (en) * | 2001-08-06 | 2003-02-06 | Kawasaki Jukogyo Kabushiki Kaisha | Thermal protection structure |
| CN104554822A (en) * | 2014-12-31 | 2015-04-29 | 哈尔滨工业大学 | Multilayer hollow interlayer inflated cabin |
| CN106428642A (en) * | 2016-08-16 | 2017-02-22 | 北京空间飞行器总体设计部 | Open type circular truncated cone-shaped thermal insulation devices for spacecraft thrusters |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN112366438A (en) * | 2020-10-22 | 2021-02-12 | 西安空间无线电技术研究所 | Satellite-borne antenna multilayer composite temperature control cover |
| CN114180104A (en) * | 2021-12-30 | 2022-03-15 | 中国科学院长春光学精密机械与物理研究所 | High-precision temperature control device of space optical remote sensing satellite star sensor |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171020 |
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