CN106184825B - A kind of method for improving fast respone space moonlet thermal control ability - Google Patents
A kind of method for improving fast respone space moonlet thermal control ability Download PDFInfo
- Publication number
- CN106184825B CN106184825B CN201610827985.4A CN201610827985A CN106184825B CN 106184825 B CN106184825 B CN 106184825B CN 201610827985 A CN201610827985 A CN 201610827985A CN 106184825 B CN106184825 B CN 106184825B
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- Prior art keywords
- heat
- thermal control
- thermal
- moonlet
- control component
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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)
- Cooling Or The Like Of Electrical Apparatus (AREA)
- Thermally Actuated Switches (AREA)
Abstract
A kind of device for improving fast respone space moonlet thermal control ability of the disclosure of the invention, belongs to spacecraft Evolution of Thermal Control Technique field.The device includes：Thermal control component, heat conducting pipe, heat-conducting layer, spacing heat sink；Described heat conducting pipe one end connects thermal control component, and the other end connects one or more satellite borne equipments；The other end of thermal control component is connected by heat-conducting layer with spacing heat sink；The thermal control component includes：Thermal insulation layer, heat storage pool, thermo-electric device, thermal switch, wherein the thermal control component between the heat conducting pipe and heat-conducting layer is followed successively by：Heat storage pool, thermo-electric device, thermal switch, the thermal insulation layer are wrapped in the outside of thermal control component.This method for improving fast respone space moonlet thermal control ability, the Active thermal control ability of satellite can be improved with less energy, its satellite borne equipment under multi-track, different intraware consumption conditions is worked in suitable temperature range, accelerate the development speed of moonlet heat control system.
Description
Technical field
The invention belongs to spacecraft Evolution of Thermal Control Technique field.
Background technology
The late 1980s, the U.S. propose fast respone space satellite conception for the first time.Fast respone space satellite
Using cost it is cheap, it is functional, using flexible moonlet and small vehicle as instrument, with rapid development, quickly enter the orbit, quickly
Using for means, the rapid reaction to accident is realized at lower cost.The it is proposed of fast respone space concept brings whole
The change of individual space technology system.
The development of traditional thermal control needs the substantial amounts of time, this with fast respone space moonlet rapid development, enter the orbit, apply
Target run counter to.In order to improve the response speed of moonlet, the thermal control design of satellite must be before task be assigned, in load, star
It is pre-designed and is optimized in the case of parts, track etc. is indefinite.In order that moonlet adapts to different tracks, difference
The change of module dissipation is, it is necessary to strengthen the Active thermal control ability of satellite.
The content of the invention
Fast respone space little Wei under the conditions of multi-track, intraware change of power consumption is difficult in adapt in order to solve prior art
Star thermal design needs of problems, the present invention propose a kind of method for improving fast respone space moonlet thermal control ability, it is intended to
Less energy consumption improves the Active thermal control ability of fast respone space moonlet, makes it in different tracks, different module dissipations
Under conditions of ensure star in equipment be operated in suitable temperature range.
To achieve these goals, the technical solution adopted in the present invention is：
A kind of device for improving fast respone space moonlet thermal control ability, it is characterised in that the device includes：Miniature heat
Control assembly, heat conducting pipe, heat-conducting layer, spacing heat sink；Described heat conducting pipe one end connects miniature thermal control component, other end connection one
Individual or multiple satellite borne equipments；The other end of miniature thermal control component is connected by heat-conducting layer with spacing heat sink；The miniature thermal control
Component processed includes：Thermal insulation layer, heat storage pool, thermo-electric device, miniature thermal switch, wherein between the heat conducting pipe and heat-conducting layer
Miniature thermal control component is followed successively by：Heat storage pool, thermo-electric device, miniature thermal switch, the thermal insulation layer are wrapped in miniature thermal control
The outside of component processed.
Preferably, described heat conducting pipe is built using flexible heat pipe, is close to by heat-conducting silicone grease on satellite borne equipment.
Preferably, spacing heat sink surface scribbles able thermochromic, and its emissivity is with temperature change；When temperature is high, hair
Penetrate that rate is higher, strengthen ability of the heat to space radiation；When temperature is low, emissivity is relatively low, reduces scattering and disappearing for heat.
Preferably, heat storage pool material is foamy carbon.
Preferably, micro thermoelectric device is multistage thermo-electric device, and the ceramic wafer at device both ends is AlN materials.
Preferably, miniature thermal switch changes very greatly in the thermal conductivity of the pattern of opening and closing；It is micro- when temperature is less than 18 DEG C
Type thermal switch is closed, and its thermal conductivity is very low, reduces inside satellite and outside heat exchange；When temperature is higher than 25 DEG C, miniature heat
Switch is opened, and thermal conductivity becomes big, enhancing inside satellite and outside heat exchange.
The combination of thermo-electric device of the present invention, miniature thermal switch and the able thermochromic on spacing heat sink, Neng Gou great
The earth increases the Active thermal control ability of moonlet.When satellite borne equipment temperature is too high, micro thermoelectric device freezes to it, and
Heat is then conducted miniature thermal switch by the another side of micro thermoelectric device, and miniature thermal switch part is heated to be opened, and heat is easily passed
To spacing heat sink, strengthen the heat-sinking capability of heat；Conversely, then thermo-electric device heats to satellite borne equipment, miniature thermal switch closes
Close, reduce scattering and disappearing for heat.When satellite borne equipment is in suitable temperature range, then micro thermoelectric device is neither heated with not making
It is cold, to reduce the consumption of the energy.
Beneficial effects of the present invention：This method for improving fast respone space moonlet thermal control ability, can be with less
Energy improve the Active thermal control ability of satellite, enable its satellite borne equipment under multi-track, different intraware consumption conditions
It is enough to be worked in suitable temperature range, accelerate the development speed of moonlet heat control system.
Brief description of the drawings
Fig. 1 is the scheme of installation of the present invention.
Fig. 2 is the structural representation of the miniature thermal control component of the present invention.
Embodiment
Below in conjunction with the accompanying drawings to a kind of method for improving quick additional space moonlet thermal control ability provided by the invention
Embodiment elaborates.
It is the scheme of installation of the present invention shown in Fig. 1.Satellite is largely divided into two parts：Inside satellite 1 and satellite external surface.
Mainly satellite borne equipment 2, heat conducting pipe 3, miniature thermal control component 4, high-performance heat-conducting layer 5 and satellite appearance are included in inside satellite 1
The spacing heat sink 6 in face.
Heat conducting pipe 3 in Fig. 1 is made up of bendable heat pipe.Its one end is close to power consumption in satellite borne equipment 2 by heat-conducting silicone grease
Big electronic component, the other end are close to miniature thermal control component 4 by heat-conducting silicone grease.
High-performance heat-conducting layer 5 in Fig. 1 is made of the material that thermal conductivity is high, density is small.One face passes through thermal conductive silicon
Fat is close to miniature thermal control component 4, and another face passes through heat-conducting silicone grease snug space heat sink 6.
The surface of spacing heat sink 6 in Fig. 1 scribbles able thermochromic.
It is the structural representation of the miniature thermal control component of the present invention shown in Fig. 2.Miniature thermal control component 4 by thermal insulation layer 7,
Heat storage pool 8, micro thermoelectric device 9 and miniature thermal switch 10 form.
Heat storage pool 8 in Fig. 2 is mainly made of thermal conductivity height, the material that specific heat capacity is big, density is small, such as foamy carbon
Deng.
Micro thermoelectric device 9 in Fig. 2 uses 2 grades of micro thermoelectric devices, and the ceramic wafer on two faces of device is using leading
The ceramic materials such as the preferable AlN of heating rate.
Miniature thermal switch 10 in Fig. 2 uses miniature paraffin thermal switch.
Claims (6)
1. a kind of device for improving fast respone space moonlet thermal control ability, it is characterised in that the device includes：Miniature thermal control
Component (4) processed, heat conducting pipe (3), heat-conducting layer (5), spacing heat sink (6)；Described heat conducting pipe one end connects miniature thermal control component, separately
One end connects one or more satellite borne equipments；The other end of miniature thermal control component is connected by heat-conducting layer with spacing heat sink；Institute
Stating miniature thermal control component includes：Thermal insulation layer (7), heat storage pool (8), thermo-electric device (9), miniature thermal switch (10), wherein
Miniature thermal control component between the heat conducting pipe and heat-conducting layer is followed successively by：Heat storage pool, thermo-electric device, miniature thermal switch,
The thermal insulation layer is wrapped in the outside of miniature thermal control component.
A kind of 2. device for improving fast respone space moonlet thermal control ability as claimed in claim 1, it is characterised in that institute
The heat conducting pipe (3) stated is built using flexible heat pipe, is close to by heat-conducting silicone grease on satellite borne equipment.
A kind of 3. device for improving fast respone space moonlet thermal control ability as claimed in claim 1, it is characterised in that institute
State spacing heat sink (6) surface and scribble able thermochromic, its emissivity is with temperature change；When temperature is high, emissivity is higher, increases
Ability of the heat-flash amount to space radiation；When temperature is low, emissivity is relatively low, reduces scattering and disappearing for heat.
A kind of 4. device for improving fast respone space moonlet thermal control ability as claimed in claim 1, it is characterised in that institute
It is foamy carbon to state heat storage pool material.
A kind of 5. device for improving fast respone space moonlet thermal control ability as claimed in claim 1, it is characterised in that institute
It is multistage thermo-electric device to state thermo-electric device (9), and the ceramic wafer at device both ends is AlN materials.
A kind of 6. device for improving fast respone space moonlet thermal control ability as claimed in claim 1, it is characterised in that institute
The thermal conductivity that miniature thermal switch (10) is stated in the pattern of opening and closing changes very greatly；When temperature is less than 18 DEG C, miniature thermal switch
(10) close, its thermal conductivity is very low, reduces inside satellite and outside heat exchange；When temperature is higher than 25 DEG C, miniature thermal switch
(10) open, thermal conductivity becomes big, enhancing inside satellite and outside heat exchange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610827985.4A CN106184825B (en) | 2016-09-18 | 2016-09-18 | A kind of method for improving fast respone space moonlet thermal control ability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610827985.4A CN106184825B (en) | 2016-09-18 | 2016-09-18 | A kind of method for improving fast respone space moonlet thermal control ability |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106184825A CN106184825A (en) | 2016-12-07 |
| CN106184825B true CN106184825B (en) | 2018-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610827985.4A Expired - Fee Related CN106184825B (en) | 2016-09-18 | 2016-09-18 | A kind of method for improving fast respone space moonlet thermal control ability |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143294B (en) * | 2019-04-11 | 2021-03-09 | 上海卫星工程研究所 | Thermal design structure of full-orbit full-attitude aircraft |
| CN110294146B (en) * | 2019-07-02 | 2023-03-24 | 上海微小卫星工程中心 | On-orbit autonomous operation management method for spacecraft thermal control system |
| CN110712766B (en) * | 2019-10-29 | 2021-07-20 | 北京空间技术研制试验中心 | Hierarchical distributed autonomous thermal control power management method based on integrated electronic system |
| CN113359908B (en) * | 2020-08-17 | 2022-06-28 | 中国科学院微小卫星创新研究院 | Spacecraft satellite-borne single machine on-orbit temperature control system and method |
| CN112849437B (en) * | 2021-01-11 | 2022-09-09 | 中国科学院微小卫星创新研究院 | On-orbit thermal control system and thermal control method for spacecraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11171100A (en) * | 1997-12-12 | 1999-06-29 | Nec Eng Ltd | Passive temperature control device for artificial satellite-mounted equipment |
| CN104477412A (en) * | 2014-11-21 | 2015-04-01 | 上海卫星工程研究所 | Method for on-track control of electronic control heat shield |
| CN204998798U (en) * | 2015-09-30 | 2016-01-27 | 东莞前沿技术研究院 | Close on spacecraft and hot accuse system thereof |
| CN205221138U (en) * | 2015-09-21 | 2016-05-11 | 上海卫星工程研究所 | Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft |
-
2016
- 2016-09-18 CN CN201610827985.4A patent/CN106184825B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11171100A (en) * | 1997-12-12 | 1999-06-29 | Nec Eng Ltd | Passive temperature control device for artificial satellite-mounted equipment |
| CN104477412A (en) * | 2014-11-21 | 2015-04-01 | 上海卫星工程研究所 | Method for on-track control of electronic control heat shield |
| CN205221138U (en) * | 2015-09-21 | 2016-05-11 | 上海卫星工程研究所 | Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft |
| CN204998798U (en) * | 2015-09-30 | 2016-01-27 | 东莞前沿技术研究院 | Close on spacecraft and hot accuse system thereof |
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| Publication number | Publication date |
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| CN106184825A (en) | 2016-12-07 |
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Granted publication date: 20180406 Termination date: 20200918 |