CN108791964A - A kind of thermal protection method and apparatus suitable for star outside antenna rectangular waveguide - Google Patents
A kind of thermal protection method and apparatus suitable for star outside antenna rectangular waveguide Download PDFInfo
- Publication number
- CN108791964A CN108791964A CN201810622991.5A CN201810622991A CN108791964A CN 108791964 A CN108791964 A CN 108791964A CN 201810622991 A CN201810622991 A CN 201810622991A CN 108791964 A CN108791964 A CN 108791964A
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- Prior art keywords
- waveguide
- heat
- star
- dissipating fin
- temperature
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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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/02—Arrangements for de-icing; Arrangements for drying-out ; Arrangements for cooling; Arrangements for preventing corrosion
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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)
- Details Of Aerials (AREA)
Abstract
The present invention provides a kind of temperature barriers suitable for star outside antenna rectangular waveguide, including multilayer insulation component, waveguide heat-dissipating fin, thermal control coating, heating element and thermistor, the multilayer insulation component is coated on waveguide surrounding, and the opening stretched out for waveguide heat-dissipating fin is left at waveguide edge；The heat-dissipating fin and waveguide are integrated, and waveguide heat-dissipating fin two sides is pasted with thermal control coating, and the heating element is mounted on waveguide outer surface, for providing thermal compensation when low temperature storage；The thermistor is pasted onto waveguide outer surface, and to measure waveguide temperature, whether control heater assembly provides thermal compensation.The present invention can largely reduce influence of the space heat flux to star outer waveguide, reduce temperature gradient and the fluctuation of star outer waveguide, increase thermal environment stability when waveguide work；Thermal design reasonable of the present invention, it is few to consume electric resources on star, technique realize it is simple, it is good reliability, adaptable.
Description
Technical field
The present invention is the technical field of space flight and aviation, is particularly suitable for the thermal protection method and dress of star outside antenna rectangular waveguide
It sets.
Background technology
Currently, the communication of spacecraft, remote sensing or relaying all carry out data transmission work using electromagnetic wave, and electromagnetic wave
Reflection and receiving are required for antenna to complete.It is waveguide that the channel of electromagnetic wave is transmitted in antenna, and rectangular waveguide is most common one
Kind, good transmitting and the environment for receiving electromagnetic wave can reach best to enable amount conversion.Star outer waveguide is in transmission electromagnetic wave mistake
There is loss in journey, this partition losses can form heat consumption, cause temperature rise.With advances in technology, the power of waveguide input
Increasing, it is also bigger that loss is formed by heat consumption, additionally due to waveguide outside star, is affected by space heat flux, it is same
Moment different parts can also be caused waveguide temperature to fluctuate by according to difference, and excessively high temperature can make the mechanical performance of waveguide big
It is big to reduce, or keep its internal electronic equipment environment temperature exceeded, receive influence so as to cause spacecraft data transmission.Traditional sets
Meter heats the additional compensation of star outer waveguide spray-coated white paint, and this design point can make the temperature of waveguide relatively low, a large amount of to need
Electrical power resource be used for heating compensation.
Invention content
The purpose of the present invention is to solve outside star the problem of the thermal control demand of rectangular waveguide, it is proposed that one kind being suitable for star
The thermal protection method and apparatus of outside antenna rectangular waveguide especially adapt to the thermal control design of the outer rectangular waveguide of star under complicated Orbital heat flux.
To achieve the above object, the invention is realized by the following technical scheme：
A kind of temperature barrier suitable for star outside antenna rectangular waveguide, including multilayer insulation component, waveguide heat-dissipating fin,
Thermal control coating, heating element and thermistor, the multilayer insulation component are coated on waveguide surrounding, are stayed at waveguide edge
Under the opening stretched out for waveguide heat-dissipating fin, multilayer insulation component should be bonded cladding face as possible；The heat-dissipating fin and waveguide
It is integrated, heat-dissipating fin should ensure that certain thickness and planarity requirements, waveguide interior outside surface state are aluminium alloy
Electric conductive oxidation；The heating element is mounted on waveguide outer surface, for providing thermal compensation when low temperature storage；The temperature-sensitive electricity
Antiplastering is attached to waveguide outer surface, and to measure waveguide temperature, whether control heater assembly provides thermal compensation.
Further, the multilayer insulation component is made of the multilayer insulation unit of N units, the multilayer of each unit every
Hot cell is connected by one layer of two-sided aluminized mylar and one layer of polyamide fibre screen cloth interval to be constituted.
The thermal control coating is pasted onto two sides outside waveguide heat-dissipating fin.Further, the thermal control coating type can root
It is chosen according to the space environment of the track (low orbit, middle orbit, high orbit etc.) of spacecraft operation.Preferably, the thermal control coating
For glass mould second surface mirror (OSR).
Further, the installation site of the heating element is close to waveguide heat-dissipating fin
It is worth noting that, the heating element installation opportunity should be before the implementation of multilayer insulation component.
The present invention provides a kind of thermal protection method suitable for star outside antenna rectangular waveguide, this method is by above-mentioned
Temperature barrier controls the temperature of rectangular waveguide outside star in the reasonable scope.
The present invention is influenced according to star outside antenna waveguide assemblies by external complex hot-fluid, and integral coating multilayer insulation is used
The mode of component completely cuts off the influence of space heat flux；The spoke in cold space is provided by the way of stretching out fin in waveguide surface simultaneously
Heat dissipation channel is penetrated, and low temp compensating measure is provided by the electric heater compensating element, of waveguide surface, to reach waveguide assemblies
The temperature requirement of operation on orbit.Compared with prior art, the present invention has following advantageous effects：
Can largely reduce influence of the space heat flux to star outer waveguide, reduce star outer waveguide temperature gradient and
Fluctuation increases thermal environment stability when waveguide work；Thermal design reasonable of the present invention, consume star on electric resources it is few,
Technique realize it is simple, it is good reliability, adaptable.
Description of the drawings
Fig. 1 is the structural schematic diagram of a specific embodiment of the invention.
Fig. 2 is the vertical view of Fig. 1.
Fig. 3 is that certain GEO satellite number passes the in-orbit temperature of the outer rectangular waveguide component of Satellite Antenna System.
Specific implementation mode
With reference to specific embodiment, the present invention is described in detail.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
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.
To make the above purposes, features and advantages of the invention more obvious and understandable, below in conjunction with the accompanying drawings to the present invention
Specific embodiment be described in detail.
As Figure 1-Figure 2, an embodiment of the present invention provides a kind of thermal protection dresses suitable for star outside antenna rectangular waveguide
Set, including multilayer insulation component 1, waveguide heat-dissipating fin 2, thermal control coating, heating element 3 and thermistor 4, the multilayer every
Hot component is coated on waveguide surrounding, and the opening stretched out for waveguide heat-dissipating fin, multilayer insulation component are left at waveguide edge
It should be bonded coated waveguide surface setting as possible；The heat-dissipating fin and waveguide are integrated, and heat-dissipating fin should ensure that centainly
Thickness and planarity requirements, waveguide interior outside surface state be aluminium alloy electric conductive oxidation；The thermal control coating is pasted onto waveguide
Two sides outside heat-dissipating fin pastes detailed process and the related specifications according to space thermal control coating is required to implement；The heater
Element is mounted on waveguide outer surface, and installation site should be close to waveguide heat-dissipating fin；The thermistor is pasted onto waveguide outer surface,
Corresponding waveguide measuring point, the thermistor type are MF501 types.The multilayer insulation component is made of 20 layers of insulating unit, often
A insulating unit is separately made of one layer of 6 μm of two-sided aluminized mylar and one layer of 20d polyamide fibres hairnet.
In the present embodiment, heat-dissipating fin is molded when processing together with waveguide, and heat-dissipating fin thickness is 1mm；Planarity requirements
To be better than 0.1mm.
In the present embodiment, it is the OSR pieces of 0.15mm that thermal control coating, which selects thickness, and specific size is cut according to fin size.
In the present embodiment, the heater uses polyimides constantan foil electric heating sheets, is pasted onto fin extended position
Waveguide lateral surface at 10mm is used for low temperature thermal compensation.
By the above thermal design thinking and method, the waveguide that antenna is passed to the number of certain GEO satellite has carried out analysis calculating, model
Carried out necessary simplification and it is assumed that satellite other parameters (track, posture, coating and Material Physics attribute) by satellite totality skill
Art requires setting.Fig. 3 is that certain GEO satellite number passes antenna waveguide data in orbit, it can be seen that using of the present invention
Thermal controls apparatus and method, number pass the outer rectangular waveguide the operation is stable of Satellite Antenna System, and in-orbit temperature levels are reasonable, while demonstrating the present invention
The validity of the thermal controls apparatus and method.
This specific implementation is coated waveguide by multilayer insulation component entirely, while temperature is excessively high in order to prevent, at waveguide
It is outer to extend heat dissipation channel, and temperature-compensating is provided to prevent the temperature of waveguide too low around.This design method was both met
The control requirement of the in-orbit temperature of star outer waveguide, provides a good thermal environment, and reduce boat for the transmission channel of electromagnetic wave
The consumption of the electric resources of its device.The present invention by multilayer insulation component integral coating be combined with integration waveguide heat-dissipating fin heat dissipation with
And the mode of heating compensation, reach the thermal protection effect outside star under complicated thermal environment to waveguide, while than traditional method
It is more energy saving.
Although present disclosure is as above, present invention is not limited to this.Any those skilled in the art are not departing from this
It in the spirit and scope of invention, can make various changes or modifications, therefore protection scope of the present invention should be with claim institute
Subject to the range of restriction.
Claims (6)
1. a kind of temperature barrier suitable for star outside antenna rectangular waveguide, which is characterized in that including multilayer insulation component, waveguide
Heat-dissipating fin, thermal control coating, heating element and thermistor, the multilayer insulation component is coated on waveguide surrounding, in wave
It leads edge and leaves the opening stretched out for waveguide heat-dissipating fin；The heat-dissipating fin and waveguide are integrated, the wave
It leads heat-dissipating fin two sides and is pasted with thermal control coating, the heating element is mounted on waveguide outer surface, is deposited for providing low temperature
Thermal compensation when storage；The thermistor is pasted onto waveguide outer surface, and to measure waveguide temperature, whether control heater assembly
Thermal compensation is provided.
2. a kind of temperature barrier suitable for star outside antenna rectangular waveguide as described in claim 1, which is characterized in that described
Multilayer insulation component be made of the multilayer insulation unit of N units, the multilayer insulation unit of each unit is by one layer of two-sided plating
Aluminium polyester film and one layer of polyamide fibre screen cloth interval, which are connected, to be constituted.
3. a kind of temperature barrier suitable for star outside antenna rectangular waveguide as described in claim 1, which is characterized in that described
Waveguide interior outside surface state is aluminium alloy electric conductive oxidation.
4. a kind of temperature barrier suitable for star outside antenna rectangular waveguide as described in claim 1, which is characterized in that described
Thermal control coating is glass mould second surface mirror (OSR).
5. a kind of temperature barrier suitable for star outside antenna rectangular waveguide as described in claim 1, which is characterized in that described
The installation site of heating element is close to waveguide heat-dissipating fin.
6. a kind of thermal protection method suitable for star outside antenna rectangular waveguide, which is characterized in that this method uses such as claim
1-5 any one of them temperature barrier controls the temperature of rectangular waveguide in suitable range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810622991.5A CN108791964A (en) | 2018-06-15 | 2018-06-15 | A kind of thermal protection method and apparatus suitable for star outside antenna rectangular waveguide |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810622991.5A CN108791964A (en) | 2018-06-15 | 2018-06-15 | A kind of thermal protection method and apparatus suitable for star outside antenna rectangular waveguide |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720605A (en) * | 2019-02-27 | 2019-05-07 | 南京航空航天大学 | A kind of planetary probe device |
| CN109927939A (en) * | 2019-02-14 | 2019-06-25 | 上海卫星工程研究所 | Spacecraft exposed component thermal controls apparatus out of my cabin |
| CN112298619A (en) * | 2020-11-05 | 2021-02-02 | 上海卫星工程研究所 | Ultra-stable temperature control device and method for cables between SAR antenna boards |
| CN113911394A (en) * | 2021-09-30 | 2022-01-11 | 北京空间飞行器总体设计部 | Light-weight large-bearing extraterrestrial planet detection pointing mechanism |
| CN114476139A (en) * | 2022-01-13 | 2022-05-13 | 上海卫星工程研究所 | Thermal control design system and method for Mars circulator traveling wave tube assembly |
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| CN107529382B (en) * | 2013-02-05 | 2015-07-15 | 上海卫星工程研究所 | The performance test apparatus of satellite semiconductor cooler |
| CN107167774A (en) * | 2017-05-18 | 2017-09-15 | 上海卫星工程研究所 | Bilateral regards high-power hyperpyrexia plane of flow phased array antenna heat control system |
| CN107229299A (en) * | 2017-05-18 | 2017-10-03 | 上海卫星工程研究所 | High band high-power RF signal wire transmission heat abstractor in vacuum tank |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927939A (en) * | 2019-02-14 | 2019-06-25 | 上海卫星工程研究所 | Spacecraft exposed component thermal controls apparatus out of my cabin |
| CN109720605A (en) * | 2019-02-27 | 2019-05-07 | 南京航空航天大学 | A kind of planetary probe device |
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| CN112298619A (en) * | 2020-11-05 | 2021-02-02 | 上海卫星工程研究所 | Ultra-stable temperature control device and method for cables between SAR antenna boards |
| CN113911394A (en) * | 2021-09-30 | 2022-01-11 | 北京空间飞行器总体设计部 | Light-weight large-bearing extraterrestrial planet detection pointing mechanism |
| CN114476139A (en) * | 2022-01-13 | 2022-05-13 | 上海卫星工程研究所 | Thermal control design system and method for Mars circulator traveling wave tube assembly |
| CN114476139B (en) * | 2022-01-13 | 2024-01-30 | 上海卫星工程研究所 | Mars circulator traveling wave tube assembly thermal control design system and method |
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Application publication date: 20181113 |