CN104369876B - Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus - Google Patents
Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus Download PDFInfo
- Publication number
- CN104369876B CN104369876B CN201410608270.0A CN201410608270A CN104369876B CN 104369876 B CN104369876 B CN 104369876B CN 201410608270 A CN201410608270 A CN 201410608270A CN 104369876 B CN104369876 B CN 104369876B
- Authority
- CN
- China
- Prior art keywords
- horizon instrument
- horizon
- instrument
- low side
- rollably
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012546 transfer Methods 0.000 title claims abstract description 17
- 238000013461 design Methods 0.000 claims abstract description 22
- 238000009413 insulation Methods 0.000 claims abstract description 20
- 239000003973 paint Substances 0.000 claims abstract description 20
- 239000011248 coating agent Substances 0.000 claims abstract description 18
- 238000000576 coating method Methods 0.000 claims abstract description 18
- 230000001419 dependent effect Effects 0.000 claims abstract description 14
- 230000004069 differentiation Effects 0.000 claims abstract description 6
- 238000005507 spraying Methods 0.000 claims description 13
- 229920000134 Metallised film Polymers 0.000 claims description 4
- 239000004952 Polyamide Substances 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- 239000004033 plastic Substances 0.000 claims description 4
- 229920003023 plastic Polymers 0.000 claims description 4
- 230000007423 decrease Effects 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 3
- 229920003223 poly(pyromellitimide-1,4-diphenyl ether) Polymers 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 claims description 2
- 239000002918 waste heat Substances 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims 1
- 238000011156 evaluation Methods 0.000 abstract description 2
- 239000007921 spray Substances 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 6
- 230000008859 change Effects 0.000 description 3
- 229920002647 polyamide Polymers 0.000 description 3
- 238000005286 illumination Methods 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000009916 joint effect Effects 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Landscapes
- Control Of Resistance Heating (AREA)
Abstract
The invention provides a kind of orbit transfer vehicle infrared horizon instrument temperature difference alienation on the low side thermal controls apparatus, comprise heat insulating mattress, S781 white paint thermal control coating, multilayer insulation assembly, electric heater, thermally dependent resistor, horizon instrument, horizon instrument support.The present invention opens independent heat delivery surface first on infrared horizon instrument, and according to different by the situation of photograph, the heat delivery surface position that pitching horizon instrument and rollably level are opened is different, be convenient to implement, reliability is high, strong adaptability, aggregate resource occupancy is few, it adopts heat insulating mattress to increase thermal resistance between celestial body and infrared horizon instrument, for realizing the independent temperature control evaluation of foundation of horizon instrument, and in order to realize temperature design philosophy on the low side, independent heat delivery surface is opened at infrared horizon instrument head, and spray S781 white paint thermal control coating, achieve the differentiation thermal design of infrared horizon instrument, enhance the comformability of horizon instrument motive track.
Description
Technical field
The invention belongs to spacecraft thermal control design field, particularly relate to a kind of orbit transfer vehicle infrared horizon instrument temperature difference alienation on the low side thermal design technology.
Background technology
6:30 ± 30min local time the in that certain model aircraft test objective track needing to adapt to descending node, the change of orbit altitude 500 ~ 800km.Aircraft needs repeatedly vehicle out-driving in-orbit, and rail conditions change causes greatly aircraft Orbital heat flux condition to change greatly, and outside unit, by complicated according to situation, therefore requires that the especially outside unit thermal environment of aircraft thermal control design has high adaptive capacity.This aircraft adopts two infrared horizon instruments: rollably level and pitching horizon instrument.Horizon instrument head passes through horizon instrument support installing in aircraft cabin body cylinder section to ground outside face, and rollably level head is towards heading, and pitching horizon instrument head is towards opaco IV quadrantal heading.Two infrared horizon instrument working temperature ranges are-8 ~+42 DEG C, relative to other units out of my cabin, range of temperatures is narrower, due to the joint effect of external environment condition and self hear rate, under worst hot case, the temperature levels of infrared horizon instrument is comparatively severe, simultaneously in order to reduce resource consumption, and strengthening its motive track comformability, taking low temperature to design.In addition vehicle out-driving impact, two infrared horizon instrument area of illumination are different, pitching horizon instrument head tail end is shone, rollably level sunny slope is shone, therefore must consider respectively when thermal design, in order to make two tableland level all in suitable range of temperatures, differentiation thermal design must be taked to two tableland level.
Usual satellite infrared horizon instrument is installed on satellite opaco, outside hot-fluid is stablized, therefore infrared horizon instrument is when designing, except with except the heat insulation installation of celestial body, the outside whole coated multilayer insulation assembly of infrared horizon instrument, the coated multilayer insulation assembly of infrared horizon instrument support, without independent heat delivery surface, side by side level pastes compensating heater compensation leakage heat.In order to simplified design, on usual satellite, infrared horizon instrument takes Uniting as far as possible.And transfer orbit aircraft two infrared horizon instruments are arranged on the junction of sunny slope and opaco, affect by vehicle out-driving, horizon instrument can be subject to sunshine shining directly in various degree, external high temperature bad environments, and two tableland level area of illumination different, if take the outside complete coated multilayer of general satellite infrared horizon instrument thermal design means, and design philosophy is unified, infrared horizon instrument operating temperature when worst hot case certainly will be caused to approach and even to exceed the high temperature upper limit, or a certain meets the demands but another is close to even exceeding indication range, thus bring potential safety hazard.Therefore for orbit transfer vehicle, while considering to prevent low temperature from leaking heat, also must consider the heat dissipation problem under worst hot case, also need to carry out differentiation design to two tableland level simultaneously.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of orbit transfer vehicle infrared horizon instrument temperature difference alienation on the low side thermal design technology, independent heat delivery surface is opened first on infrared horizon instrument, and according to different by the situation of photograph, the heat delivery surface position that pitching horizon instrument and rollably level are opened is different, and this technology is convenient to implement, reliability is high, strong adaptability, aggregate resource occupancy are few.
According to a kind of orbit transfer vehicle infrared horizon instrument provided by the invention temperature difference alienation on the low side thermal controls apparatus, comprise heat insulating mattress, S781 white paint thermal control coating, multilayer insulation assembly, electric heater, thermally dependent resistor, horizon instrument, horizon instrument support;
Heat insulating mattress is padded, to reduce the thermal coupling between horizon instrument and celestial body between horizon instrument head and horizon instrument bracket mounting face; Horizon instrument comprises pitching horizon instrument and rollably level; Pitching horizon instrument head stretches out the outside face spraying S781 white paint thermal control coating of horizon instrument holder part except optical mirror slip towards IV quadrantal heading, rollably level head opaco spraying S781 white paint thermal control coating, pitching horizon instrument and rollably level open heat delivery surface in different positions, by loose for horizon instrument waste heat row, enhance the space environment comformability of horizon instrument, also achieve simultaneously pitching horizon instrument and rollably level differentiation design;
Pitching horizon instrument and the rollably level whole coated multilayer insulation assembly of outside face except spraying S781 white paint, to block under worst hot case while hot-fluid direct projection, also reduces the leakage heat under worst cold case, decrease aggregate resource occupancy; The head of pitching horizon instrument and rollably level all pastes electric heater and thermally dependent resistor.
Preferably, horizon instrument support and the heat insulation installation of celestial body, heat insulating mattress is the glass-felt plastic heat insulating mattress being not less than 5mm.
Preferably, the heat delivery surface spraying S781 white paint thermal control coating of pitching horizon instrument and rollably level.
Preferably, multilayer insulation assembly is made up of 20d polyamide fibre silk screen and 6 μm of two-sided aluminized mylars, and outermost layer is the silver-plated second surface mirror of conductivity type F46 film.
Preferably, temperature booster is spacecraft Kapton type electric heater, arranges two-way, each other active and standby part, strengthens reliability, is pasted on the head of pitching horizon instrument and rollably level.
Preferably, the thermally dependent resistor trade mark is MF501.
Preferably, utilize electric heater and thermally dependent resistor, achieved the accurate temperature controlling of horizon instrument by the mode of Real-Time Monitoring horizon instrument temperature data and low temp compensating hear rate.
Compared with prior art, the present invention has following beneficial effect:
1, employing heat insulating mattress increases the thermal resistance between celestial body and infrared horizon instrument, for realizing the independent temperature control evaluation of foundation of horizon instrument;
2, in order to realize temperature design philosophy on the low side, independent heat delivery surface is opened at infrared horizon instrument head, and spray S781 white paint thermal control coating, according to being subject to according to situation, pitching horizon instrument head stretches out the outside face spraying S781 white paint thermal control coating of holder part except optical mirror slip towards IV quadrantal heading, rollably level head opaco spraying S781 white paint thermal control coating, achieves the differentiation thermal design of infrared horizon instrument, enhances the comformability of horizon instrument motive track;
3, adopt multilayer insulation assembly, when reducing high temperature, the sun directly affect according on the irradiation of horizon instrument, decreases low temperature simultaneously and leaks hot;
4, adopt electric heater and thermally dependent resistor, achieve the accurate temperature controlling of infrared horizon instrument, and the temperature levels of energy real-time monitored horizon instrument, be infrared horizon instrument smooth operation in-orbit, provide good thermal environment;
5, this technology be convenient to implement, high, the strong adaptability of reliability, do not affect by aircraft vehicle out-driving, resource occupation is few, is applicable to the thermal design of orbit transfer vehicle infrared horizon instrument.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1, Fig. 2 are conventional satellite infrared horizon instrument thermal control design view;
Fig. 3 is pitching horizon instrument thermal control design view;
Fig. 4 is rollably level thermal control design view;
In figure:
1, horizon instrument head, 2, multilayer insulation assembly, 3, electric heater, 4, horizon instrument support, 5, bottom surface is installed, 6, glass-felt plastic heat insulating mattress, 7, horizon instrument head surface, 8, S781 white paint thermal control coating, 9, all the other outside faces of horizon instrument head, 10, horizon instrument support, 11, thermally dependent resistor, 12, horizon instrument head opaco, 13, horizon instrument head sunny slope, 14, horizon instrument head trailing exterior surface.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
The invention provides a kind of orbit transfer vehicle infrared horizon instrument temperature difference alienation on the low side thermal design technology, comprise heat insulating mattress 1, S781 white paint thermal control coating 2, multilayer insulation assembly 3, thermally dependent resistor 4, electric heater 5.
First pitching horizon instrument and rollably level head paste thermally dependent resistor 4 and temperature booster 5 respectively, ensure that temperature booster and horizon instrument surface are fitted good, at pitching horizon instrument head spraying S781 white paint thermal control coating 2 after fixing, rollably level opaco spraying S781 white paint thermal control coating 2, the coated multilayer insulation assembly 3 of all the other outside faces of pitching horizon instrument head, rollably level head tail end and the coated multilayer insulation assembly 3 of sunny slope, fixing with polyester thread binding.Described horizon instrument heat delivery surface spraying S781 white paint thermal control coating 2; Described multilayer insulation assembly 3 is made up of 20d polyamide fibre silk screen and 6 μm of two-sided aluminized mylars, and outermost layer is the silver-plated second surface mirror of conductivity type F46 film; Described temperature booster 5 is spacecraft Kapton type electric heater, and preferred described thermally dependent resistor 4 trade mark is MF501.
Then be arranged on respective support respectively by two infrared horizon instruments, install heat insulating mattress 1 between infrared horizon instrument and support, preferred described heat insulating mattress 1 is for being not less than the glass-felt plastic heat insulating mattress of 5mm.
Finally by coated for horizon instrument support multilayer insulation assembly 3, described multilayer insulation assembly 3 is made up of 20d polyamide fibre silk screen and 6 μm of two-sided aluminized mylars, and outermost layer is the silver-plated second surface mirror of conductivity type F46 film, and fixes with multilayer clip.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (7)
1. an orbit transfer vehicle infrared horizon instrument temperature difference alienation on the low side thermal controls apparatus, is characterized in that, comprises heat insulating mattress, S781 white paint thermal control coating, multilayer insulation assembly, electric heater, thermally dependent resistor, horizon instrument, horizon instrument support;
Heat insulating mattress is padded, to reduce the thermal coupling between horizon instrument and celestial body between horizon instrument head and horizon instrument bracket mounting face; Horizon instrument comprises pitching horizon instrument and rollably level; Pitching horizon instrument head stretches out the part of horizon instrument support towards IV quadrantal heading, outside face spraying S781 white paint thermal control coating except optical mirror slip, rollably level head opaco spraying S781 white paint thermal control coating, pitching horizon instrument and rollably level open heat delivery surface in different positions, by loose for horizon instrument waste heat row, enhance the space environment comformability of horizon instrument, also achieve simultaneously pitching horizon instrument and rollably level differentiation design;
Pitching horizon instrument and the rollably level whole coated multilayer insulation assembly of outside face except spraying S781 white paint, to block under worst hot case while hot-fluid direct projection, also reduces the leakage heat under worst cold case, decrease aggregate resource occupancy; The head of pitching horizon instrument and rollably level all pastes electric heater and thermally dependent resistor.
2. orbit transfer vehicle infrared horizon instrument according to claim 1 temperature difference alienation on the low side thermal controls apparatus, is characterized in that, horizon instrument support and the heat insulation installation of celestial body, and heat insulating mattress is the glass-felt plastic heat insulating mattress being not less than 5mm.
3. orbit transfer vehicle infrared horizon instrument according to claim 1 temperature difference alienation on the low side thermal controls apparatus, is characterized in that, the heat delivery surface spraying S781 white paint thermal control coating of pitching horizon instrument and rollably level.
4. orbit transfer vehicle infrared horizon instrument according to claim 1 temperature difference alienation on the low side thermal controls apparatus, it is characterized in that, multilayer insulation assembly is by 20
dpolyamide fibre silk screen and 6 μm of two-sided aluminized mylar compositions, outermost layer is the silver-plated second surface mirror of conductivity type F46 film.
5. orbit transfer vehicle infrared horizon instrument according to claim 1 temperature difference alienation on the low side thermal controls apparatus, it is characterized in that, temperature booster is spacecraft Kapton type electric heater, two-way is set, active and standby part each other, strengthen reliability, be pasted on the head of pitching horizon instrument and rollably level.
6. orbit transfer vehicle infrared horizon instrument according to claim 1 temperature difference alienation on the low side thermal controls apparatus, is characterized in that, the thermally dependent resistor trade mark is MF501.
7. orbit transfer vehicle infrared horizon instrument according to claim 1 temperature difference alienation on the low side thermal controls apparatus, it is characterized in that, utilize electric heater and thermally dependent resistor, achieved the accurate temperature controlling of horizon instrument by the mode of Real-Time Monitoring horizon instrument temperature data and low temp compensating hear rate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410608270.0A CN104369876B (en) | 2014-10-31 | 2014-10-31 | Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410608270.0A CN104369876B (en) | 2014-10-31 | 2014-10-31 | Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104369876A CN104369876A (en) | 2015-02-25 |
| CN104369876B true CN104369876B (en) | 2016-04-27 |
Family
ID=52549139
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410608270.0A Active CN104369876B (en) | 2014-10-31 | 2014-10-31 | Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104369876B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108052143A (en) * | 2017-10-27 | 2018-05-18 | 上海卫星工程研究所 | Engine servo mechanism with integrated thermal control for heat protection and heat dissipation |
| CN108791964A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | A kind of thermal protection method and apparatus suitable for star outside antenna rectangular waveguide |
| CN108974392A (en) * | 2018-06-15 | 2018-12-11 | 上海卫星工程研究所 | A kind of more star transmitting Upper Stage satellite separating supports |
| CN109850187B (en) * | 2019-03-07 | 2021-02-09 | 中国空间技术研究院 | An energy allocation method for transfer orbit under the evening launch window of GEO satellites |
| CN111891407B (en) * | 2020-07-21 | 2021-12-14 | 上海卫星工程研究所 | Temperature equalization control device and control method under unbalanced external heat flow condition |
| 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 |
| CN114413060B (en) * | 2021-12-20 | 2024-07-26 | 上海空间推进研究所 | Device for reducing on-orbit temperature of control valve of space engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4713275A (en) * | 1986-05-14 | 1987-12-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Ceramic/ceramic shell tile thermal protection system and method thereof |
| JP2001315700A (en) * | 2000-05-01 | 2001-11-13 | Mitsubishi Heavy Ind Ltd | Thermal control system for spacecraft |
| US7691435B2 (en) * | 2006-08-10 | 2010-04-06 | The Boeing Company | Thermal control coatings |
| DE102007062150A1 (en) * | 2007-09-14 | 2009-04-02 | Thales Electron Devices Gmbh | Device for dissipating heat loss and ion accelerator arrangement and traveling wave tube arrangement with a Wärmeleitanordnung |
| CN104335712B (en) * | 2007-12-25 | 2015-07-25 | 上海卫星工程研究所 | Thermal Control Device for Spaceborne Radar Transmitting and Receiving Chip Components |
| CN103448925A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | High-precision temperature control device for star sensors for satellites |
-
2014
- 2014-10-31 CN CN201410608270.0A patent/CN104369876B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104369876A (en) | 2015-02-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104369876B (en) | Orbit transfer vehicle infrared horizon instrument is on the low side temperature difference alienation thermal controls apparatus | |
| CN104443441B (en) | Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature | |
| CN103332302B (en) | A kind of separation device thermal controls apparatus and thermal control method thereof | |
| CN104290924A (en) | Star sensor temperature control device | |
| CN205168943U (en) | A low-temperature independent thermal control device for star sensors of orbit transfer vehicles | |
| CN103486784B (en) | Heat control system of high-power satellite-borne Stirling refrigerator | |
| CN105035365A (en) | Satellite temperature control method allowing rapid responding and multi-orbit adaption | |
| CN103482087B (en) | A kind of heat control device suitable in Mars landing device | |
| JP6302603B2 (en) | Spaceship | |
| CN104210673B (en) | A kind of thermal control method of the quick molectron of star | |
| CN108791958A (en) | Star sensor illumination adapts to heat control device entirely | |
| CN105383714A (en) | A spaceborne active temperature control system | |
| CN110143294B (en) | Thermal design structure of full-orbit full-attitude aircraft | |
| CN220181101U (en) | Integrated thermal control device, system and artificial satellite | |
| CN103303498B (en) | Radiation capsule for star sensor | |
| CN108791964A (en) | A kind of thermal protection method and apparatus suitable for star outside antenna rectangular waveguide | |
| CN204998798U (en) | Close on spacecraft and hot accuse system thereof | |
| CN116674770A (en) | Telescope thermal control method suitable for Lagrange point L2 aircraft | |
| CN109552671A (en) | A kind of spaceborne survey meter probing head thermal controls apparatus | |
| CN108860664B (en) | Novel thermal control device for space flexible mechanism | |
| CN103471634A (en) | Cooling device of space optical remote sensor | |
| CN204250387U (en) | Star sensor temperature regulating device | |
| CN108974392A (en) | A kind of more star transmitting Upper Stage satellite separating supports | |
| CN109367758A (en) | A kind of thermal protection component and thermal protection system | |
| CN108052143A (en) | Engine servo mechanism with integrated thermal control for heat protection and heat dissipation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |