CN104443441A - Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle - Google Patents
Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle Download PDFInfo
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- CN104443441A CN104443441A CN201410608314.XA CN201410608314A CN104443441A CN 104443441 A CN104443441 A CN 104443441A CN 201410608314 A CN201410608314 A CN 201410608314A CN 104443441 A CN104443441 A CN 104443441A
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Abstract
The invention provides a star sensor sub-low temperature independent thermal control device of an orbit transfer vehicle. The device comprises an imported star sensor A, a domestic star sensor B, thermistors (2), heaters (3), light shields (4), F46 films (5), an S781 white paint thermal control coating (6), mounting supports (7), a self support (8), heat insulation pads (8), a plurality of layers of heat insulation components (10) and thermal protection layers (11). Thermal resistance between stars and the star sensors is increased through the heat insulation pads, heat leakage compensation is greatly reduced, and a foundation is laid for independent temperature control over the star sensors. According to the sub-low temperature design requirement, the S781 white paint thermal control coating is adopted to increase the temperature adaptability of a star sensor motive track. The heat insulation components and the protection layers are adopted, and the radiation influence of a 25N engine on the imported star sensor A is effectively prevented. The device is convenient to implement, high in reliability and adaptability and small in total occupied resource, and the heat radiation of the engine can be effectively prevented.
Description
Technical field
The invention belongs to spacecraft thermal control design field, particularly relate to the independent thermal design technology of a kind of orbit transfer vehicle star sensor temperature on the low side.
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 star sensors: import star sensor A and domestic star sensor B.Be installed on inclined III quadrant of loaded cylinder IV.Two star sensor working temperature ranges are-40 ~+35 DEG C, and domestic star sensor B storage temperature range is-30 ~+60 DEG C.In order to reduce the thermal coupling of star sensor and cabin body, star sensor takes the independent thermal control design of heat insulation installation.Due to aircraft, there is attitude yaw mode in period in orbit, Orbital heat flux variation range is larger, under thermal control design need ensure various operating mode, star sensor is all within the scope of index request, need increase the comformability of star sensor to external environment condition, therefore star sensor takes temperature on the low side to design: wherein import star sensor A shade and star sensor head paste the silver-plated second surface mirror thermal control coating of conductivity type F46; Domestic star sensor B housing outer surface all sprays S781 white paint thermal control coating except attachment face region, and mounting bracket spraying S781 white paint thermal control coating, shade pastes the silver-plated second surface mirror thermal control coating of conductivity type F46.Simultaneously, near import star sensor A, 25N driving engine is housed, through simulation analysis and verification experimental verification, the radiation effect that engine operation is brought must be considered, therefore the coated low temperature multilayer of import star sensor A mounting flange outside face, towards driving engine one side external surface coated one deck protective layer, (protective layer adopts warm multilayer in three layers, and in every unit, warm multilayer is made up of the high silica glass cloth (wall) of one deck 100 μm and one deck 25 μm of two-sided aluminizers of polyimide (reflecting horizon).Middle temperature multilayer outmost surface adopts one deck 25 μm of conductivity type polyimide to aluminize second surface mirror coating.)。Finally, by pasting electric heater at star sensor head, low temp compensating is realized.
The satellite of usual installation star sensor is sun-synchronous orbit, without attitude yaw mode, outside hot-fluid is stablized, therefore star sensor is when designing, except with except the heat insulation installation of celestial body, star sensor independence dissipating area is less, all coated multilayer insulation assembly in all the other places, star sensor head pastes low temp compensating temperature booster (every road 10W, takies resource more).Meanwhile, near usual Satellite sensor, driving engine is not installed, without the need to considering that engine radiation affects.And owing to there is attitude yaw mode in transfer orbit aircraft star sensor, outside hot-fluid is unstable, if take the measure that general satellite half is coated, under yaw attitude, under certainly will causing the joint effect of star sensor changes of heat flux and interior power consumption outside, star sensor independence heat delivery surface is not enough in addition, thus causes star sensor temperature to rise, close to even exceeding temperature upper limit, cause potential safety hazard.Moreover through simulation analysis and experimental investigation, the radiation effect of driving engine to star sensor is very important, the thermal protection problem of star sensor must be considered when thermal design.
Summary of the invention
For defect of the prior art, the object of this invention is to provide the independent thermal design technology of a kind of orbit transfer vehicle star sensor temperature on the low side, this technology is convenient to enforcement, reliability is high, strong adaptability, aggregate resource occupancy are few, and effectively can protect engine radiation.
According to the independent thermal controls apparatus of a kind of orbit transfer vehicle star sensor provided by the invention temperature on the low side, comprise import star sensor A, domestic star sensor B, thermally dependent resistor, temperature booster, shade, F46 film, S781 white paint thermal control coating, mounting bracket, self support, heat insulating mattress, multilayer insulation assembly, thermal protection shield;
The head of import star sensor A, domestic star sensor B is all pasted with thermally dependent resistor and temperature booster;
The shade of the head of import star sensor A, the shade of import star sensor A and domestic star sensor B is all pasted with F46 film;
The head of import star sensor A, domestic star sensor B is all coated with S781 white paint thermal control coating;
Import star sensor A, domestic star sensor B are arranged on respective mounting bracket respectively, and import star sensor A pads heat insulating mattress between self support and mounting bracket, pad heat insulating mattress between the head of domestic star sensor B and mounting bracket;
Mounting bracket and the coated multilayer insulation assembly on self support of import star sensor A, add three layers of thermal protection shield again outside the close engine side of import star sensor A.
Preferably, temperature booster is spacecraft Kapton type electric heater.
Preferably, the trade mark of thermally dependent resistor is MF501.
Preferably, F46 film is the silver-plated second surface mirror thermal control coating of conductivity type F46.
Preferably, heat insulating mattress is the glass-felt plastic heat insulating mattress being not less than 5mm.
Preferably, multilayer insulation assembly comprises 20
dpolyamide fibre silk screen and 6 μm of two-sided aluminized mylars, the outermost layer of multilayer insulation assembly 10 is the silver-plated second surface mirror of conductivity type F46 film.
Preferably, thermal protection shield adopts warm multilayer in three layers, in every layer, warm multilayer is made up of as the high silica glass cloth of 100 μm of wall and one deck 25 μm of two-sided aluminizers of polyimide as reflecting horizon one deck, and middle temperature multilayer outmost surface adopts one deck 25 μm of conductivity type polyimide to aluminize second surface mirror coating.
Compared with prior art, the present invention has following beneficial effect:
1, employing heat insulating mattress increases the thermal resistance between celestial body and star sensor, greatly reduces leakage thermal compensation, for realizing the independent temperature control evaluation of foundation of star sensor;
2, according to temperature designing requirement on the low side, S781 white paint thermal control coating is adopted to add the Acclimation temperature ability of star sensor motive track;
3, adopt multilayer insulation assembly and protective layer, effectively protect the radiation effect of 25N driving engine to import star sensor A;
4, electric heater and thermally dependent resistor is adopted, the wherein active and standby each 4W of star sensor A temperature booster, the main 10W of star sensor B temperature booster, temperature booster is for 7W (conventional satellite star sensor temperature booster arranges active and standby each 10W), achieve the accurate temperature controlling of star sensor, and the temperature levels of energy real-time monitored star sensor, be star sensor smooth operation in-orbit, provide good thermal environment;
5, this technology is convenient to implement, reliability is high, thermal adaptability is strong, aggregate resource takies few, and adapting to vehicle out-driving affects, and effectively can protect 25N driving engine and affect the thermal radiation of star sensor, is applicable to the thermal design of orbit transfer vehicle star sensor.
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 is conventional satellite star sensor thermal control design view;
Fig. 2 is the thermal control design view of star sensor A, B in the present invention.
In figure: 1, star sensor head, 2, thermally dependent resistor, 3, temperature booster, 4, shade, 5, F46 film, 6, S781 white paint thermal control coating, 7, mounting bracket, 8, import star sensor A self support, 9, heat insulating mattress, 10, multilayer insulation assembly, 11, thermal protection shield.
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.
Technical scheme of the present invention is: provide one and can be applied to the independent thermal controls apparatus of orbit transfer vehicle star sensor temperature on the low side, comprise heat insulating mattress, S781 white paint thermal control coating, multilayer insulation assembly, thermal protection shield, electric heater and thermally dependent resistor; It is characterized in that: between star sensor head and its bracket mounting face, pad heat insulating mattress, reduce the thermal coupling between star sensor and cabin body; Owing to affecting by attitude driftage, star sensor takes temperature on the low side to design, and wherein import star sensor A shade and star sensor head paste the silver-plated second surface mirror thermal control coating of conductivity type F46; Domestic star sensor B housing outer surface all sprays S781 white paint thermal control coating except attachment face region, and mounting bracket spraying S781 white paint thermal control coating, shade pastes the silver-plated second surface mirror thermal control coating of conductivity type F46, enhances the thermal adaptability of star sensor.The coated low temperature multilayer of import star sensor A mounting flange outside face, towards the coated one deck protective layer of driving engine one side external surface, has effectively protected the thermal radiation impact that 25N driving engine brings.Finally, by pasting electric heater and thermally dependent resistor at star sensor head, the Real-Time Monitoring to star sensor temperature and accurate temperature controlling is realized.
Described star sensor head and the heat insulation installation of its bracket mounting face, preferred described heat insulating mattress is the glass-felt plastic heat insulating mattress being not less than 5mm; Described star sensor heat delivery surface spraying S781 white paint thermal control coating; Described 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; Described thermal protection shield adopts warm multilayer in three layers, in every unit, warm multilayer is made up of the high silica glass cloth (wall) of one deck 100 μm and one deck 25 μm of two-sided aluminizers of polyimide (reflecting horizon), and middle temperature multilayer outmost surface adopts one deck 25 μm of conductivity type polyimide to aluminize second surface mirror coating; Preferred shade sticking film is the silver-plated second surface mirror of conductivity type F46 film; Described temperature booster is spacecraft Kapton type electric heater, arranges two-way, each other active and standby part, strengthen its reliability, be pasted on star sensor head, wherein the active and standby each 4W of star sensor A temperature booster, the main 10W of star sensor B temperature booster, temperature booster for 7W, and and fit good between monomer; The preferred described thermally dependent resistor trade mark is MF501.
Particularly, first thermally dependent resistor 2 and temperature booster 3 is pasted at star sensor head 1, ensure that temperature booster 3 is fitted good with star sensor head 1 surface, paste F46 film 5 at import star sensor A head 1, shade 4 and domestic star sensor shade 4 after fixing, then spray S781 white paint thermal control coating 6 at domestic star sensor head 1.Described temperature booster 3 is spacecraft Kapton type electric heater, and preferred described thermally dependent resistor 2 trade mark is MF501; Described star sensor head 1 sprays space flight level S781 white paint thermal control coating 6; Described shade 4 and the quick A head 1 of import star paste F46 film 5 for the silver-plated second surface mirror thermal control coating of conductivity type F46.
Then be arranged on by star sensor on support 7, pad heat insulating mattress 9, pad heat insulating mattress 9 between domestic star sensor head 1 and mounting bracket 7 between import star sensor A self support 8 and mounting bracket 7, preferred described heat insulating mattress 9 is for being not less than the glass-felt plastic heat insulating mattress of 5mm.
Finally coated multilayer insulation assembly 10 on import star sensor mounting bracket 7 and self support 8, outside engine side, add three layers of thermal protection shield 11 again, described multilayer insulation assembly 10 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; Described thermal protection shield 11 adopts warm multilayer in three layers, in every unit, warm multilayer is made up of the high silica glass cloth (wall) of one deck 100 μm and one deck 25 μm of two-sided aluminizers of polyimide (reflecting horizon), and middle temperature multilayer outmost surface adopts one deck 25 μm of conductivity type polyimide to aluminize second surface mirror coating.
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. the independent thermal controls apparatus of orbit transfer vehicle star sensor temperature on the low side, it is characterized in that, comprise import star sensor A, domestic star sensor B, thermally dependent resistor (2), temperature booster (3), shade (4), F46 film (5), S781 white paint thermal control coating (6), mounting bracket (7), self support (8), heat insulating mattress (9), multilayer insulation assembly (10), thermal protection shield (11);
The head (1) of import star sensor A, domestic star sensor B is all pasted with thermally dependent resistor (2) and temperature booster (3);
The shade (4) of the head (1) of import star sensor A, the shade (4) of import star sensor A and domestic star sensor B is all pasted with F46 film (5);
The head (1) of import star sensor A, domestic star sensor B is all coated with S781 white paint thermal control coating (6);
Import star sensor A, domestic star sensor B are arranged on respective mounting bracket (7) respectively, pad heat insulating mattress (9) between self support (8) of import star sensor A and mounting bracket (7), between the head (1) of domestic star sensor B and mounting bracket (7), pad heat insulating mattress (9);
The mounting bracket (7) of import star sensor A and the upper coated multilayer insulation assembly (10) of self support (8), add three layers of thermal protection shield (11) again outside the close engine side of import star sensor A.
2. the independent thermal controls apparatus of orbit transfer vehicle star sensor according to claim 1 temperature on the low side, is characterized in that, temperature booster (3) is spacecraft Kapton type electric heater.
3. the independent thermal controls apparatus of orbit transfer vehicle star sensor according to claim 1 temperature on the low side, is characterized in that, the trade mark of thermally dependent resistor (2) is MF501.
4. the independent thermal controls apparatus of orbit transfer vehicle star sensor according to claim 1 temperature on the low side, is characterized in that, F46 film (5) is the silver-plated second surface mirror thermal control coating of conductivity type F46.
5. the independent thermal controls apparatus of orbit transfer vehicle star sensor according to claim 1 temperature on the low side, is characterized in that, heat insulating mattress (9) is for being not less than the glass-felt plastic heat insulating mattress of 5mm.
6. the independent thermal controls apparatus of orbit transfer vehicle star sensor according to claim 1 temperature on the low side, it is characterized in that, multilayer insulation assembly (10) comprises 20d polyamide fibre silk screen and 6 μm of two-sided aluminized mylars, and the outermost layer of multilayer insulation assembly 10 is the silver-plated second surface mirror of conductivity type F46 film.
7. the independent thermal controls apparatus of orbit transfer vehicle star sensor according to claim 1 temperature on the low side, it is characterized in that, warm multilayer during thermal protection shield (11) adopts three layers, in every layer, warm multilayer is made up of as the high silica glass cloth of 100 μm of wall and one deck 25 μm of two-sided aluminizers of polyimide as reflecting horizon one deck, and middle temperature multilayer outmost surface adopts one deck 25 μm of conductivity type polyimide to aluminize second surface mirror coating.
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| CN105059570A (en) * | 2015-08-18 | 2015-11-18 | 航天东方红卫星有限公司 | Detachment-free engine protection cover for mini-satellite |
| CN105109708A (en) * | 2015-08-31 | 2015-12-02 | 北京航天长征飞行器研究所 | Thermal control method of spatial aircraft |
| CN105549306A (en) * | 2015-12-21 | 2016-05-04 | 中国科学院长春光学精密机械与物理研究所 | Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera |
| CN106114912A (en) * | 2016-08-12 | 2016-11-16 | 上海卫星工程研究所 | GEO track Rotating Platform for High Precision Star Sensor high stable in-orbit points to ensuring method |
| CN106336128A (en) * | 2016-08-19 | 2017-01-18 | 上海裕达实业有限公司 | Flexible OSR second surface mirror thermal control coating and preparation method and application thereof |
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| CN108791958A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor illumination adapts to heat control device entirely |
| 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 |
| 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 |
| CN109057971A (en) * | 2018-06-15 | 2018-12-21 | 上海卫星工程研究所 | Star engine low temperature lightweight multilayer insulation component |
| CN109141472A (en) * | 2018-08-13 | 2019-01-04 | 上海航天控制技术研究所 | For assessing the sight star test device and method of star sensor thermal stability |
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| 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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| CN105109708A (en) * | 2015-08-31 | 2015-12-02 | 北京航天长征飞行器研究所 | Thermal control method of spatial aircraft |
| CN105549306A (en) * | 2015-12-21 | 2016-05-04 | 中国科学院长春光学精密机械与物理研究所 | Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera |
| CN106114912A (en) * | 2016-08-12 | 2016-11-16 | 上海卫星工程研究所 | GEO track Rotating Platform for High Precision Star Sensor high stable in-orbit points to ensuring method |
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| CN109141472B (en) * | 2018-08-13 | 2020-08-28 | 上海航天控制技术研究所 | Star observation testing device and method for evaluating thermal stability of star sensor |
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| CN111099039A (en) * | 2019-12-11 | 2020-05-05 | 上海卫星工程研究所 | Surface thermal control structure suitable for spacecraft and preparation method thereof |
| CN111099039B (en) * | 2019-12-11 | 2021-10-01 | 上海卫星工程研究所 | Surface thermal control structure suitable for spacecraft and preparation method thereof |
| CN111319790A (en) * | 2020-03-11 | 2020-06-23 | 浙江时空道宇科技有限公司 | Star sensor support |
| 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 |
| 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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| CN116149396A (en) * | 2023-04-18 | 2023-05-23 | 东方空间技术(山东)有限公司 | Temperature control system of arrow-borne flight control combination and preparation method of flexible heating device |
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