CN104443441B - Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature - Google Patents
Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature Download PDFInfo
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- CN104443441B CN104443441B CN201410608314.XA CN201410608314A CN104443441B CN 104443441 B CN104443441 B CN 104443441B CN 201410608314 A CN201410608314 A CN 201410608314A CN 104443441 B CN104443441 B CN 104443441B
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Abstract
The invention provides a kind of orbit transfer vehicle star sensor independent thermal controls apparatus of temperature on the low side, including import star sensor (A), domestic star sensor (B), critesistor (2), heater (3), shade (4), F46 thin 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 present invention adopts heat insulating mattress to increase 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；And according to temperature designing requirement on the low side, adopt S781 white paint thermal control coating to add the temperature adaptation ability of star sensor motive track；And adopt multilayer insulation assembly and overcoat, effectively protect the 25N electromotor radiation effect to import star sensor (A)；It is convenient to carry out, reliability is high, strong adaptability, aggregate resource occupancy are few, and can effectively protect engine radiation.
Description
Technical field
The invention belongs to spacecraft thermal control design field, particularly relate to a kind of independent thermal design technology of orbit transfer vehicle star sensor temperature on the low side.
Background technology
Certain model aircraft test objective track need to adapt to 6:30 ± 30min local time the in of southbound 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 is by complicated according to situation, therefore it is required 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.It is installed on inclined III quadrant of loaded cylinder IV.Two star sensor operating temperature ranges are-40～+35 DEG C, and it is-30～+60 DEG C that domestic star sensor B stores temperature range.In order to reduce the thermal coupling of star sensor and nacelle, star sensor takes the independent thermal control design of heat insulation installation.Owing to aircraft period in orbit exists attitude yaw mode, Orbital heat flux excursion is bigger, thermal control design need to ensure that under various operating mode, star sensor is all within the scope of index request, need to increasing the star sensor adaptability 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 installed surface 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, equipped with 25N electromotor near import star sensor A, through simulation analysis and verification experimental verification, must take into the radiation effect that electromotor work brings, therefore import star sensor A mounting flange outer surface cladding low temperature multilamellar, (overcoat adopts temperature multilamellar in three layers, and in every unit, temperature multilamellar is made up of high silica glass cloth (wall) and the one layer 25 μm two-sided aluminizer of the polyimides (reflecting layer) of one layer 100 μm to be coated with one layer of overcoat towards engine side outer surface.Middle temperature multilamellar outmost surface adopts one layer of 25 μm of conductivity type polyimides to aluminize second surface mirror coating.).Finally, by pasting electric heater at star sensor head, it is achieved low temp compensating.
The satellite being commonly installed star sensor is sun-synchronous orbit, yaw mode without attitude, outside hot-fluid is stable, therefore star sensor is when design, except with the heat insulation installation of celestial body, star sensor independence area of dissipation is less, and all the other places are all coated with multilayer insulation assembly, star sensor head pastes low temp compensating heater (every road 10W, take resource more).Meanwhile, near usual Satellite sensor, electromotor is not installed, it is not necessary to consider engine radiation impact.And owing to there is attitude yaw mode in transfer orbit aircraft star sensor, outside hot-fluid is unstable, if taking the measure of general satellite half cladding, under yaw-position, star sensor changes of heat flux outside certainly will be caused with under the joint effect of interior power consumption, and star sensor independence radiating surface is not enough in addition, thus causing that star sensor temperature rises, close to even more than temperature upper limit, causing potential safety hazard.Furthermore, through simulation analysis and experimental study, electromotor is very important to the radiation effect of star sensor, must take into the thermal protection problem of star sensor when thermal design.
Summary of the invention
For defect of the prior art, it is an object of the invention to provide a kind of independent thermal design technology of orbit transfer vehicle star sensor temperature on the low side, this technology is convenient to carry out, reliability is high, strong adaptability, aggregate resource occupancy are few, and can effectively protect engine radiation.
According to a kind of orbit transfer vehicle star sensor independent thermal controls apparatus of temperature on the low side provided by the invention, including import star sensor A, domestic star sensor B, critesistor, heater, shade, F46 thin film, S781 white paint thermal control coating, mounting bracket, self support, heat insulating mattress, multilayer insulation assembly, thermal protection shield；
Import star sensor A, domestic star sensor B head be all pasted with critesistor and heater；
The head of import star sensor A, the shade of import star sensor A and the shade of domestic star sensor B are all pasted with F46 thin film；
Import star sensor A, domestic star sensor B head be all coated with S781 white paint thermal control coating；
Import star sensor A, domestic star sensor B are separately mounted in respective mounting bracket, pad heat insulating mattress between self support and the mounting bracket of import star sensor A, pad heat insulating mattress between the head of domestic star sensor B and mounting bracket；
In the mounting bracket of import star sensor A and self support, cladding multilayer insulation assembly, adds three layers thermal protection shield outside the close engine side of import star sensor A again.
Preferably, heater is spacecraft Kapton type electric heater.
Preferably, the trade mark of critesistor is MF501.
Preferably, F46 thin film is the silver-plated second surface mirror thermal control coating of conductivity type F46.
Preferably, heat insulating mattress is the fiberglass heat insulating mattress being not less than 5mm.
Preferably, multilayer insulation assembly includes 20dChinlon silk screen and 6 μm of two-sided aluminized mylars, the outermost layer of multilayer insulation assembly 10 is the conductivity type silver-plated second surface mirror of F46 thin film.
Preferably, thermal protection shield adopts temperature multilamellar in three layers, in every layer, temperature multilamellar is made up of one layer of high silica glass cloth as 100 μm of wall and one layer of 25 μm of two-sided aluminizer of polyimides as reflecting layer, and middle temperature multilamellar outmost surface one layer of 25 μm of conductivity type polyimides of employing are aluminized second surface mirror coating.
Compared with prior art, the present invention has following beneficial effect:
1, adopt heat insulating mattress to increase the thermal resistance between celestial body and star sensor, greatly reduce 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 temperature adaptation ability of star sensor motive track；
3, adopt multilayer insulation assembly and overcoat, effectively protect the 25N electromotor radiation effect to import star sensor A；
4, electric heater and critesistor are adopted, the wherein active and standby each 4W of star sensor A heater, the main 10W of star sensor B heater, heater is for 7W (conventional satellite star sensor heater 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, for star sensor stable operation in-orbit, it is provided that good thermal environment；
5, this technology is convenient to carry out, reliability is high, thermal adaptability is strong, aggregate resource takies few, adapts to vehicle out-driving impact, and can effectively protect the 25N electromotor heat radiation on star sensor and affect, it is adaptable to orbit transfer vehicle star sensor thermal design.
Accompanying drawing explanation
By reading detailed description non-limiting example made with reference to the following drawings, the other features, objects and advantages of the present invention will become more apparent upon:
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, critesistor, 3, heater, 4, shade, 5, F46 thin film, 6, S781 white paint thermal control coating, 7, mounting bracket, 8, import self support of star sensor A, 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 example will assist in those skilled in the art and are further appreciated by the present invention, but do 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, it is also possible to make some deformation and improvement.These broadly fall into protection scope of the present invention.
The technical scheme is that providing one can be applied to the orbit transfer vehicle star sensor independent thermal controls apparatus of temperature on the low side, including heat insulating mattress, S781 white paint thermal control coating, multilayer insulation assembly, thermal protection shield, electric heater and critesistor；It is characterized in that: pad heat insulating mattress between star sensor head and its bracket mounting face, reduce the thermal coupling between star sensor and nacelle；Owing to being affected 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 installed surface 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.Import star sensor A mounting flange outer surface cladding low temperature multilamellar, is coated with one layer of overcoat towards engine side outer surface, has effectively protected the heat radiation impact that 25N electromotor brings.Finally, by pasting electric heater and critesistor at star sensor head, it is achieved monitoring and the accurate temperature controlling in real time to star sensor temperature.
Described star sensor head and the heat insulation installation of its bracket mounting face, it is preferable that described heat insulating mattress is the fiberglass heat insulating mattress being not less than 5mm；Described star sensor radiating surface spraying S781 white paint thermal control coating；Described multilayer insulation assembly is by 20dChinlon silk screen and 6 μm of two-sided aluminized mylar compositions, outermost layer is the conductivity type silver-plated second surface mirror of F46 thin film；Described thermal protection shield adopts temperature multilamellar in three layers, in every unit, temperature multilamellar is made up of high silica glass cloth (wall) and the one layer 25 μm two-sided aluminizer of the polyimides (reflecting layer) of one layer 100 μm, and middle temperature multilamellar outmost surface one layer of 25 μm of conductivity type polyimides of employing are aluminized second surface mirror coating；Preferred shade sticking film is the conductivity type silver-plated second surface mirror of F46 thin film；Described heater is spacecraft Kapton type electric heater, arranges two-way, each other master backup, strengthen its reliability, be pasted on star sensor head, wherein the active and standby each 4W of star sensor A heater, the main 10W of star sensor B heater, heater is for 7W, and and fits good between monomer；The preferred described critesistor trade mark is MF501.
Specifically, first critesistor 2 and heater 3 is pasted at star sensor head 1, ensure that heater 3 is good with the laminating of star sensor head 1 surface, paste F46 thin 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 heater 3 is spacecraft Kapton type electric heater, it is preferable that described critesistor 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 thin film 5 for the silver-plated second surface mirror thermal control coating of conductivity type F46.
Then star sensor is arranged on support 7, between import star sensor A self support 8 and mounting bracket 7, pads heat insulating mattress 9, pad heat insulating mattress 9 between domestic star sensor head 1 and mounting bracket 7, it is preferable that described heat insulating mattress 9 is the fiberglass heat insulating mattress being not less than 5mm.
Last cladding multilayer insulation assembly 10 in import star sensor mounting bracket 7 and self support 8, adds three layers thermal protection shield 11 again outside engine side, and described multilayer insulation assembly 10 is by 20dChinlon silk screen and 6 μm of two-sided aluminized mylar compositions, outermost layer is the conductivity type silver-plated second surface mirror of F46 thin film；Described thermal protection shield 11 adopts temperature multilamellar in three layers, in every unit, temperature multilamellar is made up of high silica glass cloth (wall) and the one layer 25 μm two-sided aluminizer of the polyimides (reflecting layer) of one layer 100 μm, and middle temperature multilamellar outmost surface one layer of 25 μm of conductivity type polyimides of employing are aluminized second surface mirror coating.
Above specific embodiments of the invention are described.It is to be appreciated that the invention is not limited in above-mentioned particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims, and this has no effect on the flesh and blood of the present invention.
Claims (6)
1. the orbit transfer vehicle star sensor independent thermal controls apparatus of temperature on the low side, it is characterized in that, including import star sensor (A), domestic star sensor (B), critesistor (2), heater (3), shade (4), F46 thin 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)；
Import star sensor (A), domestic star sensor (B) head (1) be all pasted with critesistor (2) and heater (3)；
The head (1) of import star sensor (A), the shade (4) of import star sensor (A) and the shade (4) of domestic star sensor (B) are all pasted with F46 thin film (5)；
Import star sensor (A), domestic star sensor (B) head (1) be all coated with S781 white paint thermal control coating (6)；
Import star sensor (A), domestic star sensor (B) are separately mounted in respective mounting bracket (7), 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 self support (8) upper cladding multilayer insulation assembly (10), add three layers thermal protection shield (11) again outside the close engine side of import star sensor (A)；
Thermal protection shield (11) adopts temperature multilamellar in three layers, in every layer, temperature multilamellar is made up of one layer of high silica glass cloth as 100 μm of wall and one layer of 25 μm of two-sided aluminizer of polyimides as reflecting layer, and middle temperature multilamellar outmost surface one layer of 25 μm of conductivity type polyimides of employing are aluminized second surface mirror coating.
2. the orbit transfer vehicle star sensor according to claim 1 independent thermal controls apparatus of temperature on the low side, it is characterised in that heater (3) is spacecraft Kapton type electric heater.
3. the orbit transfer vehicle star sensor according to claim 1 independent thermal controls apparatus of temperature on the low side, it is characterised in that the trade mark of critesistor (2) is MF501.
4. the orbit transfer vehicle star sensor according to claim 1 independent thermal controls apparatus of temperature on the low side, it is characterised in that F46 thin film (5) is the silver-plated second surface mirror thermal control coating of conductivity type F46.
5. the orbit transfer vehicle star sensor according to claim 1 independent thermal controls apparatus of temperature on the low side, it is characterised in that heat insulating mattress (9) is the fiberglass heat insulating mattress being not less than 5mm.
6. the orbit transfer vehicle star sensor according to claim 1 independent thermal controls apparatus of temperature on the low side, it is characterised in that multilayer insulation assembly (10) includes 20dChinlon silk screen and 6 μm of two-sided aluminized mylars, the outermost layer of multilayer insulation assembly 10 is the conductivity type silver-plated second surface mirror of F46 thin film.
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