CN108820259B - Integral thermal protection device suitable for multidimensional movement of extraterrestrial rotating mechanism - Google Patents
Integral thermal protection device suitable for multidimensional movement of extraterrestrial rotating mechanism Download PDFInfo
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- CN108820259B CN108820259B CN201810661575.6A CN201810661575A CN108820259B CN 108820259 B CN108820259 B CN 108820259B CN 201810661575 A CN201810661575 A CN 201810661575A CN 108820259 B CN108820259 B CN 108820259B
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- 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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Abstract
The invention discloses an integral thermal protection device suitable for multidimensional movement of an extraterrestrial rotating mechanism, wherein a plurality of layers of frameworks are installed and fixed on the periphery of the multidimensional rotating mechanism, and the size of the plurality of layers of frameworks is larger than the envelope of the multidimensional movement track of the mechanism; the fixed multilayer heat insulation assembly is coated on the periphery of the multilayer framework to form a multilayer cover; one end of the elastic multilayer heat insulation assembly is coated on the top of the multilayer framework, the other end of the elastic multilayer heat insulation assembly is arranged on a structural component on the upper part of the rotating mechanism, and a certain margin is reserved in the length direction; the thermal control coating is integrally sprayed on the outer surface of the multidimensional rotating mechanism; the fixed multilayer heat insulation assembly is provided with a plurality of heat dissipation windows for providing heat dissipation channels of the multidimensional rotating mechanism; the thermal compensation element is mounted on the multi-dimensional rotating mechanism component. According to the invention, the effect of integral thermal control coating on the rotating mechanism is achieved by combining the rigid multilayer framework with the fixed and elastic multilayer heat insulation assembly, and meanwhile, the hooking risk of the traditional thermal control coating on the multidimensional movement of the mechanism is eliminated.
Description
Technical Field
The invention relates to the technical field of aerospace and aviation, in particular to an integral thermal protection device suitable for multidimensional movement of an extraterrestrial rotating mechanism.
Background
Most of communication, data transmission and relay antennas configured by current spacecrafts such as communication, remote sensing or relay have a multi-dimensional rotation function, the structure of a rotation mechanism is complex, the mechanism is greatly influenced by heat flow outside the space, and the temperature gradient of mechanism parts can be caused by the illumination difference of different parts of the rotation mechanism at the same moment. If the thermal deformation caused by the temperature difference of the rotating mechanism parts reaches a certain degree, the rotating mechanism is blocked or the performance is reduced, and finally the data transmission of the spacecraft is influenced. The traditional thermal design is that the mechanism is integrally sprayed with a thermal control coating, and the design state can cause that the temperature difference of the rotating mechanism is huge in different seasons of the rail, so that the integral temperature level of the mechanism is difficult to effectively control. In addition, a large amount of electric power resources are required for the heat preservation of the mechanism during low temperatures, and for compensating for the temperature difference of the rotating mechanism. The optimal thermal design method is that the influence of the heat flow change outside the space on the temperature of the mechanism is isolated by the integral thermal control coating of the rotating part, so that the integral temperature level of the mechanism is stable; meanwhile, the heat dissipation window meets the heat dissipation requirement of the mechanism in the high-temperature season at the end of the rail, and the temperature control requirement of the mechanism in the low-temperature season at the initial stage of the rail is guaranteed in an active thermal compensation mode. The design idea not only meets the temperature control requirements of the rotating mechanism in different seasons at different periods of the orbit, but also consumes less satellite power resources, and has small temperature level difference and small thermal deformation of the whole mechanism.
Disclosure of Invention
The invention provides an integral thermal protection device suitable for multidimensional movement of an extraterrestrial rotating mechanism, which achieves the effect of integral thermal control coating on the rotating mechanism in a mode of combining a rigid multilayer framework with a fixed and elastic multilayer thermal insulation assembly, and simultaneously eliminates the hooking risk of the traditional thermal control coating on the multidimensional movement of the mechanism.
The purpose of the invention is realized by the following technical scheme: an integral thermal protection device suitable for multidimensional movement of an extraterrestrial rotating mechanism comprises a multi-layer framework, a fixed multi-layer heat insulation assembly, an elastic multi-layer heat insulation assembly, a thermal control coating and a thermal compensation element; the multi-layer framework is fixedly arranged on the periphery of the multi-dimensional rotating mechanism, and the size of the multi-layer framework is larger than the envelope of the multi-dimensional motion track of the mechanism; the fixed multilayer heat insulation assembly is coated on the periphery of the multilayer framework to form a multilayer cover; one end of the elastic multilayer heat insulation assembly is coated on the top of the multilayer framework, the other end of the elastic multilayer heat insulation assembly is arranged on a structural component on the upper part of the rotating mechanism, and a certain allowance is formed in the length direction, so that the multidimensional movement of the mechanism is not influenced; the thermal control coating is integrally sprayed on the outer surface of the multidimensional rotating mechanism; the fixed multilayer heat insulation assembly is provided with a plurality of heat dissipation windows for providing heat dissipation channels of the multidimensional rotating mechanism; the thermal compensation element is arranged on the multidimensional rotating mechanism component and used for thermal compensation when the temperature of the mechanism component is lower than the stored low temperature.
The fixed multilayer heat insulation assembly and the elastic multilayer heat insulation assembly are composed of 20 units, each unit is composed of a layer of double-sided aluminum-plated polyester film and a layer of nylon mesh cloth at intervals, and the outermost surface film of the multilayer heat insulation assembly is an antistatic polyimide aluminum-plated secondary surface mirror.
The heat dissipation window is arranged on the north side of the fixed type multilayer heat insulation assembly, and the opening angle of the heat dissipation window is 44 degrees.
The thermal control coating is made of ACR-1 antistatic white paint, and the spraying is implemented according to the specification of the ACR-1 antistatic white paint.
The thermal compensation element is a polyimide film type electric heating element, is pasted on a motor and a joint of the multidimensional rotating mechanism, and is used for thermal compensation of the mechanism storage state in low-temperature seasons.
Compared with the prior art, the invention has the following beneficial effects:
(1) the influence of heat flow outside the space on the rotating mechanism can be greatly reduced, the integral temperature gradient of the mechanism is reduced, and the thermal deformation of the mechanism is effectively reduced;
(2) the rigid multilayer framework combines the mode of fixing the multilayer heat insulation assembly and the mode of 'elastic' multilayer heat insulation assembly, has the effect of integral thermal control coating on the rotating mechanism, and simultaneously eliminates the hooking risk of the traditional thermal control coating on the multidimensional movement of the mechanism;
(3) the thermal design method is reasonable and feasible, consumes less satellite power resources, and has simple process realization, good reliability and strong adaptability.
Drawings
Fig. 1 is a schematic view of an overall thermal protection device adapted to multi-dimensional motion of an outboard rotating mechanism according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of an embodiment of the present invention.
Fig. 3 shows the in-orbit operation data of the GEO satellite data transmission antenna according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in FIG. 1, the embodiment of the invention provides an integral thermal protection device for multi-dimensional movement of an outboard rotating mechanism, which comprises a multi-layer framework 1, a fixed multi-layer thermal insulation assembly 2, an elastic multi-layer thermal insulation assembly 3, a thermal control coating and a thermal compensation element; the multi-layer framework 1 is fixedly arranged on the periphery of the multi-dimensional rotating mechanism, and the size of the multi-layer framework 1 is larger than the envelope of the multi-dimensional motion track of the mechanism; the fixed multilayer heat insulation assembly 2 is coated around the multilayer framework to form a multilayer cover; one end of the elastic multilayer heat insulation component 3 is coated on the top of the multilayer framework, the other end of the elastic multilayer heat insulation component is arranged on a structural part at the upper part of the rotating mechanism, and a certain margin is reserved in the length direction, so that the multidimensional movement of the mechanism is not influenced; the thermal control coating is integrally sprayed on the outer surface of the multidimensional rotating mechanism; the fixed multilayer heat insulation assembly is provided with a plurality of heat dissipation windows 4 for providing heat dissipation channels of the multidimensional rotating mechanism; the thermal compensation element is arranged on the multidimensional rotating mechanism component and used for thermal compensation when the temperature of the mechanism component is lower than the stored low temperature.
The fixed multilayer heat insulation assembly and the elastic multilayer heat insulation assembly are composed of 20 units, each unit is composed of a layer of double-sided aluminum-plated polyester film and a layer of nylon mesh cloth at intervals, and the outermost surface film of the multilayer heat insulation assembly is an antistatic polyimide aluminum-plated secondary surface mirror.
The heat dissipation window is arranged on the north side of the fixed type multilayer heat insulation assembly, and the opening angle of the heat dissipation window is 44 degrees. The thermal control coating is made of ACR-1 antistatic white paint, and the spraying is implemented according to the specification of the ACR-1 antistatic white paint. The thermal compensation element is a polyimide film type electric heating element, is pasted on a motor and a joint of the multidimensional rotating mechanism, and is used for thermal compensation of the mechanism storage state in low-temperature seasons.
As shown in fig. 2, the two-dimensional rotation mechanism of the data transmission antenna of a GEO satellite is analyzed and calculated by adopting the thermal control design device, the model is necessarily simplified and assumed, and the basic parameters of the satellite, such as the orbit, the attitude and the like, are set according to the overall technical requirements; the selection of the thermophysical parameters of the satellite thermal control coating and the material is set according to the general technical requirements. According to the in-orbit operation data of a certain GEO satellite data transmission antenna shown in the attached figure 3, the temperature of the two-dimensional rotating mechanism is controlled at a reasonable level after the thermal design method and the measures are adopted, the two-dimensional rotating mechanism of the data transmission antenna works stably, and the performance meets the requirements. Meanwhile, the effectiveness and the reasonability of the thermal design method and the measures are verified.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (1)
1. An integral thermal protection device suitable for multidimensional movement of an extraterrestrial rotating mechanism is characterized by comprising a multi-layer framework, a fixed multi-layer heat insulation assembly, an elastic multi-layer heat insulation assembly, a thermal control coating and a thermal compensation element; the multi-layer framework is fixedly arranged on the periphery of the multi-dimensional rotating mechanism, and the size of the multi-layer framework is larger than the envelope of the multi-dimensional motion track of the mechanism; the fixed multilayer heat insulation assembly is coated on the periphery of the multilayer framework to form a multilayer cover; one end of the elastic multilayer heat insulation assembly is coated on the top of the multilayer framework, the other end of the elastic multilayer heat insulation assembly is arranged on a structural component on the upper part of the rotating mechanism, and a certain allowance is formed in the length direction, so that the multidimensional movement of the mechanism is not influenced; the thermal control coating is integrally sprayed on the outer surface of the multidimensional rotating mechanism; the fixed multilayer heat insulation assembly is provided with a heat dissipation window for providing a heat dissipation channel of the multidimensional rotating mechanism; the thermal compensation element is arranged on the multidimensional rotating mechanism part;
the fixed multilayer heat insulation assembly and the elastic multilayer heat insulation assembly are both composed of 20 units, each unit is composed of a layer of double-sided aluminum-plated polyester film and a layer of nylon mesh cloth at intervals, and the outermost surface film of the multilayer heat insulation assembly is an antistatic polyimide aluminum-plated secondary surface mirror;
the heat dissipation window is arranged on the north side of the fixed multilayer heat insulation assembly, and the opening angle is 44 degrees;
the thermal control coating is ACR-1 antistatic white paint, and the spraying is implemented according to the specification of the ACR-1 antistatic white paint;
the thermal compensation element is a polyimide film type electric heating element, is pasted on a motor and a joint of the multidimensional rotating mechanism, and is used for thermal compensation of the mechanism storage state in low-temperature seasons.
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| CN201810661575.6A CN108820259B (en) | 2018-06-25 | 2018-06-25 | Integral thermal protection device suitable for multidimensional movement of extraterrestrial rotating mechanism |
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| CN201810661575.6A CN108820259B (en) | 2018-06-25 | 2018-06-25 | Integral thermal protection device suitable for multidimensional movement of extraterrestrial rotating mechanism |
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| CN108820259B true CN108820259B (en) | 2020-07-10 |
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| CN112366438A (en) * | 2020-10-22 | 2021-02-12 | 西安空间无线电技术研究所 | Satellite-borne antenna multilayer composite temperature control cover |
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| CN202797273U (en) * | 2012-07-19 | 2013-03-13 | 北京空间飞行器总体设计部 | Thermal protection device for moving parts of movable spot beam antennas |
| 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 |
| CN103662088B (en) * | 2013-11-26 | 2015-08-19 | 中国空间技术研究院 | A kind of star sensor thermal control layout method of GEO orbiter |
| CN104290924B (en) * | 2014-09-17 | 2017-05-24 | 上海卫星工程研究所 | Star sensor temperature control device |
| CN204250387U (en) * | 2014-09-17 | 2015-04-08 | 上海卫星工程研究所 | Star sensor temperature regulating device |
| CN104210673B (en) * | 2014-09-19 | 2016-08-24 | 航天东方红卫星有限公司 | A kind of thermal control method of the quick molectron of star |
| CN104443441B (en) * | 2014-10-31 | 2016-07-27 | 上海卫星工程研究所 | Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature |
| CN104477415B (en) * | 2014-11-21 | 2017-01-11 | 上海卫星工程研究所 | Light-shading heat-insulation cover framework structure for spacecraft |
| CN107264843A (en) * | 2017-05-18 | 2017-10-20 | 上海卫星工程研究所 | The outer unit temperature protective device of light special-shaped star |
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