CN109004335B - Thermal control design method of large-caliber antenna suitable for Mars detection - Google Patents
Thermal control design method of large-caliber antenna suitable for Mars detection Download PDFInfo
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- CN109004335B CN109004335B CN201810631112.5A CN201810631112A CN109004335B CN 109004335 B CN109004335 B CN 109004335B CN 201810631112 A CN201810631112 A CN 201810631112A CN 109004335 B CN109004335 B CN 109004335B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/12—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave
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- Aviation & Aerospace Engineering (AREA)
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- Aerials With Secondary Devices (AREA)
Abstract
The invention discloses an antenna main reflecting surface of a large-aperture antenna and an antenna mechanism which are independently designed, wherein the antenna mechanism is arranged on a satellite through a driving motor, two heaters are respectively arranged at two ends of a frame of the driving motor, and two paths of heaters are independently controlled in a closed loop manner; a polyimide film is adhered to the back surface of the main reflecting surface of the antenna; the front surface of the antenna main reflecting surface adopts a passive thermal control design of thermal control paint spraying. The invention designs the main reflecting surface and the mechanism of the large-aperture antenna independently and controls the main reflecting surface and the mechanism independently, and particularly adopts the independent design of the heater and the closed-loop control to accurately control the temperature difference at two ends according to the temperature difference requirements at two ends of the motor frame. The main reverse back of the antenna adopts a special thermal design of sticking a polyimide film, so that low-temperature compensation can be carried out by using the heat of the star body, the heat compensation can be obtained from the star body when the temperature of the antenna is low, heat can be radiated outwards when the temperature of the antenna is high, and not only can accurate control be realized, but also energy can be saved.
Description
Technical Field
The invention belongs to the field of spacecraft thermal control, and particularly relates to a large-caliber antenna thermal control design method suitable for Mars detection.
Background
With the development of aerospace technology, the breadth and depth of deep space exploration performed by human beings are continuously increased, and compared with a near-earth space spacecraft, the deep space spacecraft has the advantages that the deep space spacecraft has high requirements on the ground communication function due to the long operating distance, and a large-caliber antenna needs to be installed.
Compared with a near-earth satellite antenna, the large-aperture antenna of the Mars detector has the characteristics of complex system structure and severe external thermal environment: firstly, the large-caliber antenna has large size, and the rotating joint and the driving mechanism have complex structures, so that the antenna thermal control design has difficulty. Secondly, the antenna needs to be driven and rotated for many times in the process of flying to a mars, the external heat flow is changed violently, the antenna is heated unevenly, and a fixed radiating surface is not provided, so that high requirements are provided for the thermal design of the large-aperture antenna, and the temperature control requirements of the antenna are met under the limited resource condition.
Therefore, the large-aperture antenna thermal control design method applicable to Mars detection is provided aiming at the characteristics that a large-aperture antenna system of a Mars detector is complex and has high requirements on thermal control design.
Disclosure of Invention
Aiming at the problems, the invention provides a large-caliber antenna thermal control design method suitable for Mars detection.
The invention is realized by the following technical scheme:
a thermal control design method of a large-aperture antenna suitable for Mars detection is characterized in that an antenna main reflecting surface and an antenna mechanism of the large-aperture antenna are independently designed, the antenna mechanism is installed on a satellite through a driving motor, two ends of a frame of the driving motor are respectively provided with a heater, and two paths of heaters are independently controlled in a closed loop mode, so that the temperature difference between the two ends is controlled within a required range when the heaters work; the back of the main reflection surface of the antenna is pasted with a polyimide film, when the main reflection temperature is low, the main reflection temperature can be compensated by the radiation of the star, and when the main reflection temperature is high, partial heat can be radiated outwards, the temperature is reduced, and the effect of reducing the temperature gradient is achieved.
Preferably, the front surface of the main reflecting surface of the antenna adopts a passive thermal control design of thermal control paint spraying to ensure wider temperature adaptability. And for the antenna mechanism, because the requirement on the temperature control range is narrow, and the heat consumption change of the mechanism is large, the antenna mechanism is controlled by adopting a heater, and the heating compensation can be carried out when the temperature is low.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the large-aperture antenna thermal control design method, each part is independently thermally designed according to different temperature requirements of the antenna part, closed-loop control is adopted, particularly the temperature difference requirements of two ends of a motor frame can be accurately controlled, and the antenna system can be conveniently planned and accurately controlled;
(2) the large-aperture antenna adopts the thermal control design of sticking the polyimide film on the back surface, can utilize the heat of the star body to carry out thermal compensation on the antenna, ensures that the heat can be obtained from the star body at low temperature, can radiate outwards at high temperature, and can save energy.
Drawings
Other characteristic objects and advantages of the invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following figures.
Fig. 1 is a schematic diagram of a wire layout in an embodiment of the invention.
FIG. 2 is a schematic diagram of an in-line thermal control design in an embodiment of the 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 it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
According to the large-aperture antenna thermal control design method suitable for Mars detection provided by the embodiment of the invention, the antenna main reflecting surface 1 and the antenna mechanism 2 of the large-aperture antenna are independently designed, and the front surface 11 of the antenna main reflecting surface adopts a passive thermal control design of thermal control paint spraying aiming at different temperature control requirements of all parts of the large-aperture antenna so as to ensure wider temperature adaptability, as shown in figure 1. Aiming at the requirement of the temperature difference between the two ends of the antenna driving motor frame, the heaters 3 are respectively designed at the two ends of the frame for closed-loop control, so that the temperature difference between the two ends is controlled within the required range when the heaters work, as shown in figure 2. The back 12 of the main reflection surface of the antenna adopts a special thermal design to compensate by using the star heat, as shown in fig. 2, the back of the main reflection surface adopts a thermal design of sticking a polyimide film, when the main reflection temperature is low, the main reflection temperature can be compensated by star radiation, and when the main reflection temperature is high, partial heat can be radiated outwards to reduce the temperature, so that the effect of reducing the temperature gradient is achieved.
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 or 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. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (1)
1. A thermal control design method of a large-aperture antenna suitable for Mars detection is characterized in that an antenna main reflecting surface and an antenna mechanism of the large-aperture antenna are independently designed, the antenna mechanism is installed on a satellite through a driving motor, two heaters are respectively arranged at two ends of a frame of the driving motor, and two paths of heaters are independently controlled in a closed loop manner; a polyimide film is adhered to the back surface of the main reflecting surface of the antenna;
aiming at different temperature control requirements of each part of the large-aperture antenna, the front surface of the main reflecting surface of the antenna adopts a passive thermal control design of thermal control paint spraying so as to ensure wider temperature adaptability;
aiming at the requirement of the temperature difference between the two ends of the antenna driving motor frame, heaters are respectively designed at the two ends of the frame for closed-loop control, so that the temperature difference between the two ends is controlled within the required range when the heaters work;
the back of the main reflection surface of the antenna adopts a special thermal design to compensate the back of the main reflection surface by using the star heat and adopts a thermal design of sticking a polyimide film, when the main reflection temperature is low, the main reflection temperature can be compensated by the star radiation, and when the main reflection temperature is high, partial heat can be radiated outwards to reduce the temperature, thereby achieving the effect of reducing the temperature gradient.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810631112.5A CN109004335B (en) | 2018-06-19 | 2018-06-19 | Thermal control design method of large-caliber antenna suitable for Mars detection |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810631112.5A CN109004335B (en) | 2018-06-19 | 2018-06-19 | Thermal control design method of large-caliber antenna suitable for Mars detection |
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| CN109004335A CN109004335A (en) | 2018-12-14 |
| CN109004335B true CN109004335B (en) | 2021-07-30 |
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| CN201810631112.5A Active CN109004335B (en) | 2018-06-19 | 2018-06-19 | Thermal control design method of large-caliber antenna suitable for Mars detection |
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| CN112181023B (en) * | 2020-10-22 | 2021-09-24 | 上海卫星工程研究所 | High-reliability autonomous temperature control method and system for temperature consistency of different areas |
| CN113497360A (en) * | 2021-05-24 | 2021-10-12 | 西安空间无线电技术研究所 | High-precision profile control thermal control structure of zero-transmission solar screen and satellite-borne antenna reflector |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201332140Y (en) * | 2008-11-28 | 2009-10-21 | 北京空间飞行器总体设计部 | Solid-surface antenna reflector thermal control device utilizing single-layered insulating component |
| 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 |
| CN106688333B (en) * | 2010-12-31 | 2014-06-18 | 上海卫星工程研究所 | The thermal controls apparatus of radar antenna transmitting-receiving subassembly |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008265522A (en) * | 2007-04-20 | 2008-11-06 | Japan Aerospace Exploration Agency | Heat control device |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201332140Y (en) * | 2008-11-28 | 2009-10-21 | 北京空间飞行器总体设计部 | Solid-surface antenna reflector thermal control device utilizing single-layered insulating component |
| CN106688333B (en) * | 2010-12-31 | 2014-06-18 | 上海卫星工程研究所 | The thermal controls apparatus of radar antenna transmitting-receiving subassembly |
| 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 |
| 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 |
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