CN106767909B - Earth simulator for measuring attitude of linear array infrared earth sensor - Google Patents
Earth simulator for measuring attitude of linear array infrared earth sensor Download PDFInfo
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- CN106767909B CN106767909B CN201611086487.5A CN201611086487A CN106767909B CN 106767909 B CN106767909 B CN 106767909B CN 201611086487 A CN201611086487 A CN 201611086487A CN 106767909 B CN106767909 B CN 106767909B
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- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
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Abstract
The invention discloses an earth simulator for measuring the attitude of a linear array infrared earth sensor, which comprises four earth boundary infrared radiation simulation units, four attitude simulation units and a system control unit. The earth boundary infrared radiation simulation unit simulates by adjusting the infrared radiation difference of the hot plate and the cold diaphragm; the four attitude simulation units respectively drive the four infrared radiation simulation units to rotate, earth infrared radiation images seen when the infrared earth sensor operates under different attitudes are simulated, a ground test means is provided for the attitude and orbit control subsystem to carry out linear array static infrared earth sensor, and high-precision attitude measurement is further ensured to be provided for the satellite by the infrared earth sensor. The invention has the advantages that: the simulator has strong universality, good stability and high precision.
Description
Technical Field
The invention relates to ground test equipment of a satellite-borne infrared earth sensor. In particular to a novel method for generating an earth radiation source simulation, which is suitable for a linear array infrared earth sensor detection means.
Background
One type of infrared earth sensor is an attitude sensor which measures the orientation of a spacecraft relative to a local vertical line or a local horizon by using the infrared radiation of the earth, and is also called a horizon. Currently, the infrared earth sensor mainly has 3 forms: horizon-crossing, boundary-tracking, and radiant heat-balancing. The linear array static infrared earth sensor is a typical radiant heat balance type earth sensor, has small volume and mass and low power consumption because of no moving parts, is particularly suitable for long-life flight tasks, and is widely applied to artificial satellites such as ground directional detection, meteorology, communication, ground fund and the like.
The linear array static infrared earth sensor (hereinafter referred to as earth sensor) generally has 4 optical systems which are symmetrically distributed at equal intervals. Each optical system respectively receives infrared radiation from different parts of the earth, and the attitude of the spacecraft is obtained by analyzing different infrared radiation energy received by each optical system. For example, the earth sensor indicates that the attitude angle of the spacecraft is zero when all optical systems receive equal energy. When the received energy of the front optical system and the rear optical system is not equal, the spacecraft is represented to have attitude deviation on a pitching axis; similarly, when the received energy of the left and right fields is not equal, it indicates a deviation in the attitude of the roll axis.
The performance and accuracy of the earth sensor directly affect the working state of the satellite on the orbit. In order to perform performance test and precision calibration on the earth sensor, a set of special performance test equipment, namely an earth simulator, must be developed on the ground for the earth sensor to simulate the infrared images of the earth seen when the earth sensor operates in different orbits and different postures, so as to realize ground test evaluation of the performance indexes of the earth sensor.
Disclosure of Invention
The invention aims to provide an earth simulator suitable for performance test and precision calibration on the ground for different linear array static infrared earth sensors, so that ground test evaluation of performance indexes of the earth sensor is realized, and the universality of the earth simulator is improved.
The earth simulator for measuring the attitude of the linear array infrared earth sensor comprises four earth boundary infrared radiation simulation units 1, four attitude simulation units 2 and a system control unit 3;
the earth infrared radiation simulation unit is characterized in that a heating film 1-5 in the earth infrared radiation simulation unit is adhered to a hot plate 1-7, a heating film thermal baffle 1-4 covers the heating film 1-5 and is fixedly connected with the hot plate 1-7 through a screw, the hot plate 1-7 and a cold diaphragm 1-2 are fixedly connected through four hot plate thermal insulation supports 1-6, an infrared collimating mirror 1-1 is fixedly connected with a frame 1-3 through a screw, the frame 1-3 is fixedly connected with an arc swinging table 2-1 through a screw, earth boundary infrared radiation is simulated by controlling the temperature difference of the hot plate 1-7 and the cold diaphragm 1-2 in the earth infrared radiation simulation unit 1, and the four infrared radiation simulation units jointly form the whole infrared radiation earth infrared radiation;
the arc swing table 2-1 in the attitude simulation unit 2 is fixedly connected with the inclined bracket 2-2 through a screw, and the inclined bracket 2-2 is fixedly connected with the top plate 2-3 through a screw;
the system control unit 3 controls the attitude simulation unit 2 to drive the earth infrared radiation simulation unit 1 to rotate, and the angle change of different attitudes is simulated, so that the ground test and calibration of the on-line array infrared earth sensor are realized.
The invention has the advantages that: the simulator has strong universality, good stability and high precision.
Drawings
FIG. 1 is a diagram of an earth simulator composition;
in the figure: 1-earth infrared radiation simulation unit; 2-an attitude simulation unit; and 3, a system control unit.
FIG. 2 is a block diagram of an earth simulator;
in the figure: 1-1-infrared lens, 1-2-cold diaphragm, 1-3-frame, 1-4-heating film heat-insulating plate, 1-5-heating film and 1-6-heat-insulating support, 1-7-hot plate, 2-1-arc placing table, 2-2-inclined support and 2-3-top plate.
Detailed Description
A preferred embodiment of the present invention is shown in fig. 1 and 2 and described in detail to better understand the structural and functional features of the present invention. It should be noted that the examples are given for illustrating the present invention and are not intended to limit the scope of the present invention.
As shown in fig. 1, the present invention includes four earth boundary infrared radiation simulation units 1, four attitude simulation units 2, and a system control unit 3. The earth infrared radiation simulation unit 1 is controlled to generate an infrared radiation signal, the attitude simulation unit 2 drives the infrared radiation simulation unit 1 to rotate, the system control unit 3 controls the temperature difference of the earth infrared radiation simulation unit 1 and the rotation parameters of the attitude simulation unit 2 to simulate four attitude angle earth infrared radiation of (rolling angle 0 degrees, pitch angle 15 degrees), (rolling angle 15 degrees, pitch angle 0 degrees), (rolling angle 0 degrees, pitch angle-15 degrees) and (rolling angle-15 degrees and pitch angle 0 degrees), and the linear array infrared earth sensor obtains corresponding attitude angle changes through collection, processing and calculation and corresponds to the attitude angle simulated by the earth simulator to perform ground test and judgment test on the linear array static infrared earth sensor.
As shown in figure 2, a heating film 1-5 in an earth infrared radiation simulation unit is adhered to a hot plate 1-7, a heating film thermal baffle 1-4 is covered on the heating film 1-5 and is fixedly connected with the hot plate 1-7 through a screw, the hot plate 1-7 and a cold diaphragm 1-2 are fixedly connected through four hot plate thermal insulation supports 1-6, an infrared collimating mirror 1-1 is fixedly connected with a frame 1-3 through a screw, the frame 1-3 is fixedly connected with an arc swinging table 2-1 through a screw, the arc swinging table 2-1 is fixedly connected with an inclined support 2-2 through a screw, and the inclined support 2-2 is fixedly connected with a top plate 2-3 through a screw.
Wherein the focal length of the infrared collimating lens 1-6 is 14.2mm, the field angle is 32 degrees, the surfaces of the cold diaphragm 1-2 diaphragm and the hot plate 1-7 are subjected to black anodic oxidation treatment, and the emission coefficienth≥0.85。
Claims (1)
1. An earth simulator for measuring the attitude of a linear array infrared earth sensor comprises four earth boundary infrared radiation simulation units (1), four attitude simulation units (2) and a system control unit (3); the method is characterized in that:
the earth boundary infrared radiation simulation device is characterized in that a heating film (1-5) in an earth boundary infrared radiation simulation unit (1) is adhered to a hot plate (1-7), a heating film thermal baffle (1-4) covers the heating film (1-5), the heating film thermal baffle (1-4) and the heating film (1-5) are fixedly connected with the hot plate (1-7) through screws, the hot plate (1-7) and a cold diaphragm (1-2) are fixedly connected through four hot plate thermal insulation supports (1-6), an infrared collimating mirror (1-1) is fixedly connected with a frame (1-3) through screws, the frame (1-3) is fixed with an arc swing table (2-1) through screws, and the earth boundary infrared radiation is simulated by controlling the temperature difference of the hot plate (1-7) and the cold diaphragm (1-2) in the earth boundary infrared radiation simulation unit (1), the four infrared radiation simulation units jointly form the whole infrared earth thermal radiation; wherein, the focal length of the infrared collimating lens is 14.2mm, and the field angle is 32 degrees;
the arc swing table (2-1) in the attitude simulation unit (2) is fixedly connected with the inclined bracket (2-2) through a screw, and the inclined bracket (2-2) is fixedly connected with the top plate (2-3) through a screw;
the system control unit (3) controls the attitude simulation unit (2) to drive the earth boundary infrared radiation simulation unit (1) to rotate, and the angle change of different attitudes is simulated, so that the ground test and calibration of the on-line array infrared earth sensor are realized.
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| CN201611086487.5A CN106767909B (en) | 2016-11-30 | 2016-11-30 | Earth simulator for measuring attitude of linear array infrared earth sensor |
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| CN106767909B true CN106767909B (en) | 2020-10-13 |
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| CN109459216B (en) * | 2018-12-27 | 2019-07-30 | 北京航天长征飞行器研究所 | Extraterrestrial target various dimensions dynamic optical characteristic integrated measuring system and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101462599A (en) * | 2008-12-15 | 2009-06-24 | 中国科学院上海技术物理研究所 | Novel terrestrial globe simulator for static state infrared horizon ground detection |
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| FR2816406B1 (en) * | 2000-11-08 | 2003-04-18 | Centre Nat Etd Spatiales | GROUND TEST BENCH OF A STELLAR SENSOR FOR PART OF AN ATTITUDE MONITORING SYSTEM OF AN ARTIFICIAL SATELLITE |
| CN102175247B (en) * | 2011-01-14 | 2012-11-14 | 中国科学院上海技术物理研究所 | Method for improving altitude measurement precision of linear array static infrared horizon sensor |
| CN105136171B (en) * | 2015-09-22 | 2017-11-21 | 中国科学院上海技术物理研究所 | Analogy method based on linear array infrared earth sensor electric signal generation device |
| CN206281500U (en) * | 2016-11-30 | 2017-06-27 | 中国科学院上海技术物理研究所 | For the earth simulator for earth of linear array infrared earth sensor attitude measurement |
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| CN101462599A (en) * | 2008-12-15 | 2009-06-24 | 中国科学院上海技术物理研究所 | Novel terrestrial globe simulator for static state infrared horizon ground detection |
Non-Patent Citations (1)
| Title |
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| 地球模拟器中热地球温度分析;付东辉等;《光机电信息》;20101130;第27卷(第11期);正文第1-3节 * |
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