CN111854803B - Star sensor thermal stability detection device and detection method thereof - Google Patents
Star sensor thermal stability detection device and detection method thereof Download PDFInfo
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- CN111854803B CN111854803B CN202010746849.9A CN202010746849A CN111854803B CN 111854803 B CN111854803 B CN 111854803B CN 202010746849 A CN202010746849 A CN 202010746849A CN 111854803 B CN111854803 B CN 111854803B
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Abstract
The invention discloses star sensor thermal stability detection equipment which comprises a vacuum tank and a plurality of supports arranged in the vacuum tank, wherein the front surface of each support is used for mounting a star sensor, the front surface of each support is provided with a star sensitive prism positioned on the side surface of the star sensor, the back surface of each support is provided with a beam splitter prism, the side surface of each beam splitter prism is provided with a reflector, each support is correspondingly provided with a multi-star simulator, a single-axis autocollimator and a double-axis autocollimator which are positioned outside the vacuum tank, the vacuum tank is provided with a plurality of glass windows, the star sensor is coaxial with the optical axis of the corresponding multi-star simulator through the glass windows, the star sensitive prism is coaxial with the optical axis of the corresponding single-axis autocollimator through the glass windows, and the beam splitter prism is coaxial with the optical axis of the corresponding double-axis autocollimator through the glass windows. Through a plurality of supports of inside setting, can carry out a plurality of star sensor's thermal stability simultaneously and detect, reduce cost improves detection efficiency. The invention also discloses a detection method applying the equipment.
Description
Technical Field
The invention relates to the field of star sensor detection, in particular to star sensor thermal stability detection equipment. In addition, the invention also relates to a detection method applying the equipment.
Background
The star sensor on the satellite is an important component for accurately adjusting the attitude of the satellite, and in the development process of the star sensor, the star sensor is comprehensively tested under the space environment condition besides image quality evaluation and performance test under the laboratory condition so as to investigate the adaptability of the star sensor to the space environment condition, and necessary basic data is provided for the thermal design of the star sensor.
Therefore, the method is an essential important detection item for the thermal vacuum and thermo-optical test evaluation of the star sensor. The method aims to evaluate whether an optical axis of the star sensor deviates from a detector under the conditions of vacuum, high and low temperature and thermal radiation through a simulated orbit environment, find out the quantitative relation corresponding to the change of the optical axis and the detector along with the temperature, and give correction.
Therefore, how to provide a device capable of efficiently and accurately detecting the thermal stability of multiple star sensors at the same time is a technical problem to be solved by those skilled in the art.
Disclosure of Invention
The invention aims to provide star sensor thermal stability detection equipment, which is internally provided with a plurality of supports, can detect the thermal stability of a plurality of star sensors at the same time, reduces the cost and improves the detection efficiency. Another object of the present invention is to provide a detection method using the above-mentioned device.
In order to solve the technical problems, the invention provides star sensor thermal stability detection equipment which comprises a vacuum tank and a plurality of supports arranged in the vacuum tank, wherein a temperature adjusting device is arranged in the vacuum tank, the front surface of each support is used for installing a star sensor, a star sensor prism positioned on the side surface of the star sensor is arranged on the front surface of each support, a beam splitter prism is arranged on the back surface of each support, a reflector is arranged on the side surface of the beam splitter prism, each support is correspondingly provided with a multi-star simulator, a single-axis autocollimator and a double-axis autocollimator which are positioned outside the vacuum tank, a plurality of glass windows are arranged on the vacuum tank, the star sensor is coaxial with the optical axis of the corresponding multi-star simulator through the glass windows, and the star sensor prism is coaxial with the optical axis of the corresponding single-axis autocollimator through the glass windows, the beam splitter prism is coaxial with the optical axis of the corresponding biaxial autocollimator through the glass window.
Preferably, the single-axis autocollimator is mounted on the corresponding side surface of the multi-star simulator and aligned with the same glass window.
Preferably, the plurality of glass windows are opposite to each other in pairs, and the two opposite glass windows are respectively aligned with the front and the back of the same bracket.
Preferably, each support side is provided with a mounting frame, and the reflector is arranged on the mounting frame.
Preferably, the support is in particular a T-shaped frame.
Preferably, the device comprises three uniformly distributed supports, the back surfaces of the supports face the center of the vacuum tank, six uniformly distributed glass windows, three multi-star simulators and three double-shaft autocollimators are arranged on the vacuum tank in an alternating mode.
The invention discloses a detection method of star sensor thermal stability detection equipment, which comprises the following steps:
installing a plurality of star sensors to be detected on the front sides of the corresponding brackets;
acquiring first initial position information of the star sensor about the corresponding multi-star simulator;
acquiring second initial position information of the single-axis autocollimator about the corresponding star sensor prism;
acquiring third initial position information of the biaxial autocollimator about the corresponding beam splitter prism;
adjusting the temperature or the vacuum degree in the vacuum tank;
acquiring first detection position information of the star sensor about the corresponding multi-star simulator;
acquiring second detection position information of the single-axis autocollimator about the corresponding star sensitive prism;
Acquiring third detection position information of the double-axis autocollimator about the corresponding beam splitter prism;
obtaining a first change angle according to the first initial position information and the first detection position information;
obtaining a second change angle according to the second initial position information and the second detection position information;
obtaining a third change angle according to the third initial position information and the third detection position information;
and removing the second change angle and the third change angle from the first change angle to obtain the angle deviation of the star sensor along with the temperature change.
Preferably, the angular deviation at a plurality of temperatures is obtained, and a quantitative relationship between the angular deviation and the temperature change is obtained.
The invention provides star sensor thermal stability detection equipment which comprises a vacuum tank and a plurality of supports arranged in the vacuum tank, wherein a temperature adjusting device is arranged in the vacuum tank, the front surface of each support is used for installing a star sensor, a star sensitive prism positioned on the side surface of the star sensor is arranged on the front surface of each support, a beam splitter prism is arranged on the back surface of each support, a reflector is arranged on the side surface of the beam splitter prism, a multi-star simulator, a single-shaft autocollimator and a double-shaft autocollimator which are positioned outside the vacuum tank are correspondingly arranged on each support, a plurality of glass windows are arranged on the vacuum tank, the star sensor is coaxial with the optical axis of the corresponding multi-star simulator through the glass windows, the star sensitive prism is coaxial with the optical axis of the corresponding single-shaft autocollimator through the glass windows, and the beam splitter prism is coaxial with the optical axis of the corresponding double-shaft autocollimator through the glass windows. Through a plurality of supports of inside setting, can carry out a plurality of star sensor's thermal stability simultaneously and detect, reduce cost improves detection efficiency.
The invention also provides a detection method using the device, and the detection method has the same technical effects as the device has the technical effects, so that the detection method is not described in detail herein.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of a star sensor thermal stability testing apparatus according to the present invention;
fig. 2 is a schematic diagram of a single star sensor according to an embodiment of the star sensor thermal stability testing apparatus of the present invention.
Detailed Description
The core of the invention is to provide the star sensor thermal stability detection equipment, which is internally provided with a plurality of supports, can simultaneously detect the thermal stability of a plurality of star sensors, reduces the cost and improves the detection efficiency. The other core of the invention is to provide a detection method applying the device.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic structural diagram of an embodiment of a star sensor thermal stability detecting apparatus according to the present invention; fig. 2 is a schematic diagram of a single star sensor according to an embodiment of the star sensor thermal stability testing apparatus of the present invention.
The invention provides star sensor thermal stability detection equipment which comprises a vacuum tank 1 and a plurality of supports 6 arranged in the vacuum tank 1, wherein a temperature adjusting device is arranged in the vacuum tank 1, rapid and accurate temperature control is realized, mounting interfaces are provided for all parts, each support 6 is provided with a front surface and a back surface, the front surface of each support 6 is used for mounting a star sensor 2, meanwhile, a star sensitive prism 7 is also arranged on the front surface of each support 6, the star sensitive prism 7 is positioned on the side surface of the star sensor 2, a beam splitter prism 8 is arranged on the back surface of each support 6, and a reflector 9 is arranged on the side surface of each beam splitter prism 8. The vacuum tank 1 is also provided with a plurality of multi-star simulators 3, a single-axis autocollimator 4 and a double-axis autocollimator 5 in corresponding quantities outside, and each support 6 is correspondingly provided with one multi-star simulator 3, one single-axis autocollimator 4 and one double-axis autocollimator 5. Meanwhile, in order to complete detection work and guarantee sealing effect, a plurality of glass windows 11 are arranged on the vacuum tank 1, the star sensor 2 is coaxial with the optical axis of the corresponding multi-star simulator 3 through the glass windows 11, the star sensor prism 7 is coaxial with the optical axis of the corresponding single-axis autocollimator 4 through the glass windows 11, and the beam splitter prism 8 is coaxial with the optical axis of the corresponding double-axis autocollimator 5 through the glass windows 11.
In the step 3, the multi-star simulator 3 is used as an observation target of the star sensor 2, can simulate constant star light from infinity, generates a static simulated star map with a large spatial scale, and generates an observation effect similar to a vacuum star space under laboratory conditions, so that the star sensor 2 can complete tasks such as star identification, attitude determination, polarity inspection and the like. Preferably, the static multi-star simulator 3 simulates stars by using tiny light-transmitting dots engraved on the optical reticle, and the light rays transmitted by the dots are collimated by the optical system to simulate the light of a star from infinity.
The uniaxial autocollimator 4 can realize high-precision measurement of the deflection angle of the reflecting mirror and the incident light and the deflection angle of the rotating shaft. The biaxial autocollimator 5 can simultaneously realize high-precision measurement of the deflection angle of two reflected lights generated by the beam splitter prism 8 and the deflection angle of the rotating shaft. The incidence surface of the beam splitter prism 8 is a transmission surface, the installation surface is a reflection surface, the middle surface is a semi-reflection and semi-transmission surface, and the emergence surface is a transmission surface.
In order to save space and simplify the structure, the corresponding single-axis autocollimators 4 are mounted on the sides of the corresponding multi-star simulator 3, close to each other, and aligned to the same glass window 11. Meanwhile, the corresponding star sensitive prism 7 and the star sensor 2 are close to each other, namely, the four components use one glass window 11, so that the equipment space is saved, and the corresponding mode can be adjusted according to the situation, which is within the protection scope of the invention.
Further, since each component is installed on the front and back sides of the bracket 6, two glass windows 11 are needed to be installed on each bracket 6 and aligned with the front and back sides of the same bracket 6, i.e. the glass windows 11 are opposite to each other and surround the side circumference of the vacuum tank 1. It is also possible to use one glass window with more components by increasing the size of the glass window 11.
A mounting frame 10 may be provided at a side of each bracket 6, and the reflecting mirror 9 is provided to the mounting frame 10. The support 6 is specifically a T-shaped frame, provides equipment strength, and each support 6 and relevant parts all adopt the lower invar steel material of coefficient of linear expansion, will the bearing structure's the temperature variation influence will be minimum. Or the shapes and the sizes of the components are adjusted according to the conditions, and the invention is within the protection scope.
On the basis of the star sensor thermal stability detection equipment provided by each specific embodiment, three supports 6 can be arranged, each support 6 is provided with one star sensor 2, and further three star sensitive prisms 7, a beam splitter prism 8, a reflector 9, a multi-star simulator 3, a single-axis autocollimator 4 and a double-axis autocollimator 5 are correspondingly arranged, and six glass windows are arranged on the vacuum tank 1. The three supports 6 are evenly distributed and clamped at 120 degrees with each other, while the back surfaces of the supports 6 face the center of the vacuum tank 1, i.e. the diameter of the circular section of the vacuum tank 1 is vertical and passes through the front and back surfaces of the supports 6, while the front surface of the supports 6 is closer to the inner wall of the vacuum tank 1. Correspondingly, six glass windows 11 are uniformly distributed, the included angle between the six glass windows is 60 degrees, the connecting line of two opposite glass windows 11 is the diameter of the circular section of the vacuum tank 1, the three supports 6 and parts mounted on the supports 6 are arranged on three diameters and are sequentially aligned with each star sensor 2 and the beam splitter prism 8, meanwhile, the three multi-star simulators 3 and the three double-shaft autocollimators 5 are alternately arranged and are sequentially aligned with the six glass windows 11, the three single-shaft autocollimators 4 are respectively close to the three multi-star simulators 3, and one glass window 11 is shared by the corresponding multi-star simulators 3. The number of the brackets 6 can be increased or decreased according to the situation, the number of the corresponding parts can be adjusted, and the parts can not interfere with each other, and the invention is within the protection scope.
The detection method specifically comprises the following steps: a plurality of star sensors 2 to be detected are arranged on the front face of each corresponding support 6, and the star sensors 2 are enabled to be coaxial with the optical axis of the corresponding multi-star simulator 3 through a glass window 11 according to the adjustment of the corresponding star sensitive prism 7, a beam splitter prism 8, a reflector 9, the multi-star simulator 3, the single-axis autocollimator 4 and the double-axis autocollimator 5, the star sensitive prism 7 is coaxial with the optical axis of the corresponding single-axis autocollimator 4 through the glass window 11, and the beam splitter prism 8 is coaxial with the optical axis of the corresponding double-axis autocollimator 5 through the glass window 11. And a vacuum environment is provided by the vacuum tank 1.
Acquiring first initial position information of the star sensor 2 about the corresponding multi-star simulator 3; acquiring second initial position information of the single-axis autocollimator 4 relative to the corresponding star sensitive prism 7; third initial position information of the biaxial autocollimator 5 with respect to the corresponding beam splitter prism 8 is acquired. Specifically, the star sensor 2 interacts with the static multi-star simulator 3, and the star sensor 2 receives light rays of a light source of the multi-star simulator 3 through the glass window 11, so as to obtain first initial position information. The light emitted by the single-axis autocollimator 4 reaches the star sensor prism 7 through the glass window 11 and returns to the single-axis autocollimator 4 through the star sensor prism 7, and then second initial position information is obtained. Light emitted by the double-axis autocollimator 5 reaches the beam splitter prism 8 through the glass window 11, one part of the light is reflected back to the double-axis autocollimator 5 through the mounting surface of the prism 8, the other part of the light is reflected to the reflector 9 on the side of the beam splitter prism 8, returns to the beam splitter prism 8 through the reflector 9 and finally returns to the double-axis autocollimator 5, two beams of light returned through the mounting surface of the beam splitter prism 8 and the reflector 9 form two light spots on the double-axis autocollimator 5 respectively, and further third initial position information is obtained.
Adjusting the temperature or the vacuum degree in the vacuum tank 1 according to the experiment requirement; then acquiring first detection position information of the star sensor 2 about the corresponding multi-star simulator 3; acquiring second detection position information of the single-axis autocollimator 4 relative to the corresponding star sensitive prism 7; third detection position information of the biaxial autocollimator 5 with respect to the corresponding beam splitter prism 8 is acquired. As described above, the position information of the sensor is necessarily changed due to the temperature change, and therefore the position information detected at both sides is different.
Further, a first change angle, that is, an angle change of the entire apparatus generated under a temperature change, is obtained from the first initial position information and the first detected position information. And obtaining a second change angle, namely the angle change of the front surface of the bracket 6 (the mounting surface of the star sensor 2) under the temperature change according to the second initial position information and the second detection position information. And obtaining a third change angle, namely the angle change of the bracket 6 under the temperature change according to the third initial position information and the third detection position information.
And removing the second detection angle and the third detection angle through the first detection angle to obtain the angle deviation of the star sensor 2 along with the temperature change. Namely, the integral angle change is formed by the angle change of the front surface of the bracket 6, the angle change of the bracket 6 and the angle deviation of the star sensor 2, and the real performance change of the star sensor 2 along with the temperature change under the vacuum condition is obtained by removing other influences.
Further, the angular deviation under a plurality of temperatures is obtained, and the quantitative relation between the angular deviation and the temperature change is obtained, so that the thermal stability detection of the star sensor 2 can be accurately completed. Through a plurality of supports 6 of inside setting, can carry out the heat stability of a plurality of star sensors 2 simultaneously and detect, reduce cost improves detection efficiency.
The star sensor thermal stability detection device and the detection method thereof provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (7)
1. The utility model provides a star sensor thermal stability check out test set, its characterized in that, including vacuum tank (1) with install in a plurality of supports (6) in vacuum tank (1), be provided with temperature regulation apparatus in vacuum tank (1), every the front of support (6) is used for installing star sensor (2), install in the front of support (6) and be located star sensitive prism (7) of star sensor (2) side, the back mounted of support (6) has beam splitter prism (8), beam splitter prism (8) side-mounting has speculum (9), every support (6) all correspond and are provided with and are located outside many stars simulator (3), unipolar autocollimator (4) and biax autocollimator (5) of vacuum tank (1), be provided with a plurality of glass windows (11) on vacuum tank (1), star sensor (2) are passed through glass window (11) with the correspondence the optical axis of many stars simulator (3) The star sensitive prism (7) is coaxial with the optical axis of the corresponding single-axis autocollimator (4) through the glass window (11), and the beam splitter prism (8) is coaxial with the optical axis of the corresponding double-axis autocollimator (5) through the glass window (11);
Including three evenly distributed support (6), the back of support (6) all faces the center of vacuum tank (1), be provided with evenly distributed six on vacuum tank (1) glass window (11), three many stars simulator (3) and three biax autocollimator (5) set up in turn.
2. The star sensor thermal stability inspection device according to claim 1, wherein the single-axis autocollimator (4) is mounted on the corresponding side of the multi-star simulator (3) and aligned with the same glass window (11).
3. The star sensor thermal stability detection device according to claim 2, characterized in that the plurality of glass windows (11) are opposite to each other in pairs, and the two opposite glass windows (11) are respectively aligned with the front surface and the back surface of the same support (6).
4. The star sensor thermal stability detection device according to claim 3, wherein each support (6) is provided with a mounting frame (10) at the side, and the reflector (9) is arranged on the mounting frame (10).
5. The star sensor thermal stability detection device according to claim 1, characterized in that the support (6) is embodied as a T-shaped frame.
6. A detection method of star sensor thermal stability detection equipment is characterized by comprising the following steps:
A plurality of star sensors (2) to be detected are arranged on the front surface of each corresponding bracket (6);
acquiring first initial position information of the star sensor (2) about a corresponding multi-star simulator (3);
acquiring second initial position information of the single-axis autocollimator (4) about the corresponding star sensitive prism (7);
acquiring third initial position information of the biaxial autocollimator (5) about the corresponding beam splitter prism (8);
adjusting the temperature or the vacuum degree in the vacuum tank (1);
acquiring first detection position information of the star sensor (2) about the corresponding multi-star simulator (3);
acquiring second detection position information of the single-axis autocollimator (4) about the corresponding star sensitive prism (7);
acquiring third detection position information of the biaxial autocollimator (5) about the corresponding beam splitter prism (8);
obtaining a first change angle according to the first initial position information and the first detection position information;
obtaining a second change angle according to the second initial position information and the second detection position information;
obtaining a third change angle according to the third initial position information and the third detection position information;
and removing the second change angle and the third change angle from the first change angle to obtain the angle deviation of the star sensor (2) along with the temperature change.
7. The method for detecting the thermal stability of the star sensor according to claim 6, wherein the angular deviation at a plurality of temperatures is obtained, and a quantitative relationship between the angular deviation and the temperature variation is obtained.
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| CN106184821A (en) * | 2016-08-12 | 2016-12-07 | 上海卫星工程研究所 | The remote sensing instrument of a kind of high precision high stability configuration integrated with star sensor |
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| CN109186588A (en) * | 2018-10-10 | 2019-01-11 | 上海航天控制技术研究所 | A kind of miniature multimode star sensor |
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| US8640994B1 (en) * | 2010-09-27 | 2014-02-04 | The Boeing Company | Agile dedicated spacecraft for spinning microwave imagers and sounders |
| CN102564458B (en) * | 2011-12-29 | 2014-07-02 | 北京控制工程研究所 | Low-frequency error measuring method for star sensor |
| CN106568462A (en) * | 2016-10-28 | 2017-04-19 | 北京控制工程研究所 | Multi-probe star sensor fusion attitude testing method |
| CN108759821A (en) * | 2018-06-14 | 2018-11-06 | 上海卫星工程研究所 | A kind of multiple star sensor configurations of GEO satellite |
| CN109655079B (en) * | 2018-12-12 | 2021-08-06 | 上海航天控制技术研究所 | Method for measuring coordinate system from star sensor to prism coordinate system |
| CN110345970B (en) * | 2019-08-06 | 2024-03-19 | 西安中科微星光电科技有限公司 | Optical navigation sensor calibration method and device thereof |
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| CN106184821A (en) * | 2016-08-12 | 2016-12-07 | 上海卫星工程研究所 | The remote sensing instrument of a kind of high precision high stability configuration integrated with star sensor |
| CN108759869A (en) * | 2018-06-20 | 2018-11-06 | 上海卫星工程研究所 | Rotating Platform for High Precision Star Sensor holder heat distortion test system |
| CN109186588A (en) * | 2018-10-10 | 2019-01-11 | 上海航天控制技术研究所 | A kind of miniature multimode star sensor |
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