CN109141472B - Star observation testing device and method for evaluating thermal stability of star sensor - Google Patents
Star observation testing device and method for evaluating thermal stability of star sensor Download PDFInfo
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- CN109141472B CN109141472B CN201810916247.6A CN201810916247A CN109141472B CN 109141472 B CN109141472 B CN 109141472B CN 201810916247 A CN201810916247 A CN 201810916247A CN 109141472 B CN109141472 B CN 109141472B
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Abstract
The invention relates to a star observation testing device for evaluating the thermal stability of a star sensor, which comprises: the integrated support is of an axisymmetric structure, normal included angles between every two of a plurality of mounting surfaces on the integrated support are equal, and the same star sensor is correspondingly arranged on each mounting surface; the precise temperature control instrument comprises an electric heating sheet and a thermistor, and is adhered to the outer side surface and the bottom surface mounting surface of each star sensor light shield for temperature acquisition and closed-loop control; the windproof protective cover covers the outside of the integrated bracket provided with the plurality of star sensors and is arranged on the outfield star observation test platform; and the test industrial personal computer is arranged at intervals with the integrated support and is connected with each star sensor through a cable. The invention also provides a star observation test method for evaluating the thermal stability of the star sensor. The invention provides an accurate and effective quantitative evaluation method for the thermal stability of the star sensor by the technical means of common installation reference, active temperature control, heat insulation, wind prevention and the like and by utilizing the characteristic of consistent thermal stability characteristics of the same star sensor.
Description
Technical Field
The invention relates to a device and a method for evaluating the thermal stability of a star sensor, in particular to a star observation testing device and a method for evaluating the thermal stability of the star sensor, and belongs to the technical field of ground tests of space photoelectric sensors.
Background
The star sensor is a high-precision spacecraft attitude measurement single machine, takes a fixed star as a detection target, and outputs three-axis attitude information after being processed by an internal optical system, an electronic component and software. Due to the influence of external heat flow and deep cooling space background, the temperature field of the star sensor generally shows fluctuation of the orbit period, and low-frequency errors of the orbit period are generated due to thermal deformation. The temperature of the mounting surface of the star sensor is generally used as a reference temperature to measure the variation of the temperature along with the temperature of the mounting surface, and the thermal stability of the star sensor is evaluated. Meanwhile, the temperature fluctuation range of the star sensor light shield is considered to be large, and the influence of the temperature of the light shield on the thermal stability of the star sensor needs to be considered additionally.
In the prior art, the research on the thermal stability of the star sensor focuses on temperature control, namely a series of thermal control means are adopted, so that the fluctuation range of the temperature is reduced, and the thermal deformation is inhibited. However, direct evaluation of thermal stability is less studied, and a thermal stability measurement system for mature application is not available at home at present.
Currently, there are two methods for evaluating thermal stability that can be used for reference: one is to measure the deformation of the structure in a temperature-varying environment by means of other optical measuring instruments, such as autocollimators, cube mirrors, etc. The disadvantage of this method is that the deformation of the structure is not equivalent to a change in the measurement results of the optical measuring instrument. The other method is to use the star sensor on-orbit data to analyze the low-frequency error in the orbit period, but the influence of the satellite platform stability and other installation structure thermal deformation cannot be stripped in the process. Therefore, the two methods cannot directly and effectively evaluate the thermal stability of the star sensor.
Based on the above, the invention provides a star observation testing device and method for evaluating the thermal stability of a star sensor, thereby solving the defects and limitations in the prior art.
Disclosure of Invention
The invention aims to provide a star observation testing device and method for evaluating the thermal stability of a star sensor, which provide an accurate and effective method for quantitatively evaluating the thermal stability of the star sensor by means of common installation reference, active temperature control, heat insulation, wind prevention and other technical means and by utilizing the characteristic that the thermal stability characteristics of the same star sensor are consistent.
In order to achieve the above object, the present invention provides a star observation testing apparatus for evaluating thermal stability of a star sensor, comprising: the integrated support is of an axisymmetric structure, a plurality of mounting surfaces are arranged on the integrated support, the normal included angles between every two mounting surfaces are equal, and a plurality of same star sensors are correspondingly arranged on each mounting surface; the precise temperature controller comprises a plurality of electric heating sheets and a plurality of thermistors, and is adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor to perform temperature acquisition and closed-loop control on the star sensor; the windproof protective cover covers the outside of the integrated bracket provided with the plurality of star sensors and is arranged on the outfield star observation test platform; and the test industrial personal computer is arranged at a distance from the integrated support provided with the plurality of star sensors and is connected with each star sensor through a cable.
Preferably, the normal included angle between every two installation surfaces on the integrated support is 0-60 degrees.
Preferably, the integrated bracket is made of invar steel, and the linear expansion coefficient of the integrated bracket is less than 1 × 10-7/℃。
Preferably, each mounting surface on the integrated bracket is provided with a preformed groove.
Preferably, the precision temperature controller further comprises: the temperature control instrument host is arranged at a distance from the integrated bracket provided with the plurality of star sensors; the plurality of electric heating pieces are respectively adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor, and each electric heating piece is connected with the temperature control instrument host through a cable; the plurality of thermistors are respectively adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor and are positioned on one side of each electric heating sheet, and each thermistor is connected with the temperature control instrument host through a cable.
Preferably, the electric heating sheet is adhered to the outer side surface of the light shield of each star sensor, and the adhering area of the electric heating sheet does not exceed 1/2 of the circumferential area; and the sticking positions of the electric heating sheets and the thermistors on the outer side surface of the light shield of each star sensor are the same, and the resistance value deviation of each electric heating sheet positioned at the same position is not more than 1%.
Preferably, the electric heating plates adhered to the bottom surface mounting surfaces of the star sensors are correspondingly arranged in the preformed grooves of the integrated bracket, and the star sensors are correspondingly arranged on the mounting surfaces of the integrated bracket.
Preferably, the heat insulating multilayer assembly is coated and arranged on the outer side surface of the light shield of each star sensor to which the plurality of electric heating sheets are attached.
The windproof protective cover is made of transparent organic glass; the top surface of the windproof protective cover is preset with observation holes according to the size of a view field of the star sensor.
The invention also provides a star observation test method for evaluating the thermal stability of the star sensor, which is realized by adopting the star observation test device and specifically comprises the following steps:
s1, after the star observation testing device and the star sensor to be tested are installed, the star sensor is powered on until the star sensor enters a stable tracking state, and attitude quaternion data are output based on a real star sky;
s2, setting a first target temperature of the bottom surface mounting surface of the star sensor;
s3, controlling the temperature of each star sensor to reach a first target temperature through a precision temperature controller in a closed loop mode and stabilizing, collecting attitude quaternion data output by each star sensor for not less than 10min by using a test industrial personal computer, and calculating the optical axis pointing included angle between every two star sensors;
s4, adjusting a second target temperature of the bottom mounting surface of the star sensor, and repeatedly executing S3 to evaluate the thermal stability of the star sensor according to the ratio of the angle variation pointed by the optical axis to the temperature variation of the bottom mounting surface;
s5, keeping a second target temperature of the bottom surface mounting surface of the star sensor, setting different target temperatures of the light shield of the star sensor, controlling the temperature of each star sensor to reach the target temperature of the corresponding light shield through a precise temperature controller in a closed loop manner, and after the temperature of each star sensor is stable, collecting attitude quaternion data output by each star sensor for not less than 10min by using a testing industrial personal computer, and calculating the optical axis pointing included angle between every two star sensors at the corresponding target temperature; and evaluating the influence of the temperature change of the light shield on the thermal stability of the star sensor by using the ratio of the angle change pointed by the optical axis to the temperature change of the light shield.
In summary, the star observation test device and method for evaluating the thermal stability of the star sensor provided by the invention have the advantages that the influence of the environmental temperature and the wind load on the measurement result can be ignored through the design of the integrated bracket (micro thermal deformation and common installation reference), the heat insulation multilayer component and the wind-proof protective cover; meanwhile, the characteristic that the thermal stability characteristics of all sub-samples of the same star sensor are consistent is utilized, the active closed-loop temperature control of all the star sensors is realized through a precise temperature controller, and the thermal stability of the star sensors is accurately and effectively evaluated by combining the change relation of the optical axis pointing included angle along with the temperature.
Drawings
FIG. 1 is a schematic structural diagram of a star observation testing device for evaluating the thermal stability of a star sensor according to the present invention;
FIGS. 2a and 2b are schematic views illustrating the attachment positions of the electric heating sheet and the thermistor according to the present invention;
fig. 3 is a schematic structural view of the integrated stent of the present invention.
Detailed Description
The technical contents, construction features, achieved objects and effects of the present invention will be described in detail by preferred embodiments with reference to fig. 1 to 3.
As shown in fig. 1, the star observation testing apparatus for evaluating the thermal stability of a star sensor provided by the present invention comprises: the integrated support 1 is of an axisymmetric structure, a plurality of mounting surfaces are arranged on the integrated support, normal included angles between every two mounting surfaces are equal, and a plurality of same star sensors 6 are correspondingly arranged on each mounting surface; the precise temperature controller 2 comprises a plurality of electric heating sheets 21 and a plurality of thermistors 22, and is stuck on the outer side surface and the bottom surface mounting surface of the light shield of each star sensor 6 to carry out temperature acquisition and closed-loop control on the star sensor; the windproof protective cover 4 covers the outside of the integrated bracket 1 provided with the plurality of star sensors 6 and is arranged on an outfield star observation test platform; and the test industrial personal computer is arranged at a certain distance from the integrated support 1 provided with the plurality of star sensors 6 and is connected with each star sensor 6 through a cable.
The normal included angle between every two installation surfaces on the integrated support 1 is 0-60 degrees.
The integrated bracket 1 is made of invar steel, and the linear expansion coefficient of the integrated bracket 1 is less than 1 × 10-7V. C, star ofThe opto-mechanical structure material of the sensor is two orders of magnitude lower, so that the influence of the thermal deformation of the integrated bracket 1 on the test result can be ignored.
As shown in fig. 3, each mounting surface of the integrated bracket 1 is provided with a pre-groove 11 for avoiding the electric heater and the thermistor adhered to the mounting surface of the optical probe.
In a preferred embodiment of the present invention, the integrated bracket 1 is provided with 3 mounting surfaces, and the normal included angle between every two mounting surfaces is 60 °. Each mounting surface is provided with a reserved groove 11 for correspondingly mounting 3 same star sensors 6 respectively.
As shown in fig. 2a and 2b, the precision temperature controller 2 further comprises: the temperature control instrument host is arranged at a distance from the integrated bracket 1 provided with the plurality of star sensors 6; the plurality of electric heating sheets 21 are thin film type electric heating sheets and are respectively adhered to the outer side surface and the bottom surface installation surface of the light shield of each star sensor 6, and each electric heating sheet 21 is connected with the temperature control instrument host through a cable; the thermistors 22 are respectively adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor 6 and are positioned at one side of each electric heating sheet 21, and each thermistor 22 is connected with a temperature control instrument host through a cable.
Wherein, the electric heating plate 21 pasted on the outer side surface of the light shield of each star sensor 6 has the pasting area not exceeding 1/2 of the circumference area; moreover, the sticking positions of the electric heating plates 21 and the thermistors 22 on the outer side surface of the light shield of each star sensor 6 are the same, and the resistance value deviation of each electric heating plate 21 positioned at the same position is not more than 1%.
In a preferred embodiment of the present invention, as shown in fig. 2a, 3 electric heating plates 21 are respectively provided at the same positions on the outer side surface of the light shield of each star sensor 6, and the adhering area of each electric heating plate does not exceed 1/2 of the circumferential area, and the deviation of the resistance value between the electric heating plates 21 respectively located at the same positions on different star sensors 6 is not more than 1%. Meanwhile, a thermistor 22 is also adhesively provided on one side of each electric heating piece 21. As shown in fig. 2b, 1 electric heating plate 21 is provided on the bottom surface mounting surface of each star sensor 6, and a thermistor 22 is also adhesively provided on one side of the electric heating plate 21.
As shown in fig. 1, the respective star sensors 6 are correspondingly arranged on the respective mounting surfaces of the integrated holder 1 by correspondingly arranging the electric heating strips 21 adhered to the mounting surfaces of the bottom surfaces of the respective star sensors 6 in the prepared grooves 11 of the integrated holder 1.
Further, the outer side surface of the light shield of each star sensor 6 to which the plurality of electric heating plates 21 are attached is covered with the heat insulating multilayer assembly 3, respectively, to reduce heat exchange with the external environment.
The windproof protective cover 4 is made of transparent organic glass and is packaged in a cuboid box; cable threading holes are preset in the side face of the windproof protective cover 4, so that each star sensor 6 can be connected with a test industrial personal computer through a cable, and each electric heating piece 21 and each thermistor 22 can be connected with a temperature control instrument host through cables; the top surface is preset with observation holes according to the size of the view field of the star sensor 6, so that the view field of the star sensor 6 is not shielded. According to the invention, the wind-proof protective cover 4 is arranged to avoid the influence of wind load in an external field environment on the heat stability test of the star sensor.
In summary, in the invention, each star sensor 6 to be tested, the integrated support 1, the electric heating sheet 21, the thermistor 22, the heat-insulating multilayer component 3 and the windproof protective cover 4 are arranged on the outer field star observation platform; but the test industrial personal computer and the temperature control instrument host are arranged at proper distance from the components and connected through cables.
The invention also provides a star observation test method for evaluating the thermal stability of the star sensors, which is realized by adopting the star observation test device, synchronously deviates the temperature of each star sensor 6 through the precise temperature controller 2, evaluates the thermal stability of the star sensors 6 based on an optical axis included angle method and specifically comprises the following steps:
s1, after the star observation testing device and the star sensor 6 to be tested are installed, the star sensor 6 is powered on until entering a stable tracking state, and attitude quaternion data are output based on a real star sky;
s2, setting a first target temperature of the bottom surface mounting surface of the star sensor 6;
s3, controlling the temperature of each star sensor 6 to reach a first target temperature through the precision temperature controller 2 in a closed loop mode, and after the temperature is stable, collecting attitude quaternion data output by each star sensor 6 for not less than 10min (minutes) by using a test industrial personal computer, and calculating the optical axis pointing included angle between every two star sensors 6;
s4, adjusting and setting a second target temperature of the bottom mounting surface of the star sensor 6, repeatedly executing S3, and evaluating the thermal stability of the star sensor 6 according to the ratio of the angle variation of the optical axis direction to the temperature variation of the bottom mounting surface;
s5, keeping a second target temperature of the bottom surface mounting surface of the star sensor 6, setting different target temperatures of the light shield of the star sensor 6, controlling the temperature of each star sensor 6 to reach a corresponding target temperature through a closed loop of the precise temperature controller 2 and stabilizing, collecting attitude quaternion data output by each star sensor 6 for not less than 10min by using a testing industrial personal computer, and calculating an optical axis pointing included angle between every two star sensors 6 at the corresponding target temperature; and evaluating the influence of the temperature change of the light shield on the thermal stability of the star sensor 6 by the ratio of the angle change pointed by the optical axis to the temperature change of the light shield.
The star observation test device and method for evaluating the thermal stability of the star sensor according to the present invention are described in detail below with reference to fig. 1 to 3.
And S1, mounting the star observation testing device and the star sensor 6 to be tested, electrifying the star sensor 6 until the star sensor enters a stable tracking state, and outputting attitude quaternion data based on the real starry sky.
Wherein, the concrete installation process does: adhering thin film type electric heating sheets 21 of the precise temperature control instrument 2 to the outer side surfaces of the same positions on the light shields of the star sensors 6, wherein the coverage area of the electric heating sheets 21 is not more than 1/2 of the circumference area, adhering a thermistor 22 to one side of each electric heating sheet 21, and then coating the heat-insulating multilayer component 3 on the outer side of the star sensors 6;
an electric heating sheet 21 and a thermistor 22 are adhered to the bottom surface installation surface of each star sensor 6, and the adhering positions of the electric heating sheet 21 and the thermistor 22 do not exceed the area of the preformed groove 11 on the integrated bracket 1;
correspondingly installing 3 sub-samples A, B and C of the star sensor on the integrated support 1, placing the integrated support on an outfield star observation test platform, covering the windproof protective cover 4, and enabling the cable to penetrate through a cable threading hole in the side surface of the windproof protective cover 4 and be connected with a temperature control instrument host and a test industrial personal computer which are arranged at intervals respectively.
S2, taking the environment temperature of 10 ℃ as an example, the first target temperature of the bottom surface mounting surface of the star sensor 6 is set to 15 ℃.
S3, starting the precision temperature controller 2, controlling the heating of the electric heating sheet 21, controlling the temperature of each star sensor 6 to reach 15 ℃ in a closed loop mode, regarding the temperature to reach stability when the temperature change collected by each thermistor 22 is less than 0.5 ℃ within 1 hour, collecting attitude quaternion data output by each star sensor 6 for not less than 10min by using the test industrial personal computer, and calculating the optical axis pointing included angle between every two star sensors 6 based on the attitude quaternion.
Wherein, the specific heating process is as follows: the current temperature is collected by each thermistor 22 and transmitted to the temperature controller host, and if the current temperature does not reach the target temperature, the temperature controller host continues to supply power to each electric heating sheet 21 for heating until the target temperature is reached, and then the same closed-loop control is adopted to stabilize the temperature.
The process of specifically calculating the optical axis pointing included angle is as follows:
the quaternion data of each star sensor 6 adopts the same time reference, and the quaternion sequence with equal time intervals of the star sensor subsample A in the test period is set as
The quaternion sequence of the star sensor subsample B with equal time intervals is
The time interval is the sampling period T of the attitude measurement informationc. For star sensor subsampleA and each time point t of the star sensor subsample BiQuaternion of (2)
And
its optical axis vector vAAnd vBAre respectively represented by the following formula:
therefore, the optical axis orientation angle of the star sensor subsample A and the star sensor subsample B is shown as follows:
further obtaining: sAB＝{(ti,αi) And i is 1,2, so as to obtain the mean value of the optical axis pointing included angles of the star sensor subsample A and the star sensor subsample B
According to the above, the mean value of the optical axis pointing angles of the star sensor subsample A and the star sensor subsample C can be obtained in the same way
And the mean value of the optical axis pointing included angles of the star sensor subsample B and the star sensor subsample C
S4, adjusting the second target temperature of the bottom surface mounting surface of the star sensor 6 to 25 ℃, and repeating the step S3, namely starting the precision temperature controller 2 and controlling the electric heating sheet21, controlling the temperature of each star sensor 6 to reach 25 ℃ in a closed loop manner, regarding the temperature as reaching stability when the temperature change collected by each thermistor 22 is less than 0.5 ℃ within 1 hour, collecting attitude quaternion data output by each star sensor 6 for not less than 10min by using a test industrial personal computer, and calculating the mean value of optical axis pointing included angles between every two star sensors 6 based on the attitude quaternion
And
then, the thermal stability TS of the star sensor 6 is evaluated as the ratio of the amount of change in the angle to which the optical axis points to the amount of change in the temperature of the bottom-surface mounting surface:
wherein, the thermal stability TS refers to the angle variation of optical axis pointing caused by unit temperature variation; the part before the symbol "/" in the formula represents the optical axis pointing variation of a single star sensor 6 obtained by averaging the changes of the included angles between every two star sensors, and the unit of the variation is an angle; the 25 ℃ to 15 ℃ is the amount of change in the target temperature.
S5, keeping the temperature of the bottom surface mounting surface of the star sensor 6 at 25 ℃, setting different target temperatures of the light shield of the star sensor 6, and evaluating the influence of the temperature change of the light shield on the thermal stability of the star sensor 6 by adopting the same method of S3 and S4. Namely, after the temperature of each star sensor 6 is controlled to reach the target temperature of the corresponding light shield and is stable through the precision temperature controller 2 in a closed loop mode, the test industrial personal computer collects attitude quaternion data output by each star sensor 6 for not less than 10min, and the optical axis pointing included angle between every two star sensors 6 at the corresponding target temperature is calculated; and evaluating the influence of the temperature change of the light shield on the thermal stability of the star sensor 6 by the ratio of the angle change pointed by the optical axis to the temperature change of the light shield.
In summary, the star observation testing device and method for evaluating the thermal stability of the star sensor provided by the invention can effectively evaluate the thermal stability of the star sensor by actively controlling the temperature field of the star sensor in the process of observing the star in the field, utilizing the characteristic that the thermal stability characteristics of all subsamples of the same star sensor are basically consistent and adopting the optical axis included angle method.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. through the design of the integrated bracket (micro thermal deformation and common installation reference), the heat insulation multilayer assembly and the windproof protective cover, the influence of the environmental temperature and the wind load on the measurement result can be ignored;
2. by utilizing the characteristic that the thermal stability characteristics of all sub-samples of the same star sensor are consistent, the precise temperature controller is used for actively controlling the closed-loop temperature of all the star sensors, and the thermal stability of the star sensors is accurately and effectively evaluated by combining the change relation of the optical axis pointing included angle with the temperature.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (9)
1. A star observation test method for evaluating the thermal stability of a star sensor is characterized by being realized by adopting a star observation test device; wherein the content of the first and second substances,
the star observation testing device comprises:
the integrated support is of an axisymmetric structure, a plurality of mounting surfaces are arranged on the integrated support, the normal included angles between every two mounting surfaces are equal, and a plurality of same star sensors are correspondingly arranged on each mounting surface;
the precise temperature controller comprises a plurality of electric heating sheets and a plurality of thermistors, and is adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor to perform temperature acquisition and closed-loop control on the star sensor;
the windproof protective cover covers the outside of the integrated bracket provided with the plurality of star sensors and is arranged on the outfield star observation test platform;
the testing industrial personal computer is arranged at a distance from the integrated support provided with the plurality of star sensors and is connected with each star sensor through a cable;
the star observation test method comprises the following steps:
s1, after the star observation testing device and the star sensor to be tested are installed, the star sensor is powered on until the star sensor enters a stable tracking state, and attitude quaternion data are output based on a real star sky;
s2, setting a first target temperature of the bottom surface mounting surface of the star sensor;
s3, controlling the temperature of each star sensor to reach a first target temperature through a precision temperature controller in a closed loop mode and stabilizing, collecting attitude quaternion data output by each star sensor for not less than 10min by using a test industrial personal computer, and calculating the optical axis pointing included angle between every two star sensors;
s4, adjusting a second target temperature of the bottom mounting surface of the star sensor, and repeatedly executing S3 to evaluate the thermal stability of the star sensor according to the ratio of the angle variation pointed by the optical axis to the temperature variation of the bottom mounting surface;
s5, keeping a second target temperature of the bottom surface mounting surface of the star sensor, setting different target temperatures of the light shield of the star sensor, controlling the temperature of each star sensor to reach the target temperature of the corresponding light shield through a precise temperature controller in a closed loop manner, and after the temperature of each star sensor is stable, collecting attitude quaternion data output by each star sensor for not less than 10min by using a testing industrial personal computer, and calculating the optical axis pointing included angle between every two star sensors at the corresponding target temperature; and evaluating the influence of the temperature change of the light shield on the thermal stability of the star sensor by using the ratio of the angle change pointed by the optical axis to the temperature change of the light shield.
2. The star observation and testing method for evaluating the thermal stability of the star sensor as claimed in claim 1, wherein the normal angle between every two mounting surfaces of the one-piece holder is 0-60 °.
3. The star-observation test method for evaluating the thermal stability of a star sensor as claimed in claim 1, wherein the one-piece frame is made of invar with a linear expansion coefficient less than 1 × 10-7/℃。
4. The star observation test method for evaluating the thermal stability of the star sensor as claimed in claim 1, wherein a pre-groove is provided on each mounting surface of the one-piece carrier.
5. The star observation test method for evaluating the thermal stability of a star sensor as claimed in claim 4, wherein said precise temperature controller further comprises: the temperature control instrument host is arranged at a distance from the integrated bracket provided with the plurality of star sensors;
the plurality of electric heating pieces are respectively adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor, and each electric heating piece is connected with the temperature control instrument host through a cable;
the plurality of thermistors are respectively adhered to the outer side surface and the bottom surface mounting surface of the light shield of each star sensor and are positioned on one side of each electric heating sheet, and each thermistor is connected with the temperature control instrument host through a cable.
6. The star observation test method for evaluating the thermal stability of the star sensors as claimed in claim 5, wherein the electric heating plate attached to the outer side surface of the light shield of each star sensor has an attachment area not exceeding 1/2 of the circumferential area;
the sticking positions of the electric heating sheets and the thermistors on the outer side surface of the light shield of each star sensor are the same, and the resistance value deviation of each electric heating sheet positioned at the same position is not more than 1%.
7. The sight-star test method for evaluating the thermal stability of the star sensors as claimed in claim 5, wherein the star sensors are disposed on the respective mounting surfaces of the one-piece holder by disposing the electric heating plates attached to the respective mounting surfaces of the star sensors in the respective prepared grooves of the one-piece holder.
8. The star observation test method for evaluating the thermal stability of the star sensors as claimed in claim 5, wherein the heat insulating multi-layer members are respectively coated on the outer side surface of the light shield of each of the star sensors to which the plurality of electric heating sheets are attached.
9. The star observation test method for evaluating the thermal stability of a star sensor as claimed in claim 1, wherein said windbreak protective cover is made of transparent organic glass; the top surface of the windproof protective cover is preset with observation holes according to the size of a view field of the star sensor.
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| CN111323210B (en) * | 2020-03-17 | 2021-07-09 | 北京控制工程研究所 | Device and method for testing optical axis thermal stability of optical lens |
| CN111323052A (en) * | 2020-03-20 | 2020-06-23 | 上海航天控制技术研究所 | Navigation sensor heat balance test device used in complex thermal environment |
| CN111649765A (en) * | 2020-06-18 | 2020-09-11 | 西安中科微星光电科技有限公司 | Thermal vacuum test device for star sensor performance test |
| CN111811540B (en) * | 2020-07-17 | 2022-06-24 | 上海航天控制技术研究所 | Star sensor optical axis thermal stability testing system and method |
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