CN117129016B - Ground calibration system and method for satellite payload full-range line-of-sight determination - Google Patents
Ground calibration system and method for satellite payload full-range line-of-sight determination Download PDFInfo
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- CN117129016B CN117129016B CN202311391626.5A CN202311391626A CN117129016B CN 117129016 B CN117129016 B CN 117129016B CN 202311391626 A CN202311391626 A CN 202311391626A CN 117129016 B CN117129016 B CN 117129016B
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Classifications
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- G—PHYSICS
- 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
Abstract
The invention relates to a calibration system and a method of a device, in particular to a ground calibration system and a method for determining the full-range line of sight of a satellite payload, which are used for solving the defects that the prior art is influenced by the installation position, orientation and attitude deviation of the satellite payload in ground test equipment, ground test environment and misoperation of an operator, and the high-precision ground calibration cannot be performed on the determination precision of the line of sight of the satellite payload. The ground calibration system for determining the full-range line of sight of the satellite payload adopts the scheme of single-axis azimuth rotation and pitching fixed angle measurement, so that the motion assembly is reduced as much as possible while the large-range measurement is met, various calibration errors in the ground calibration process are eliminated through the active thermoelastic simulation system and the one-dimensional turntable, the calibration precision is improved, and powerful support can be provided for high-precision tracking and measurement of the satellite.
Description
Technical Field
The invention relates to a calibration system and a method of a device, in particular to a ground calibration system and a method for determining the full-range line of sight of a satellite payload.
Background
Satellite payload line-of-sight determination accuracy refers to the error between the line-of-sight direction and angle and the actual direction and angle of a target or location measured by an optical, radar or other sensor on the satellite, which is an important indicator for measuring the accuracy of satellite payload measurements, particularly for applications requiring high accuracy positioning, imaging or measurement. The unit of accuracy of the line of sight determination is typically an angle (e.g., radians or angles). The accuracy of line-of-sight determination is affected by a variety of factors including instrument performance, environmental conditions, data processing methods, and viewing conditions. To ensure that the satellite payload can provide accurate measurements in a practical task, calibration and evaluation are required to verify that the line-of-sight determination accuracy meets the expected requirements.
Ground calibration with the accuracy of line-of-sight determination requires the use of a target simulator to simulate a starry sky background and a measured target, the measured target position observed by a satellite payload is compared with the measured target position simulated by the target simulator, and the deviation between the two is calculated. However, the method is easily affected by various factors, and cannot perform high-precision ground calibration on satellite payload line-of-sight determination precision. The main factors influencing the ground calibration accuracy include the following aspects:
(1) The satellite payload installation position, orientation and attitude bias in the ground test equipment may lead to differences between actual observed data and simulated data;
(2) Factors such as atmospheric conditions, temperature, humidity, etc. in the ground test environment can affect satellite payload and target simulator performance;
(3) Operator error may cause calibration deviations.
Disclosure of Invention
The invention aims to solve the defect that the prior art cannot perform high-precision ground calibration on the satellite payload sight line determination precision due to the influence of the installation position, orientation and attitude deviation of a satellite payload in ground test equipment, ground test environment and misoperation of an operator, and provides a ground calibration system and method for satellite payload full-range sight line determination.
In order to solve the defects existing in the prior art, the invention provides the following technical solutions:
the ground calibration system for determining the full-range line of sight of the satellite effective load comprises a two-dimensional turntable and the satellite effective load arranged on the two-dimensional turntable, wherein the two-dimensional turntable is used for realizing the full-range rotation of the visual axis of the satellite effective load through azimuth and pitching motions; the special feature is that: the system comprises an active thermoelastic simulation system, a one-dimensional turntable and a target simulation system;
the active thermoelastic simulation system is used for eliminating calibration errors caused by thermal strain by detecting and adjusting the temperature of the system to be calibrated;
the one-dimensional turntable comprises a corner calibration assembly, a base, a first automatic leveling mechanism, a turntable body and a second automatic leveling mechanism which are sequentially arranged from bottom to top; the turntable body comprises a turntable rotor and a turntable stator which are coaxially arranged; the corner calibration assembly comprises an auto-collimator and a plurality of reference frames; the auto-collimator is arranged on the turntable rotor and synchronously rotates along with the turntable rotor, the circumferences of the reference lens frames are uniformly arranged on the base, and each reference lens frame is provided with a reference lens which is aligned with the optical axis of the auto-collimator and is used for sub-second calibration of the actual rotation angle of the turntable rotor so as to realize the measurement of the rotation angle of the turntable rotor; the second automatic leveling mechanism is provided with the two-dimensional turntable through a turntable mounting plate, and the turntable mounting plate is used for providing a mounting reference for the two-dimensional turntable;
the target simulation system comprises a simulator bracket, an upper computer and a plurality of target simulators; the target simulators are arranged on the simulator support and are connected with the upper computer and used for simulating the starry sky background and the measured target.
Further, the active thermoelastic simulation system comprises an active thermal control system, a thermal strain test system and a software terminal; the thermal strain testing system is arranged on the two-dimensional turntable and the satellite payload, and the output end of the thermal strain testing system is connected with the input end of the software terminal;
the thermal strain testing system comprises a data collector, a strain sensor and a temperature compensation circuit, wherein the strain sensor and the temperature compensation circuit are arranged on the system to be calibrated; the strain sensor is used for measuring the actual thermal strain of the two-dimensional turntable and the satellite payload and outputting the actual thermal strain to the data acquisition device; the temperature compensation circuit is used for measuring the ambient temperature near the strain sensor and outputting the expected thermal strain of the two-dimensional turntable and the satellite payload to the data acquisition device according to the ambient temperature and a preset calibration curve; the data acquisition device is used for correcting the actual thermal strain according to the expected thermal strain and outputting corrected thermal strain to the software terminal;
the active thermal control system comprises a temperature controller connected with a software terminal, and a thermistor and a heating plate connected with the temperature controller; the software terminal is used for obtaining a target value of the temperature of the system to be calibrated according to the corrected thermal strain and outputting the target value to the temperature controller; the temperature controller is used for calculating the current value of the temperature of the system to be calibrated by measuring the resistance value of the thermistor, comparing the difference value between the current value and the target value, and adjusting the temperature of the system to be calibrated by controlling the current of the heating plate.
Further, the turntable body further comprises a turntable angle measurement coded disc, a turntable motor and an angular contact ball bearing; the rotary table rotor comprises a rotary platform and an axial convex ring arranged on the bottom surface of the rotary platform, and the auto-collimator is arranged on the rotary platform; the turntable stator comprises a stator shaft, the stator shaft is arranged in the axial convex ring, and an annular cavity is formed by the side wall of the stator shaft and the inner wall of the axial convex ring; the turntable angle measurement coded disc, the turntable motor and the angular contact ball bearing are sequentially sleeved on the stator shaft from top to bottom and are positioned in the annular cavity.
Further, the first automatic leveling mechanism comprises a plurality of first servo electric cylinder actuators, a first sensor and a first leveling control system which are connected in parallel, wherein the upper ends and the lower ends of the plurality of first servo electric cylinder actuators are respectively connected with the bottom surface of the turntable body and the top surface of the base, the first sensor is arranged on the bottom surface of the turntable body, the output end of the first sensor is connected with the input end of the first leveling control system and used for transmitting the levelness change of the bottom surface of the turntable body, and the output end of the first leveling control system is respectively connected with the plurality of first servo electric cylinder actuators and used for leveling the bottom surface of the turntable body;
the second automatic leveling mechanism comprises a plurality of second servo electric cylinder actuators, second sensors and a second leveling control system which are connected in parallel, wherein the upper ends and the lower ends of the plurality of second servo electric cylinder actuators are respectively connected with the bottom surface of the turntable mounting plate and the top surface of the turntable body, the second sensors are arranged on the top surface of the turntable mounting plate, the output ends of the second sensors are connected with the input ends of the second leveling control system and used for transmitting the levelness change of the top surface of the turntable mounting plate, and the output ends of the second leveling control system are respectively connected with the plurality of second servo electric cylinder actuators and used for leveling the top surface of the turntable mounting plate.
Meanwhile, the invention also provides a ground calibration method for determining the full-range vision of the satellite payload, which is characterized by comprising the following steps:
step 1, assembling the ground calibration system and the system to be calibrated for determining the full-range line of sight of the satellite payload, so that the system to be calibrated is matched with the actual in-orbit condition;
step 2, leveling the bottom surface of the turntable body and the top surface of the turntable mounting plate respectively through a first automatic leveling mechanism and a second automatic leveling mechanism, and providing a mounting reference for the two-dimensional turntable through the turntable mounting plate;
step 3, starting an active thermoelastic simulation system, and detecting and adjusting the temperature of the system to be calibrated;
step 4, calibrating azimuth angles;
the method comprises the steps that an upper computer controls a target simulator to simulate a starry sky background and a measured target, so that satellite payloads are aligned to the corresponding target simulators, then the two-dimensional turntable drives the satellite payloads to rotate by at least one preset azimuth angle, and simultaneously the one-dimensional turntable is controlled to rotate by the same angle in the opposite direction; the method comprises the steps that imaging observation of a starry sky background and a measured target is carried out under at least one preset azimuth angle, and calibration of satellite payload sight line determination accuracy under the at least one preset azimuth angle is completed;
step 5, calibrating a pitch angle;
respectively setting the postures of a plurality of target simulators according to a plurality of preset pitch angles, and controlling the plurality of target simulators to respectively simulate a starry sky background and a measured target through an upper computer; and driving the satellite effective load to carry out imaging observation on the starry sky background and the measured target under a plurality of preset pitch angles through the two-dimensional turntable, and completing calibration of the satellite effective load sight line determination accuracy under the plurality of preset pitch angles.
Compared with the prior art, the invention has the beneficial effects that:
(1) The ground calibration system for determining the full-range line of sight of the satellite payload comprises an active thermoelastic simulation system, a one-dimensional turntable and a target simulation system, adopts a scheme of single-axis azimuth rotation and pitching fixed angle measurement, reduces moving components as much as possible while meeting the requirement of large-range measurement, eliminates various calibration errors in the ground calibration process through the active thermoelastic simulation system and the one-dimensional turntable, further improves the calibration precision, and can provide powerful support for satellite high-precision tracking and measurement.
(2) The ground calibration system for determining the full-range line of sight of the satellite payload is characterized in that the bottom surface of the turntable body and the top surface of the turntable mounting plate are respectively leveled by the first automatic leveling mechanism and the second automatic leveling mechanism, and the leveling precision is better than 2', so that the automatic leveling of the system to be calibrated is realized; the invention also provides an installation reference for the two-dimensional turntable through the turntable mounting plate, and the first automatic leveling mechanism and the second automatic leveling mechanism are combined with the turntable mounting plate, so that calibration errors caused by installation errors are eliminated.
(3) The invention is used for the ground calibration system for determining the full-range line of sight of the satellite payload, and the actual rotation angle of the turntable rotor is precisely measured and feedback controlled through the rotation angle calibration assembly, so that the calibration error caused by the pointing error is eliminated.
Drawings
FIG. 1 is a schematic diagram of an embodiment of a ground calibration system for satellite payload full range line-of-sight determination in accordance with the present invention;
FIG. 2 is a schematic view of a one-dimensional turntable according to an embodiment of the present invention;
FIG. 3 is a schematic view of the structure of a transfer table body according to an embodiment of the present invention;
FIG. 4 is a schematic view of a corner calibration assembly according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of a target simulation system (not shown) according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a two-dimensional turntable driving a satellite payload to rotate by a preset azimuth angle of 90 DEG in step 3 of a ground calibration method for full-range line-of-sight determination of the satellite payload according to the present invention;
FIG. 7 is a schematic view of the one-dimensional turntable rotated 90 degrees in the opposite direction in step 3 according to the embodiment of the present invention;
FIG. 8 is a schematic diagram of a two-dimensional turntable driving a satellite payload to rotate by a preset pitch angle of 0 ° in step 4 according to an embodiment of the present invention;
FIG. 9 is a schematic diagram of a two-dimensional turntable driving a satellite payload to rotate by a preset pitch angle of 30 ° in step 4 according to an embodiment of the present invention;
fig. 10 is a schematic diagram of the two-dimensional turntable driving the satellite payload to rotate by 60 ° at a preset pitch angle in step 4 according to the embodiment of the present invention.
The reference numerals are explained as follows: 01-a two-dimensional turntable; 02-satellite payload;
1-an active thermoelastic simulation system; the device comprises a 2-one-dimensional turntable, a 21-base, a 22-first automatic leveling mechanism, a 23-turntable body, a 231-turntable rotor, a 232-turntable stator, a 233-turntable angle measuring coded disc, a 234-turntable motor, a 235-angular contact ball bearing, a 24-second automatic leveling mechanism, a 25-corner calibration assembly, a 251-reference mirror holder, a 252-reference mirror, a 253-autocollimator and a 26-turntable mounting plate; 3-target simulation system, 31-simulator stand, 32-target simulator.
Detailed Description
The invention is further described below with reference to the drawings and exemplary embodiments.
Referring to fig. 1 to 5, a ground calibration system for satellite payload full range line of sight determination comprises an active thermoelastic simulation system 1, a one-dimensional turntable 2 and a target simulation system 3;
the system to be calibrated comprises a two-dimensional turntable 01 and a satellite effective load 02 arranged on the two-dimensional turntable 01, wherein the two-dimensional turntable 01 is used for realizing the full-range rotation of the visual axis of the satellite effective load 02 through azimuth and pitching motion.
The active thermoelastic simulation system 1 is used for eliminating calibration errors caused by thermal strain by detecting and adjusting the temperature of a system to be calibrated; the active thermal bomb simulation system 1 comprises an active thermal control system, a thermal strain test system and a software terminal; the thermal strain testing system is arranged on the two-dimensional turntable 01 and the satellite payload 02, and the output end of the thermal strain testing system is connected with the input end of the software terminal and is used for transmitting the thermal strain of the system to be calibrated; the output end of the software terminal is connected with the input end of the active thermal control system.
The thermal strain testing system comprises a data collector, a strain sensor and a temperature compensation circuit, wherein the strain sensor and the temperature compensation circuit are arranged on the system to be calibrated; the strain sensor is used for measuring the actual thermal strain of the two-dimensional turntable 01 and the satellite payload 02 and outputting the actual thermal strain to the data acquisition device; the temperature compensation circuit is used for measuring the ambient temperature near the strain sensor and outputting the expected thermal strain of the two-dimensional turntable 01 and the satellite payload 02 to the data acquisition device according to the ambient temperature and a preset calibration curve; the data acquisition device is used for correcting the actual thermal strain according to the expected thermal strain and outputting corrected thermal strain to the software terminal; the active thermal control system comprises a temperature controller connected with a software terminal, and a thermistor and a heating plate connected with the temperature controller; and the software terminal is used for obtaining a target value of the temperature of the system to be calibrated according to the corrected thermal strain and outputting the target value to the temperature controller. The temperature controller is used for calculating the current value of the temperature of the system to be calibrated by measuring the resistance value of the thermistor, comparing the current value with the target value, and controlling the current of the heating plate according to the comparison result to regulate the temperature.
Referring to fig. 2, the one-dimensional turntable 2 includes a corner calibration assembly 25, and a base 21, a first automatic leveling mechanism 22, a turntable body 23, and a second automatic leveling mechanism 24, which are sequentially disposed from bottom to top.
Referring to fig. 3, the turntable body 23 includes a turntable rotor 231, a turntable stator 232, a turntable angular contact coded disc 233, a turntable motor 234, and an angular contact ball bearing 235, which are coaxially disposed; the turntable rotor 231 comprises a rotating platform and an axial convex ring arranged on the bottom surface of the rotating platform; the turntable stator 232 comprises a stator shaft, the stator shaft is arranged in the axial convex ring, and the side wall of the stator shaft and the inner wall of the axial convex ring form an annular cavity; the turntable angular coded disc 233, the turntable motor 234 and the angular contact ball bearing 235 are sleeved on the stator shaft from top to bottom in sequence and are positioned in the annular cavity.
Referring to fig. 4, the corner calibration assembly 25 includes an autocollimator 253 and 22 reference frames 251; the auto-collimator 253 is arranged on the rotating platform and synchronously rotates along with the rotating platform, the circumference of the reference mirror frame 251 is uniformly distributed on the base 21, and each reference mirror frame 251 is provided with a reference mirror 252 which is centered with the optical axis of the auto-collimator 253 and used for sub-second calibration of the actual rotation angle of the turntable, so that the measurement of the rotation angle of the turntable is realized.
The first automatic leveling mechanism 22 comprises six first servo electric cylinder actuators, a first sensor and a first leveling control system which are connected in parallel, wherein the upper ends and the lower ends of the six first servo electric cylinder actuators are respectively connected with the bottom surface of the turntable body 23 and the top surface of the base 21, the input end of the first sensor is connected with the bottom surface of the turntable body 23, the output end of the first sensor is connected with the input end of the first leveling control system and used for transmitting the levelness change of the bottom surface of the turntable body 23, and the output end of the first leveling control system is respectively connected with the six first servo electric cylinder actuators and used for leveling the bottom surface of the turntable body 23.
The second automatic leveling mechanism 24 comprises six second servo electric cylinder actuators connected in parallel, a second sensor and a second leveling control system, wherein the upper ends and the lower ends of the six second servo electric cylinder actuators are respectively connected with the bottom surface of the turntable mounting plate 26 and the top surface of the turntable body 23, the second sensor is arranged on the top surface of the turntable mounting plate 26, the output end of the second sensor is connected with the input end of the second leveling control system and used for transmitting the levelness change of the top surface of the turntable mounting plate 26, and the output end of the second leveling control system is respectively connected with the six second servo electric cylinder actuators and used for leveling the top surface of the turntable mounting plate 26.
The leveling accuracy of both the first and second automatic leveling mechanisms 22, 24 may be better than 2 ".
The two-dimensional turntable 01 is arranged on the second automatic leveling mechanism 24 through a turntable mounting plate 26, and the turntable mounting plate 26 is used for providing a mounting reference for the two-dimensional turntable 01.
Referring to fig. 5, the target simulation system 3 includes a simulator stand 31, an upper computer, and five target simulators 32; five target simulators 32 are arranged on the simulator support 31 and are all connected with an upper computer for simulating the starry sky background and the measured target.
A ground calibration method for full range line of sight determination of satellite payloads comprising the steps of:
step 1, assembling the ground calibration system and the system to be calibrated for determining the full-range line of sight of the satellite payload, so that the system to be calibrated is matched with the actual in-orbit condition;
step 2, leveling the bottom surface of the turntable body 23 and the top surface of the turntable mounting plate 26 respectively through the first automatic leveling mechanism 22 and the second automatic leveling mechanism 24, and providing a mounting reference for the two-dimensional turntable 01 through the turntable mounting plate 26;
step 3, starting the active thermoelastic simulation system 1, and eliminating calibration errors caused by thermal strain by detecting and adjusting the temperature of the system to be calibrated;
step 4, calibrating azimuth angles;
the upper computer controls one target simulator 32 to simulate a starry sky background and a measured target, so that the satellite effective load 02 is aligned to the corresponding target simulator 32, then the two-dimensional turntable 01 drives the satellite effective load 02 to rotate by a preset azimuth angle of 90 degrees, and simultaneously controls the one-dimensional turntable 2 to rotate by 90 degrees in the opposite direction, as shown in fig. 6 and 7; the calibration of the satellite payload line-of-sight determination accuracy under the preset azimuth angle is completed through imaging observation of the starry sky background and the measured target under the preset azimuth angle;
the calibration method is as follows:
[1] fan the load line-of-sight determination of space object monitoring system technical research [ D ]. University of national defense science and technology, 2018.
[2] Cang Wenchi the main error study in line of sight determination for low and medium orbit optical satellites [ D ]. National defense science and technology university, 2021.DOI:10.27052/d.cnki.gzjgu.2018.000726.
Step 5, calibrating a pitch angle;
referring to fig. 8, 9 and 10, the three target simulators 32 are respectively arranged according to three preset pitch angles of 0 °, 30 ° and 60 °, and the three target simulators 32 are controlled by an upper computer to respectively simulate a starry sky background and a measured target; and then the two-dimensional turntable 01 drives the satellite payload 02 to carry out imaging observation on the starry sky background and the measured target under three preset pitch angles, so as to finish calibration of the satellite payload sight line determination accuracy under the three preset pitch angles.
Claims (4)
1. The ground calibration system for determining the full-range line of sight of the satellite payload comprises a two-dimensional turntable (01) and the satellite payload (02) arranged on the two-dimensional turntable (01), wherein the two-dimensional turntable (01) is used for realizing the full-range rotation of the visual axis of the satellite payload (02) through azimuth and pitching motions; the method is characterized in that: comprises an active thermoelastic simulation system (1), a one-dimensional turntable (2) and a target simulation system (3);
the active thermoelastic simulation system (1) is used for eliminating calibration errors caused by thermal strain by detecting and adjusting the temperature of a system to be calibrated; the active thermoelastic simulation system (1) comprises an active thermal control system, a thermal strain test system and a software terminal; the thermal strain testing system is arranged on the two-dimensional turntable (01) and the satellite payload (02), and the output end of the thermal strain testing system is connected with the input end of the software terminal; the thermal strain testing system comprises a data collector, a strain sensor and a temperature compensation circuit, wherein the strain sensor and the temperature compensation circuit are arranged on the system to be calibrated; the strain sensor is used for measuring the actual thermal strain of the two-dimensional turntable (01) and the satellite payload (02) and outputting the actual thermal strain to the data acquisition device; the temperature compensation circuit is used for measuring the ambient temperature near the strain sensor and outputting expected thermal strains of the two-dimensional turntable (01) and the satellite payload (02) to the data collector according to the ambient temperature and a preset calibration curve; the data acquisition device is used for correcting the actual thermal strain according to the expected thermal strain and outputting corrected thermal strain to the software terminal;
the active thermal control system comprises a temperature controller connected with a software terminal, and a thermistor and a heating plate connected with the temperature controller; the software terminal is used for obtaining a target value of the temperature of the system to be calibrated according to the corrected thermal strain and outputting the target value to the temperature controller; the temperature controller is used for calculating the current value of the temperature of the system to be calibrated by measuring the resistance value of the thermistor, comparing the difference value between the current value and the target value, and regulating the temperature of the system to be calibrated by controlling the current of the heating plate;
the one-dimensional turntable (2) comprises a corner calibration assembly (25), a base (21), a first automatic leveling mechanism (22), a turntable body (23) and a second automatic leveling mechanism (24) which are sequentially arranged from bottom to top; the turntable body (23) comprises a turntable rotor (231) and a turntable stator (232) which are coaxially arranged; the corner calibration assembly (25) comprises an auto-collimator (253) and a plurality of reference frames (251); the auto-collimator (253) is arranged on the turntable rotor (231) and synchronously rotates along with the turntable rotor (231), the circumference of the reference frame (251) is uniformly arranged on the base (21), and each reference frame (251) is provided with a reference mirror (252) which is centered with the optical axis of the auto-collimator (253) and is used for sub-second calibration of the actual rotation angle of the turntable rotor (231) and measurement of the rotation angle of the turntable rotor (231); the second automatic leveling mechanism (24) is provided with the two-dimensional turntable (01) through a turntable mounting plate (26), and the turntable mounting plate (26) is used for providing a mounting reference for the two-dimensional turntable (01);
the target simulation system (3) comprises a simulator bracket (31), an upper computer and a plurality of target simulators (32); the plurality of target simulators (32) are arranged on the simulator support (31) and are connected with the upper computer, and are used for simulating a starry sky background and a measured target.
2. The ground calibration system for satellite payload full range line-of-sight determination of claim 1, wherein: the turntable body (23) further comprises a turntable angle measuring coded disc (233), a turntable motor (234) and an angular contact ball bearing (235); the turntable rotor (231) comprises a rotating platform and an axial convex ring arranged on the bottom surface of the rotating platform, and the autocollimator (253) is arranged on the rotating platform; the turntable stator (232) comprises a stator shaft, the stator shaft is arranged in the axial convex ring, and an annular cavity is formed by the side wall of the stator shaft and the inner wall of the axial convex ring; the turntable angle measurement coded disc (233), the turntable motor (234) and the angular contact ball bearing (235) are sequentially sleeved on the stator shaft from top to bottom and are positioned in the annular cavity.
3. The ground calibration system for satellite payload full range line-of-sight determination of claim 2, wherein: the first automatic leveling mechanism (22) comprises a plurality of first servo electric cylinder actuators, a first sensor and a first leveling control system which are connected in parallel, wherein the upper ends and the lower ends of the plurality of first servo electric cylinder actuators are respectively connected with the bottom surface of the turntable body (23) and the top surface of the base (21), the first sensor is arranged on the bottom surface of the turntable body (23), the output end of the first sensor is connected with the input end of the first leveling control system and used for transmitting the levelness change of the bottom surface of the turntable body (23), and the output end of the first leveling control system is respectively connected with the plurality of first servo electric cylinder actuators and used for leveling the bottom surface of the turntable body (23);
the second automatic leveling mechanism (24) comprises a plurality of second servo electric cylinder actuators, second sensors and a second leveling control system which are connected in parallel, wherein the upper ends and the lower ends of the plurality of second servo electric cylinder actuators are respectively connected with the bottom surface of the turntable mounting plate (26) and the top surface of the turntable body (23), the second sensors are arranged on the top surface of the turntable mounting plate (26), the output ends of the second sensors are connected with the input ends of the second leveling control system and used for transmitting the levelness change of the top surface of the turntable mounting plate (26), and the output ends of the second leveling control system are respectively connected with the plurality of second servo electric cylinder actuators and used for leveling the top surface of the turntable mounting plate (26).
4. A ground calibration method for full range line of sight determination of satellite payloads, comprising the steps of:
step 1, assembling the ground calibration system and the system to be calibrated for determining the full-range line of sight of the satellite payload according to the claim 1;
step 2, leveling the bottom surface of the turntable body (23) and the top surface of the turntable mounting plate (26) respectively through a first automatic leveling mechanism (22) and a second automatic leveling mechanism (24), and providing a mounting reference for the two-dimensional turntable (01) through the turntable mounting plate (26);
step 3, starting the active thermoelastic simulation system (1), and detecting and adjusting the temperature of the system to be calibrated;
step 4, calibrating azimuth angles;
a target simulator (32) is controlled by an upper computer to simulate a starry sky background and a measured target, so that a satellite effective load (02) is aligned with the corresponding target simulator (32), and then the satellite effective load (02) is driven to rotate at least one preset azimuth angle through a two-dimensional turntable (01), and meanwhile the one-dimensional turntable (2) is controlled to rotate by the same angle in the opposite direction; the method comprises the steps that imaging observation of a starry sky background and a measured target is carried out under at least one preset azimuth angle, and calibration of satellite payload sight line determination accuracy under the at least one preset azimuth angle is completed;
step 5, calibrating a pitch angle;
the method comprises the steps that the gestures of a plurality of target simulators (32) are respectively arranged according to a plurality of preset pitch angles, and the plurality of target simulators (32) are controlled by an upper computer to respectively simulate a starry sky background and a measured target; and then the satellite effective load (02) is driven by the two-dimensional turntable (01) to carry out imaging observation on the starry sky background and the measured target under a plurality of preset pitch angles, so that calibration of the satellite effective load sight line determination accuracy under the plurality of preset pitch angles is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311391626.5A CN117129016B (en) | 2023-10-25 | 2023-10-25 | Ground calibration system and method for satellite payload full-range line-of-sight determination |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311391626.5A CN117129016B (en) | 2023-10-25 | 2023-10-25 | Ground calibration system and method for satellite payload full-range line-of-sight determination |
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| Publication Number | Publication Date |
|---|---|
| CN117129016A CN117129016A (en) | 2023-11-28 |
| CN117129016B true CN117129016B (en) | 2024-04-05 |
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