High-precision calibration device for space position and attitude of satellite-borne optical camera

Abstract

The utility model belongs to the field of instrument calibration, and particularly relates to a high-precision calibration device for the spatial position and attitude of a satellite-borne optical camera. The device comprises a three-coordinate measuring instrument, a mounting shell, a laser theodolite, an accurate measuring mirror assembly, a large-aperture collimator and a beam splitter prism assembly, an imaging assembly mounting reference surface and an optical lens mounting reference surface are arranged on the mounting shell; an optical lens of a to-be-calibrated satellite-borne optical camera is mounted on the optical lens mounting datum plane, and an imaging assembly of the to-be-calibrated satellite-borne optical camera is mounted on the imaging assembly mounting datum plane; the accurate measurement lens assembly is installed on the satellite-borne optical camera. The large-aperture collimator is arranged on one side of an optical lens of the satellite-borne optical camera; the laser theodolite is arranged on one side of the satellite-borne optical camera; and the beam splitter prism assembly is arranged on an output light path of the laser theodolite. According to the utility model, the measurement precision of the space position attitude of the spaceborne optical camera is higher, and the adaptability is stronger.

Description

TECHNICAL FIELD

[0001] The utility model relates to a posture correction device, concretely relates to a high-precision calibration device for space position posture of spaceborne optical camera. BACKGROUND

[0002] At present, in the multispectral imaging satellite system at home and abroad, the multispectral remote sensing satellite system based on the spaceborne optical camera occupies the vast majority of the position, and it has the advantages of high resolution, high precision, strong stability, strong data transmission and real-time processing capacity, which directly determines the satellite imaging quality and the accuracy of data.

[0003] For the multispectral remote sensing satellite system based on the spaceborne optical camera, the space position posture of the spaceborne optical camera has an important influence on the satellite imaging quality and the accuracy of data, therefore, it is necessary to calibrate the space position posture of the spaceborne optical camera to ensure the satellite imaging quality and the accuracy of data.

[0004] In the prior art, a plurality of high-precision theodolites are usually used to realize the precise measurement of the position and posture of the mirror by self-aiming coordinate system transmission.

[0005] However, the existing calibration device is easy to cause insufficient correction accuracy and low correction efficiency of the space position posture of the spaceborne optical camera due to multiple conversions of the measurement reference. UTILITY MODEL CONTENTS

[0006] The utility model aims at solving the technical problems of insufficient correction accuracy and low correction efficiency of the space position posture of the spaceborne optical camera due to multiple conversions of the measurement reference of the existing calibration device, and provides a high-precision correction device for the space installation position posture.

[0007] To achieve the above-mentioned purpose, the utility model adopts the following technical scheme:

[0008] A high-precision calibration device for the space position posture of the spaceborne optical camera, which is characterized by:

[0009] The device comprises a three-coordinate measuring instrument, a mounting shell, a laser theodolite, a precise measurement mirror assembly, a large-diameter collimator and a beam splitter prism assembly.

[0010] The mounting shell is provided with an imaging assembly installation reference surface and an optical lens installation reference surface, and the measurement probe of the three-coordinate measuring instrument can be in contact with the imaging assembly installation reference surface and the optical lens installation reference surface respectively, so as to measure the parallelism of the imaging assembly installation reference surface and the perpendicularity between the imaging assembly installation reference surface and the optical lens installation reference surface.

[0011] The optical lens of the satellite-borne optical camera to be calibrated is mounted on an optical lens mounting reference surface, and an imaging assembly of the satellite-borne optical camera is mounted on an imaging assembly mounting reference surface; a fine measurement mirror assembly is mounted on the satellite-borne optical camera;

[0012] One side of the optical lens of the satellite-borne optical camera is a large-aperture collimator; a laser theodolite is arranged on one side of the satellite-borne optical camera and is located on a side of the satellite-borne optical camera away from the optical lens of the satellite-borne optical camera;

[0013] A light-splitting prism assembly is arranged on an output light path of the laser theodolite and is used for simultaneously presenting a self-collimation image of the laser theodolite to an X direction and a Z direction of the fine measurement mirror assembly; the X direction is a direction perpendicular to the optical lens mounting reference surface, and the Z direction is an optical lens axial direction of the satellite-borne optical camera.

[0014] Further, the display is electrically connected with the satellite-borne optical camera and is used for displaying an image output by the satellite-borne optical camera.

[0015] Further, the display is electrically connected with the satellite-borne optical camera and is used for displaying an image output by the satellite-borne optical camera.

[0016] Further, the light-splitting prism assembly comprises a light-splitting prism one, a light-splitting prism two and a light-splitting prism three.

[0017] The light-splitting prism one is arranged on the output light path of the laser theodolite, and a light-splitting light path of the light-splitting prism one is located on the X direction of the fine measurement mirror assembly.

[0018] The light-splitting prism two is arranged on a reflected light path of the light-splitting prism one, the light-splitting prism three is arranged on a reflected light path of the light-splitting prism two, and the reflected light path of the light-splitting prism three is located on the Z direction of the fine measurement mirror assembly.

[0019] Further, the four-dimensional adjustable turntable one, the four-dimensional adjustable turntable two and the four-dimensional adjustable turntable three are further included.

[0020] The light-splitting prism one, the light-splitting prism two and the light-splitting prism three are respectively mounted on the four-dimensional adjustable turntable one, the four-dimensional adjustable turntable two and the four-dimensional adjustable turntable three.

[0021] Further, the two-dimensional horizontal moving platform is further included.

[0022] A moving direction of the two-dimensional horizontal moving platform is arranged in parallel with a radial direction of the large-aperture collimator, and the laser theodolite is mounted on the two-dimensional horizontal moving platform.

[0023] Further, the optical platform is further included.

[0024] The satellite-borne optical camera, the three-coordinate measuring instrument and the large-aperture collimator are respectively mounted on the optical platform.

[0025] Further, the four-dimensional adjustable turntable four mounted on the optical platform is further included.

[0026] The spaceborne optical camera is installed on the four-dimensional adjustable rotating table four through a camera clamp.

[0027] Further, the fine measurement mirror assembly comprises a fine measurement mirror body, a fine measurement mirror seat and a lapping boss arranged on the bottom surface of the fine measurement mirror seat; the fine measurement mirror body is arranged on the top surface of the fine measurement mirror seat; the fine measurement mirror seat is connected to the spaceborne optical camera through a fastener, and the lapping boss abuts on the spaceborne optical camera.

[0028] The spaceborne optical camera has the advantages that:

[0029] 1. The spaceborne optical camera can be measured by the three-coordinate measuring instrument to measure the flatness of the imaging assembly mounting reference surface of the spaceborne optical camera, and on this basis, the perpendicularity between the optical lens mounting reference surface and the imaging assembly mounting reference surface is measured, so as to provide a calibration target for the coaxial adjustment of the spaceborne optical camera and the imaging assembly.

[0030] 2. The spaceborne optical camera can accurately measure the pixel-level offset of the optical lens horizontal or vertical field edge image of the spaceborne optical camera relative to the imaging assembly field center image, which is beneficial to more accurately complete the coaxial adjustment of the imaging assembly normal line and the optical lens optical axis, and further effectively improve the spatial position precision calibration precision of the spaceborne optical system.

[0031] 3. The two-dimensional horizontal moving platform and the laser theodolite are arranged at the front end of the large-aperture collimator, the laser theodolite, the spaceborne optical camera and the large-aperture collimator are mutually self-corrected, and coaxiality is realized; the laser theodolite can simultaneously observe the reference target object in the large-aperture collimator and the reflection image of the laser theodolite in the fine measurement mirror assembly; and the coaxial adjustment device overcomes the limitations of traditional multi-target coaxial measurement.

[0032] 4. The bottom surface of the fine measurement mirror assembly seat is provided with a lapping boss, accurate adjustment size can be provided through the laser theodolite, the position coordinate system of the fine measurement mirror assembly relative to the spaceborne optical camera is obtained, the spatial attitude position measurement efficiency of the spaceborne optical camera is higher; compared with the traditional adjustment mode of adding a lapping pad at the lower end of the fine measurement mirror seat, the device used in the utility model has higher structural stability and operation convenience.

[0033] 5. Three light splitting prisms are arranged between the measurement light path of the laser theodolite and the fine measurement mirror assembly, compared with the traditional measurement device, the measurement error caused by the multiple reference conversion during the measurement of the laser theodolite is suppressed, the measurement precision of the spatial position and attitude of the spaceborne optical camera is higher, and the adaptability is stronger. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 It is a mounting structure schematic view of the three-coordinate measuring instrument and the spaceborne optical camera mounting shell in the embodiment of the utility model.

[0035] Figure 2 is the coaxial measurement schematic diagram of the spaceborne optical camera in the embodiment of the utility model;

[0036] Figure 3 is the installation position schematic diagram of the fine measurement mirror assembly in the embodiment of the utility model;

[0037] Figure 4 is the space position attitude calibration schematic diagram of the spaceborne optical camera in the embodiment of the utility model.

[0038] In the drawing: 1-laser theodolite, 2-spaceborne optical camera, 21-optical lens, 3-fine measurement mirror assembly, 31-fine measurement mirror body, 32-fine measurement mirror seat, 33-research convex platform, 4-four-dimensional adjustable revolving stage four, 5-large aperture collimator, 6-optical platform, 7-display, 8-two-dimensional horizontal movement platform, 9-diffractive prism assembly, 91-diffractive prism one, 92-diffractive prism two, 93-diffractive prism three, 94-four-dimensional adjustable platform one, 95-four-dimensional adjustable platform two, 96-four-dimensional adjustable platform three, 10-installation shell, 101-imaging assembly installation reference surface, 102-optical lens installation reference surface, 11-three-coordinate measuring instrument, 111-measurement probe, 12-camera fixture. DETAILED DESCRIPTION

[0039] In order to make the purpose, advantages and characteristics of the utility model more clear, the following combines the drawings and specific embodiment and makes further detailed description to the space installation position attitude high-precision correction device proposed in the utility model. According to the following specific embodiment, the advantages and characteristics of the utility model will be more clear.

[0040] Referring to Figure 1 , the embodiment spaceborne optical camera space position attitude high-precision calibration device is used for measuring the installation position of fine measurement mirror assembly relative to spaceborne optical camera, including three-coordinate measuring instrument 11, spaceborne optical camera installation shell 10, laser theodolite 1, fine measurement mirror assembly 3, large aperture collimator 5, diffractive prism assembly 9, optical platform 6, display 7, two-dimensional horizontal movement platform 8, four-dimensional adjustable revolving stage one 94, four-dimensional adjustable revolving stage two 95 and four-dimensional adjustable revolving stage three 96 and four-dimensional adjustable revolving stage four 4.

[0041] The three-coordinate measuring instrument 11 and the mounting shell 10 are respectively arranged on the optical platform 6, the mounting shell 10 is provided with an imaging assembly mounting reference surface 101 and an optical lens mounting reference surface 102, the measuring probe 111 of the three-coordinate measuring instrument 11 is in contact with the imaging assembly mounting reference surface 101 and the optical lens mounting reference surface 102 respectively, and the parallelism of the imaging assembly mounting reference surface 101 and the perpendicularity of the imaging assembly mounting reference surface 101 and the optical lens mounting reference surface 102 can be measured by the three-coordinate measuring instrument 11, thereby providing a calibration target for subsequent optical lens 21 and imaging assembly normal coaxial adjustment of the spaceborne optical camera 2.

[0042] The optical lens 21 of the spaceborne optical camera 2 to be calibrated is mounted on the optical lens mounting reference surface 102, and the imaging assembly thereof is mounted on the imaging assembly mounting reference surface 101; the spaceborne optical camera 2 is mounted on the four-dimensional adjustable rotary table four 4 through the camera clamp 12, the position and posture of the spaceborne optical camera 2 can be adjusted through the four-dimensional adjustable rotary table four 4, the spaceborne optical camera 2 is electrically connected with the display 7, and the display 7 is used for displaying the image output by the spaceborne optical camera 2, so as to adjust the imaging clarity of the spaceborne optical camera 2 through the display 7.

[0043] Referring to Figure 3 The fine measurement mirror assembly 8 is mounted on the spaceborne optical camera 2. Specifically, the fine measurement mirror assembly 3 comprises a fine measurement mirror body 31, a fine measurement mirror seat 32 and a lapping boss 33 arranged on the bottom surface of the fine measurement mirror seat 32; the fine measurement mirror body 31 is arranged on the top surface of the fine measurement mirror seat 32; the fine measurement mirror seat 32 is connected to the spaceborne optical camera 2 through a fastener, and the lapping boss 33 abuts against the spaceborne optical camera 2.

[0044] The large-aperture collimator 5 is arranged on the optical platform 6 and located on one side of the optical lens 21 of the spaceborne optical camera 2; the laser theodolite 1 is mounted on the two-dimensional horizontal moving platform 8, the moving direction of the two-dimensional horizontal moving platform 8 is parallel to the radial direction of the large-aperture collimator 5, the laser theodolite 1 is arranged on one side of the optical platform 6 and located on the side of the spaceborne optical camera 2 away from the optical lens 21 thereof; the optical axes of the laser theodolite 1, the spaceborne optical camera 2 and the large-aperture collimator 5 are coaxially arranged.

[0045] The light splitting prism assembly 9 is arranged on the output light path of the laser theodolite 1 and used for simultaneously presenting the autocollimation image of the laser theodolite 1 to the X direction and the Z direction of the fine measurement mirror assembly 9. The X direction is perpendicular to the optical lens mounting reference surface 102, and the Z direction is the axial direction of the optical lens 21 of the spaceborne optical camera 2.

[0046] Specifically, the light splitting prism assembly 9 includes a light splitting prism one 91, a light splitting prism two 92 and a light splitting prism three 93; the light splitting prism one 91, the light splitting prism two 92 and the light splitting prism three 93 are respectively installed on a four-dimensional adjustable turntable one 94, a four-dimensional adjustable turntable two 95 and a four-dimensional adjustable turntable three 96. The light splitting prism one 91 is arranged on the output light path of the laser theodolite 1, and its light splitting light path is located in the X direction of the fine measurement lens assembly 3; the light splitting prism two 92 is arranged on the reflected light path of the light splitting prism one 91, the light splitting prism three 93 is arranged on the reflected light path of the light splitting prism two 92, and the reflected light path of the light splitting prism three 93 is located in the Z direction of the fine measurement lens assembly 3.

[0047] In use, the following steps are included:

[0048] Step 1, using the three-coordinate measuring instrument 11, taking the imaging assembly mounting reference surface 101 on the star-borne optical camera 2 mounting shell as the reference, the planeness h (unit: mm) is measured, and on this basis, the perpendicularity p (unit: mm) between the imaging assembly mounting reference surface 101 and the optical lens mounting reference surface 102 is measured by using the three-coordinate measuring instrument.

[0049] Step 2, the least square method is used to determine the correction misalignment amount;

[0050] The planeness h and the perpendicularity p measured in step 1 are least square fitted, so as to obtain the correction misalignment amount Δ (unit: mm) of the star-borne optical camera 2 during assembly and adjustment, which provides a reference for the subsequent coaxial adjustment of the optical lens 21 and the imaging assembly of the star-borne optical camera 2.

[0051] Step 3, coaxial adjustment of the optical lens 21 and the imaging assembly of the star-borne optical camera 2;

[0052] Step 3.1, first, the optical lens 21 of the star-borne optical camera 2 to be calibrated is mounted on the optical lens mounting reference surface 102, and then the imaging assembly of the star-borne optical camera 2 to be calibrated is mounted on the imaging assembly mounting reference surface 101.

[0053] Step 3.2, connecting the star-borne optical camera 2 to be calibrated with the display 7, the display 7 can display images, the imaging assembly of the star-borne optical camera 2 is adjusted to have clear imaging, and whether the imaging assembly of the star-borne optical camera 2 meets the preset clarity requirement is judged through the display 7, the preset clarity requirement can be subjectively set according to actual needs, which is not specifically limited in the embodiment, if yes, step 3.3 is executed; if no, the imaging assembly of the star-borne optical camera 2 is re-adjusted until the preset clarity requirement is met.

[0054] Step 3.2, adjust the relative position between the optical lens 21 and the imaging assembly of the spaceborne optical camera 2 based on the center of the imaging assembly field of view of the spaceborne optical camera 2, so that the optical lens 21 optical axis of the spaceborne optical camera 2 is coaxial with the imaging assembly normal line, and the calibration of the correction misalignment amount Δ is realized.

[0055] Step 3.3, measure the maximum pixel offset of the optical lens 21 of the spaceborne optical camera 2 at the horizontal and vertical field of view edges and the imaging assembly field of view center, and determine whether the maximum pixel offset meets the preset accuracy, in this embodiment, the preset accuracy d is in the range of 0≤d≤1. If yes, step 4 is executed, and if no, the correction misalignment amount Δ is recalibrated until the preset accuracy is met, and the coaxial calibration of the optical lens 21 of the spaceborne optical camera 2 and the imaging assembly is realized.

[0056] Step 4, establish a stable image measurement coordinate system X0-Y0-Z0 based on the optical axis of the spaceborne optical camera 2.

[0057] Step 5, coaxial adjustment of the laser theodolite 1, the spaceborne optical camera 2 and the large-aperture collimator 5;

[0058] Step 5.1, set a star point target on the end face of the large-aperture collimator 5 away from the spaceborne optical camera 2, which is used as an imaging target.

[0059] Step 5.2, install the spaceborne optical camera 2 on the four-dimensional adjustable turntable four 4, and install the spaceborne optical camera 2 and the four-dimensional adjustable turntable four 4 as a whole and the large-aperture collimator 5 on the optical platform 6 respectively, and set the spaceborne optical camera 2 at the front end of the large-aperture collimator 5, adjust the relative position between the spaceborne optical camera 2 and the star point target through the four-dimensional adjustable turntable four 4, and realize the coaxial adjustment of the optical axis of the spaceborne optical camera 2 and the large-aperture collimator 5.

[0060] Step 5.3, install the laser theodolite 1 on the two-dimensional horizontal moving platform 8, and place the laser theodolite 1 and the two-dimensional horizontal moving platform 8 as a whole on one side of the optical platform 6, and on the side of the spaceborne optical camera 2 away from the large-aperture collimator 5, adjust the relative position between the laser theodolite 1 and the spaceborne optical camera 2 through the two-dimensional horizontal moving platform 8, and finally make the optical axes of the laser theodolite 1, the spaceborne optical camera 2 and the large-aperture collimator 5 coaxial with each other.

[0061] Step 5.4, establish a coordinate system X c -Y c -Z c , convert the stable image measurement coordinate system X0-Y0-Z0 based on the optical axis of the spaceborne optical camera 2 into the measurement coordinate system X c -Yc -Z c .

[0062] Step 6, the fine measurement mirror assembly 3 includes a fine measurement mirror body 31, a fine measurement mirror seat 32 and a lapping boss 33 arranged on the bottom surface of the fine measurement mirror seat 32; the fine measurement mirror body 31 is arranged on the top surface of the fine measurement mirror seat 32. The fine measurement mirror body 31 is installed on the spaceborne optical camera 2 through the lapping boss 33.

[0063] A coordinate system X-Y-Z is established with the optical axis of the fine measurement mirror body 31 as the reference, the X direction, the Y direction and the Z direction of the coordinate system X-Y-Z correspond to the X direction, the Y direction and the Z direction of the coordinate system X-Y-Z in the initial state respectively, and the lapping prism assembly is arranged so that the autocollimation image of the laser theodolite 1 can be presented to the X direction and the Z direction of the fine measurement mirror body 31 at the same time through the lapping prism assembly, so that the spatial position measurement of the fine measurement mirror assembly 3 can be realized through one laser theodolite 1. c -Y c -Z c c c c directions of the coordinate system X-Y-Z in the initial state. The lapping prism assembly is arranged so that the autocollimation image of the laser theodolite 1 can be presented to the X direction and the Z direction of the fine measurement mirror body 31 at the same time through the lapping prism assembly, so that the spatial position measurement of the fine measurement mirror assembly 3 can be realized through one laser theodolite 1.

[0064] Step 7, the installation position of the fine measurement mirror body 31 is adjusted through the lapping boss 33 arranged on the bottom surface of the fine measurement mirror seat 32, and it is judged whether the autocollimation image of the laser theodolite 1 meets the preset tolerance requirement, if yes, the installation position adjustment of the fine measurement mirror assembly 3 is completed, if not, the installation position of the fine measurement mirror body 31 is adjusted again until the preset tolerance requirement is met.

[0065] Step 8, the spatial position of the fine measurement mirror assembly 3 relative to the spaceborne optical camera 2 is measured through the laser theodolite 1, and then the spatial position attitude of the spaceborne optical camera 2 is calibrated according to the measurement result, so as to realize the spatial position attitude measurement and calibration of the spaceborne optical camera 2.​​​

Claims

1. A high-precision calibration device for the spatial position and attitude of a spaceborne optical camera, characterized in that: It includes a coordinate measuring machine (11), a mounting housing (10), a laser theodolite (1), a precision measuring mirror assembly (3), a large-aperture collimator (5), and a beam splitter assembly (9); The mounting housing (10) is provided with an imaging component mounting reference surface (101) and an optical lens mounting reference surface (102). The measuring probe (111) of the coordinate measuring machine (11) can contact the imaging component mounting reference surface (101) and the optical lens mounting reference surface (102) respectively to measure the parallelism of the imaging component mounting reference surface (101) and the perpendicularity between the imaging component mounting reference surface (101) and the optical lens mounting reference surface (102). The optical lens (21) of the spaceborne optical camera (2) to be calibrated is mounted on the optical lens mounting reference surface (102), and its imaging component is mounted on the imaging component mounting reference surface (101). The precision measuring mirror assembly (3) is mounted on the spaceborne optical camera (2); The large-diameter collimator (5) is located on one side of the optical lens (21) of the spaceborne optical camera (2); the laser theodolite (1) is located on the side of the spaceborne optical camera (2) away from its optical lens (21); The beam splitter assembly (9) is disposed on the output optical path of the laser theodolite (1) and is used to simultaneously present the autocollimation image of the laser theodolite (1) to the X and Z directions of the precision measuring mirror assembly (3); the X direction is the direction perpendicular to the optical lens mounting reference surface (102), and the Z direction is the axis of the optical lens (21) of the spaceborne optical camera (2).

2. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 1, characterized in that: It also includes a display (7); The display (7) is electrically connected to the spaceborne optical camera (2) and is used to display the output image of the spaceborne optical camera (2).

3. A high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 1 or 2, characterized in that: The beam splitter assembly (9) includes beam splitter one (91), beam splitter two (92) and beam splitter three (93); The beam splitter prism (91) is disposed on the output optical path of the laser theodolite (1), and its beam splitting optical path is located in the X direction of the precision measuring mirror assembly (3); The second beam splitter (92) is disposed on the reflected light path of the first beam splitter (91), and the third beam splitter (93) is disposed on the reflected light path of the second beam splitter (92), and the reflected light path of the third beam splitter (93) is located in the Z direction of the precision measuring mirror assembly (3).

4. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 3, characterized in that: It also includes four-dimensional adjustable turntable one (94), four-dimensional adjustable turntable two (95) and four-dimensional adjustable turntable three (96); The beam splitter 1 (91), beam splitter 2 (92) and beam splitter 3 (93) are respectively mounted on four-dimensional adjustable turntable 1 (94), four-dimensional adjustable turntable 2 (95) and four-dimensional adjustable turntable 3 (96).

5. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 4, characterized in that: It also includes a two-dimensional horizontal moving platform (8); The moving direction of the two-dimensional horizontal moving platform (8) is set parallel to the radial direction of the large-diameter parallel light tube (5), and the laser theodolite (1) is installed on the two-dimensional horizontal moving platform (8).

6. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 5, characterized in that: It also includes an optical platform (6); The spaceborne optical camera (2), coordinate measuring machine (11), and large-aperture collimator (5) are respectively mounted on the optical platform (6).

7. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 6, characterized in that: It also includes a four-dimensional adjustable turntable four (4) mounted on the optical platform (6); The spaceborne optical camera (2) is mounted on the four-dimensional adjustable turntable (4) via camera clamp (12).

8. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 1, characterized in that: The precision measuring mirror assembly (3) includes a precision measuring mirror body (31), a precision measuring mirror mount (32), and a finishing protrusion (33) disposed on the bottom surface of the precision measuring mirror mount (32); the precision measuring mirror body (31) is disposed on the top surface of the precision measuring mirror mount (32); the precision measuring mirror mount (32) is connected to the spaceborne optical camera (2) by fasteners, and the finishing protrusion (33) abuts against the spaceborne optical camera (2).

9. The high-precision calibration device for the spatial position and attitude of a spaceborne optical camera according to claim 1, characterized in that: The exit aperture of the large-diameter collimator (5) is greater than or equal to the maximum external dimensions of the spaceborne optical camera (2) and the laser theodolite (1).

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