CN212158611U - Aerospace satellite optical and mechanical measurement reference unified precision measurement equipment - Google Patents
Aerospace satellite optical and mechanical measurement reference unified precision measurement equipment Download PDFInfo
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- CN212158611U CN212158611U CN202022083766.4U CN202022083766U CN212158611U CN 212158611 U CN212158611 U CN 212158611U CN 202022083766 U CN202022083766 U CN 202022083766U CN 212158611 U CN212158611 U CN 212158611U
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Abstract
The utility model belongs to the technical field of the space flight, concretely relates to unified accurate measurement equipment that can be applied to satellite optics and mechanical measurement benchmark. The aerospace satellite optical and mechanical measurement reference unified precision measurement equipment comprises a base, wherein a measurement ring is arranged on the base, four structural blocks are uniformly distributed on the outer circumferential surface of the measurement ring, and a cubic mirror is arranged on one of the structural blocks; the upper surface of the measuring ring is a main reference M surface, a lateral reference N surface is arranged on the side edge of the measuring ring, and the normals of the two mirror surfaces of the cubic mirror are perpendicular or parallel to the main reference M surface and the lateral reference N surface. The utility model is suitable for a condition that optics benchmark and mechanical benchmark used simultaneously, the range of reference is wide, and the assembly process of every satellite can all be adopted, and is very practical, and the meaning is very far away.
Description
Technical Field
The utility model belongs to the technical field of the space flight, concretely relates to unified accurate measurement equipment that can be applied to satellite optics and mechanical measurement benchmark.
Background
In the process of satellite accurate measurement, an optical measurement reference and a mechanical measurement reference are two different references, so that the integration of the optical measurement reference and the mechanical measurement reference of the satellite is required to be established so as to ensure the uniqueness of the accurate measurement reference.
The mechanical accurate measurement reference of the satellite is realized by designing a high-precision measurement ring and positioning and installing the satellite, and the optical accurate measurement reference criterion adopts a cubic mirror with the included angle of two adjacent surfaces superior to 5'. At present, the unification of the precision measurement reference of the optical machine mainly comprises two implementation modes which both have the defect that the precision of a part is lost in the middle of conversion. In the first mode, two adjacent vertical surfaces of the cubic mirror are bonded with two vertical surfaces designed by the measuring ring, and part of precision is lost due to the bonding force and glue solidification; in the second mode, the coincidence of a reference coordinate system for accurate measurement of a light machine is realized by online adjustment of measuring equipment (a laser tracker and a theodolite), and because a prism surface is too small, a cube mirror with the side length of 20mm is generally used, and partial precision is lost due to too close point-taking distance.
Therefore, on the basis of the existing precision measurement equipment, a novel satellite optical machine measurement reference unifying method is explored, and the satellite whole satellite integration precision can be improved.
SUMMERY OF THE UTILITY MODEL
The utility model discloses unified accurate measurement mode to two kinds of ray apparatus accurate measurement benchmarks that have now all has the technical problem of middle conversion loss part precision, and aim at provides a unified accurate measurement equipment of space satellite optics and mechanical measurement benchmark.
The aerospace satellite optical and mechanical measurement reference unified precision measurement equipment comprises a base, wherein a measurement ring is arranged on the base, four structural blocks are uniformly distributed on the outer circumferential surface of the measurement ring, and a cubic mirror is arranged on one of the structural blocks;
the upper surface of the measuring ring is a main reference M surface, a lateral reference N surface is arranged on the side edge of the measuring ring, and the normals of the two mirror surfaces of the cubic mirror are perpendicular or parallel to the main reference M surface and the lateral reference N surface.
The utility model discloses a normal of two mirror surfaces of cubic mirror and the perpendicular or parallel relation between main benchmark M face and the side direction benchmark N face realize the uniformity requirement of optical reference and mechanical reference. Adopt the utility model discloses afterwards, eliminated and pasted human error and the online measurement system's of equipment error, finally realize the unification of ray apparatus essence survey benchmark, can satisfy the satellite essence and survey the use.
The normal of one mirror surface of the cubic mirror is parallel to the main reference M surface and the lateral reference N surface respectively;
the normal of the other mirror surface of the cubic mirror is parallel to the main reference M surface and perpendicular to the lateral reference N surface.
The structure block is an L-shaped structure block in an L shape, a transverse pin hole is formed in the vertical section of the L-shaped structure block, and the L-shaped structure block penetrates through the pin hole through a positioning pin and is fixed on the outer circumferential surface of the measuring ring;
the cubic mirror is mounted on a transverse section of one of the L-shaped structural blocks.
And pin holes on the four L-shaped structure blocks determine the lateral reference N surface.
And two line segments obtained by connecting two opposite pin holes in four pin holes are positioned on a virtual surface which is vertical to the M surface of the main datum, wherein one surface is the N surface of the lateral datum.
The cubic mirror is fixed on the structural block through a locking screw.
The cube adopts a cube with the angle between two adjacent faces being better than 5 ".
The side edge of the cube mirror is provided with a laser tracker, and a target is arranged between the cube mirror and the laser tracker. The accurate position of the cubic mirror on the structural block can be determined through the laser tracker and the target, and then the cubic mirror is locked on the structural block through the locking screw.
The base is provided with four upright posts, and the bottom surfaces of the measuring rings are fixed on the four upright posts;
four universal wheels are arranged below the base. So as to move the utility model.
The utility model discloses an actively advance the effect and lie in: the utility model discloses a unified accurate survey equipment of space satellite optics and mechanical measurement benchmark is applicable to the condition that optics benchmark and mechanical benchmark used simultaneously, and the range of involvement is wide, and the assembly process of every satellite can all be adopted, and is very practical, and the meaning is very far away.
Drawings
Fig. 1 is a perspective view of the present invention.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention will be further explained with reference to the specific drawings.
Referring to fig. 1, the aerospace satellite optical and mechanical measurement reference unified precision measurement equipment comprises a base 1, wherein a measurement ring 2 is arranged on the base 1, four structural blocks 3 are uniformly distributed on the outer circumferential surface of the measurement ring 2, and a cubic mirror 4 is arranged on one of the structural blocks 3.
The upper surface of the measuring ring 2 is a main reference M surface, a lateral reference N surface is arranged on the side edge of the measuring ring 2, and the normals of the two mirror surfaces of the cubic mirror 4 are vertical or parallel to the main reference M surface and the lateral reference N surface. Wherein, the normal of one mirror surface of the cubic mirror 4 is parallel with the main reference M surface and the side reference N surface respectively. The normal of the other mirror surface of the cubic mirror 4 is parallel to the main reference M-plane and perpendicular to the lateral reference N-plane.
The structure block 3 is an L-shaped structure block 3, a transverse pin hole is formed in the vertical section of the L-shaped structure block 3, and the L-shaped structure block 3 penetrates through the pin hole through a positioning pin and is fixed on the outer circumferential surface of the measuring ring 2; the cube mirrors 4 are mounted on the lateral sections of one of the L-shaped building blocks 3. The pin holes on the four L-shaped structural blocks 3 determine the lateral reference N-plane. The four L-shaped star structure blocks are arranged in a pairwise opposite mode, so that pin holes in the four L-shaped star structure blocks are also divided into two groups of pin holes which are arranged in a pairwise opposite mode, two line segments obtained by connecting the pin holes in each group are used as virtual surfaces perpendicular to the M surface of the main datum plane through the line segments, and two virtual surfaces are obtained. One of the virtual planes is defined as the lateral reference N-plane according to the satellite orientation and measurement requirements.
The cube mirror 4 is fixed to the construction block 3 by means of locking screws. The cube 4 is a cube 4 with an included angle of adjacent faces better than 5 ".
The utility model discloses a cubic 4 normals of two mirror surfaces of mirror and the perpendicular or parallel relation between main benchmark M face and the side direction benchmark N face realize the uniformity requirement of optical benchmark and mechanical benchmark. Adopt the utility model discloses afterwards, eliminated and pasted human error and the online measurement system's of equipment error, finally realize the unification of ray apparatus essence survey benchmark, can satisfy the satellite essence and survey the use.
The side of the cube mirror 4 is provided with a laser tracker 5, and a target 6 is arranged between the cube mirror 4 and the laser tracker 5. The exact position of the cube mirror 4 on the construction block 3 can be determined by means of the laser tracker 5 and the target 6, and the cube mirror 4 is locked to the construction block 3 by means of the locking screw.
The utility model discloses when confirming cubic mirror 4, can adopt following mode:
1) the laser tracker 5 measures the main datum M surface and the lateral datum N surface respectively;
2) a cubic mirror 4 and a locking screw are arranged on the measuring ring;
3) the laser tracker 5 takes two points of the target 6.
As shown in fig. 1, the first route is: laser trackers 5, 1A, cubic mirrors 4, 1B, and a target 6; the second route is: laser trackers 5, 2A, targets 6.
4) The line connecting the two points is the normal L of the cube 4 in this direction.
5) And evaluating the relation between the L and the main reference M surface and the lateral reference N surface, and continuously adjusting the cubic mirror 4 to finally reach L// M and L// N.
6) And moving the laser tracker 5 and the target 6 to enable the laser tracker to see the other direction of the cubic mirror 4, repeating 3) -4), obtaining L ', and continuously adjusting the cubic mirror 4 again to reach L '// M and L '. DELTA.N.
At this time, the optical reference and the mechanical reference are unified.
Four upright posts are arranged on the base 1, and the bottom surface of the measuring ring 2 is fixed on the four upright posts. Four universal wheels 11 are arranged below the base 1. So as to move the utility model.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. The aerospace satellite optical and mechanical measurement reference unified precision measurement equipment comprises a base and is characterized in that a measurement ring is arranged on the base, four structural blocks are uniformly distributed on the outer circumferential surface of the measurement ring, and a cubic mirror is arranged on one of the structural blocks;
the upper surface of the measuring ring is a main reference M surface, a lateral reference N surface is arranged on the side edge of the measuring ring, and the normals of the two mirror surfaces of the cubic mirror are perpendicular or parallel to the main reference M surface and the lateral reference N surface.
2. An aerospace satellite optical and mechanical measurement reference unified precision measurement device according to claim 1, wherein the normal of one mirror face of the cube mirror is parallel to the main reference M-face and the lateral reference N-face, respectively;
the normal of the other mirror surface of the cubic mirror is parallel to the main reference M surface and perpendicular to the lateral reference N surface.
3. The aerospace satellite optical and mechanical measurement reference unified precision measurement device of claim 1, wherein the structure block is an L-shaped structure block having an L shape, a horizontal pin hole is formed on a vertical section of the L-shaped structure block, and the L-shaped structure block is fixed on the outer circumferential surface of the measurement ring by a positioning pin penetrating through the pin hole;
the cubic mirror is mounted on a transverse section of one of the L-shaped structural blocks.
4. An aerospace satellite optical and mechanical measurement reference unified fine measurement device according to claim 3, wherein pin holes in four of the L-shaped structure blocks define the lateral reference N-plane.
5. An aerospace satellite optical and mechanical measurement reference unified precision measurement device according to claim 1, wherein the cube is fixed to the structural block by locking screws.
6. An aerospace satellite optical and mechanical measurement reference unified surveying apparatus according to claim 1, wherein said cube is a cube with an adjacent dihedral angle superior to 5 ".
7. An aerospace satellite optical and mechanical measurement reference unified surveying apparatus according to any one of claims 1 to 6, wherein the cube is provided with laser trackers on its sides and a target is provided between the cube and the laser trackers.
8. The aerospace satellite optical and mechanical measurement reference unified precision measurement device of claim 1, wherein the base is provided with four posts, and the bottom surface of the measurement ring is fixed to the four posts;
four universal wheels are arranged below the base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022083766.4U CN212158611U (en) | 2020-09-22 | 2020-09-22 | Aerospace satellite optical and mechanical measurement reference unified precision measurement equipment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022083766.4U CN212158611U (en) | 2020-09-22 | 2020-09-22 | Aerospace satellite optical and mechanical measurement reference unified precision measurement equipment |
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| CN212158611U true CN212158611U (en) | 2020-12-15 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102527870B1 (en) * | 2022-11-07 | 2023-05-02 | 국방과학연구소 | Satellite reference coordinate system setting method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102527870B1 (en) * | 2022-11-07 | 2023-05-02 | 국방과학연구소 | Satellite reference coordinate system setting method |
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Effective date of registration: 20210701 Address after: 201203 building C, 888 Huanhu West 2nd Road, Pudong New Area, Shanghai Patentee after: Shanghai Paixing Information Technology Co., Ltd Address before: 201210 4th floor, 99 Haike Road, Pudong New Area, Shanghai Patentee before: SHANGHAI SCAS INFORMATION TECH. Co.,Ltd. |
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