CN108583935B - High-precision and high-stability mounting method for satellite-borne star sensor - Google Patents
High-precision and high-stability mounting method for satellite-borne star sensor Download PDFInfo
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- CN108583935B CN108583935B CN201810202225.3A CN201810202225A CN108583935B CN 108583935 B CN108583935 B CN 108583935B CN 201810202225 A CN201810202225 A CN 201810202225A CN 108583935 B CN108583935 B CN 108583935B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
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Abstract
The invention provides a high-precision and high-stability mounting method of a satellite-borne star sensor, which comprises the following steps of: the star sensor mounting structure is manufactured by adopting carbon fiber material mould pressing, and thread tapping is reserved at the corresponding position; performing matching and tapping treatment on the star sensor mounting structure at the positions corresponding to the two diagonal mounting holes of the star sensor precision measurement prism to form two screw holes; the star sensor is arranged on a satellite structure through a screw and is subjected to coarse precision adjustment; carrying out precision measurement and precision fine adjustment on the star sensor; after the precision is adjusted to the required range, the screws at the opposite corners are tightened and required torque is applied; pin holes are matched with the satellite structure through the remaining two holes on the star sensor; mounting pin screws at the two pin holes, and screwing through the flat pad, the elastic pad and the nut and applying a screwing torque; and dispensing and sealing the screw and the pin screw. When the star sensor is assembled on the satellite, the star can be assembled with high precision and high stability by using the existing mounting hole of the star sensor.
Description
Technical Field
The invention relates to the overall design technology of a spacecraft, in particular to a high-precision and high-stability installation method of a satellite-borne star sensor.
Background
With the development of high-precision space technologies such as space remote sensing mapping, space detection and the like in China, the star sensor is used as an independent and autonomous high-precision attitude measuring instrument and becomes a necessary attitude sensitive component on satellites, space shuttles and space stations. Under the background that high-precision star sensors are applied in China, the research on the high-precision high-stability star mounting technology of the high-precision star sensors has practical significance for ensuring the success of the satellite in-orbit task.
The star sensor undergoes vibration, temperature change and other factors in transmission and in-orbit operation along with the whole star, so that the star sensor mounting precision is changed, the pointing direction of the star sensor is deviated, and the star sensor mounting precision and precision stability are ensured to be necessary completely.
In the prior art, the star sensor is generally glued after being fastened with a star body structure in a mode of inner hexagon screw connection after precision measurement, precision deviation after star loading is prevented, but the mode cannot effectively ensure precision stability of the star sensor around the optical axis pointing direction (around the Z direction) before and after mechanical test, so that the precision stability is deviated, and therefore, how to ensure the precision stability deviation from an assembly angle becomes a difficult problem.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a high-precision and high-stability mounting method for a satellite-borne star sensor.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
s1, manufacturing the star sensor mounting structure by adopting carbon fiber material mould pressing, and reserving thread tapping at the corresponding position, namely, preparing an interface embedded part for drilling;
s2, performing matching and tapping treatment on the star sensor mounting structure at the positions corresponding to the two diagonal mounting holes of the star sensor precision measurement prism to form two screw holes;
s3, mounting the star sensor on the satellite structure through two screws and two screw holes formed in the step S2, and performing coarse precision adjustment;
s4, carrying out precision measurement on the star sensor and carrying out precision fine adjustment;
s5, after the precision is adjusted to the required range, tightening the diagonal screw and applying the required torque;
s6, pin hole matching is carried out on the satellite structure through the remaining two holes on the star sensor;
s7, mounting pin screws at the two pin holes, and screwing through the flat pad, the elastic pad and the nut and applying a screwing torque;
and S8, dispensing and sealing the screws and the pin screws.
The step S6 is to make pin hole matching of the satellite structure according to the following rules:
the length l of the pin segment is n (the number of flat pads) × t3 (the thickness of the flat pads) + t1+ (0.5-0.75) × t2, wherein t1 is the thickness of the mounting foot, t2 is the thickness of the mounting foot of the mounting surface structure,
the pin screw length l1 is l + b (thread segment length), where b is a (slot width) + t3 (flat pad thickness) + t4 (spring pad thickness) + (1.5-2) × t5 (nut thickness).
Compared with the prior art, the invention has the following beneficial effects:
1. when the star sensor is assembled on a satellite, the invention can ensure high-precision and high-stability assembly of the star sensor and has wider application range in engineering;
2. the method is simple, low in implementation cost and stable in precision.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is an assembly schematic diagram of a star sensor on a satellite structure in the high-precision high-stability mounting method of the satellite-borne star sensor in the embodiment of the invention.
FIG. 2 is a pin and screw assembly diagram in the high-precision and high-stability mounting method of the satellite-borne star sensor in the embodiment of the invention.
FIG. 3 is a flowchart of a high-precision and high-stability mounting method of a satellite-borne star sensor according to an embodiment of the invention.
In the figure:
1 is a star sensor;
2 is a star structure;
3 is a pin screw;
4 is a flat pad of phi 6;
5 is a flat pad of phi 5;
6 is a phi 5 elastic pad;
and 7 is a nut of M5.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 to 3, an embodiment of the present invention provides a high-precision and high-stability mounting method for a satellite-borne star sensor, including the following steps:
s1, manufacturing the star sensor mounting structure by adopting carbon fiber material mould pressing, and reserving thread tapping at the corresponding position, namely, preparing an interface embedded part for drilling;
s2, performing matching and tapping treatment on the star sensor mounting structure at the positions corresponding to the two diagonal mounting holes of the star sensor 1 precision measurement prism to form two screw holes;
s3, mounting the star sensor on the satellite structure 2 through two screws and two screw holes formed in the step S2, and performing coarse precision adjustment;
s4, carrying out precision measurement on the star sensor and carrying out precision fine adjustment;
s5, after the precision is adjusted to the required range, tightening the diagonal screw and applying the required torque;
s6, pin hole matching is carried out on the satellite structure through the remaining two holes on the star sensor;
s7, mounting pin screws 3 at the two pin holes, wherein one ends of the pin screws 3 sequentially penetrate through the phi 6 flat pad 4, the pin holes, the phi 5 flat pad 5 and the elastic pad 6 to be connected with nuts 7 in a threaded manner, and the nuts 7 are tightened and tightening torque is applied;
and S8, dispensing and sealing the screws and the pin screws.
The step S6 performs pin hole matching of the satellite structure according to the following rules:
and calculating the length specification of the pin screw in the step according to the mounting pin thickness t1 of the star sensor and the mounting pin thickness t2 of the mounting surface structure, wherein the length l of the pin section is n (the number of flat pads) × t3 (the thickness of the flat pads) + t1+ (0.5-0.75) × t2, so that the length l1 of the pin screw is l + b (the length of the thread section), and b is a (the grooving width) + t3 (the thickness of the flat pads) + t4 (the thickness of the elastic pads) + (1.5-2) × t5 (the thickness of the nut).
The implementation can effectively ensure the three rotational degrees of freedom of the star sensor, particularly the precision stability in the direction pointing around the optical axis when the high-precision single-machine assembly such as the planet sensor is carried out on the satellite.
In conclusion, when the star sensor is assembled on the star, the star sensor is assembled with high precision and high stability by adopting a mode of 'screws + pin screws', a new design method is created for the satellite design technology of subsequently equipping the high-precision star sensor in China, and the method has a wider application range in engineering.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (1)
1. The high-precision high-stability mounting method of the satellite-borne star sensor is characterized by comprising the following steps of:
s1, manufacturing the star sensor mounting structure by adopting carbon fiber material mould pressing, and reserving threads at corresponding positions for tapping;
s2, performing matching and tapping treatment on the star sensor mounting structure at the positions corresponding to the two diagonal mounting holes of the star sensor precision measurement prism to form two screw holes;
s3, mounting the star sensor on the satellite structure through two screws and two screw holes formed in the step S2, and performing coarse precision adjustment;
s4, carrying out precision measurement on the star sensor and carrying out precision fine adjustment;
s5, after the precision is adjusted to the required range, tightening the diagonal screw and applying the required torque;
s6, pin hole matching is carried out on the satellite structure through the remaining two holes on the star sensor;
s7, mounting pin screws at the two pin holes, and screwing through the flat pad, the elastic pad and the nut and applying a screwing torque;
s8, dispensing and sealing the screw and the pin screw;
the step S6 performs pin hole matching of the satellite structure according to the following rules:
since L is n × t3+ t1+ (0.5-0.75) × t2,
wherein t1 is the mounting leg thickness, t2 is the mounting leg thickness of the mounting surface structure, L is the length of the pin segment, n is the number of flat pads, and t3 is the flat pad thickness;
therefore, the temperature of the molten steel is controlled,
l1 is L + b, wherein b is a + t3+ t4+ (1.5-2) × t5, wherein L1 is the length of the pin screw, b is the length of the thread segment, a is the width of the slot, t3 is the thickness of the flat pad, t4 is the thickness of the elastic pad, and t5 is the thickness of the nut.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810202225.3A CN108583935B (en) | 2018-03-12 | 2018-03-12 | High-precision and high-stability mounting method for satellite-borne star sensor |
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| CN201810202225.3A CN108583935B (en) | 2018-03-12 | 2018-03-12 | High-precision and high-stability mounting method for satellite-borne star sensor |
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| CN108583935A CN108583935A (en) | 2018-09-28 |
| CN108583935B true CN108583935B (en) | 2020-07-14 |
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| CN104443435B (en) * | 2014-11-21 | 2016-06-29 | 上海卫星工程研究所 | For the star sensor mounting structure being thermomechanically separated and control |
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| CN105674981A (en) * | 2015-12-30 | 2016-06-15 | 中国科学院长春光学精密机械与物理研究所 | Ship-borne star sensor camera multifunctional protective apparatus |
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