CN108583935A - Spaceborne star sensor high precision high stability degree installation method - Google Patents
Spaceborne star sensor high precision high stability degree installation method Download PDFInfo
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- CN108583935A CN108583935A CN201810202225.3A CN201810202225A CN108583935A CN 108583935 A CN108583935 A CN 108583935A CN 201810202225 A CN201810202225 A CN 201810202225A CN 108583935 A CN108583935 A CN 108583935A
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- star sensor
- screw
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- pin
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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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- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
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Abstract
The present invention provides a kind of spaceborne star sensor high precision high stability degree installation methods, include the following steps：Processing and fabricating star sensor mounting structure is molded using carbon fibre material, thread tapping is reserved in corresponding position；To the star sensor mounting structure at two corresponding positions of diagonal mounting hole of star sensor accurate measurement prism carry out with beat, tapping process, formation two screw holes；Star sensor is mounted on satellite structure by screw and carries out precision coarse adjustment；Precision measure and precision accurate adjustment are carried out to star sensor；Precision is adjusted to claimed range, is tightened diagonal screw and is applied the torque of requirement；Pin hole is carried out by two holes of residue on star sensor to satellite structure to manufacture；The mounting pin screw at two pin holes, and tightened by plain cushion, spring washer, nut and apply screw-down torque；Dispensing sealing is carried out to screw and pin screw.The present invention can carry out high precision high stability degree using the existing mounting hole of star sensor and fill star when carrying out spaceborne star sensor assembly.
Description
Technical field
The present invention relates to spacecraft overall design techniques, and in particular, to spaceborne star sensor high precision high stability degree peace
Dress method.
Background technology
With the development of the high-grade, precision and advanced space technologies such as Chinese Space remote sensing mapping, space flight investigation, star sensor is as a kind of
Independent high-precision attitude measuring instrument has become posture sensing unit indispensable on satellite, space shuttle and space station.
Under the background that China has realized Rotating Platform for High Precision Star Sensor application, the high precision high stability degree dress star of Rotating Platform for High Precision Star Sensor is studied
Technology is to ensureing that the success of the in-orbit task of satellite has practical significance.
Star sensor with whole star undergo from transmitting and in orbit in vibration, temperature change and other factors make star
Sensor installation accuracy changes, and generates deviation so as to cause the direction of star sensor, therefore ensure the dress star of star sensor
Precision and precision stability are completely necessary.
In the prior art, star sensor be usually after precision measure soket head cap screw connection by way of with celestial body knot
Carry out dispensing after structure fastening, occur precision offset again after preventing dress star, but which can not be effectively ensured star sensor around
Optical axis is directed toward precision stability of the rotary freedom of (around Z-direction) before and after undergoing mechanical test, and precision stability is caused to occur
Deviation, therefore, how from angle of assembling ensure stable accuracy sexual deviation become a problem.
Invention content
For the defects in the prior art, the object of the present invention is to provide a kind of spaceborne star sensor high precision high stability degree
Installation method.
To achieve the goals above, the technical solution adopted by the present invention is as follows：
S1, processing and fabricating star sensor mounting structure is molded using carbon fibre material, and screw thread is reserved in corresponding position
The interface embedded part of brill is matched in tapping；
S2, to the star sensor mounting structure at two corresponding positions of diagonal mounting hole of star sensor accurate measurement prism into
Row with beat, tapping process, formation two screw holes；
Star sensor is mounted on satellite structure and goes forward side by side by S3, two screw holes formed by two screws and step S2
Row precision coarse adjustment；
S4, precision measure is carried out to star sensor and carries out precision accurate adjustment；
S5, precision are adjusted to claimed range, are tightened diagonal screw and are applied the torque of requirement；
S6, satellite structure progress pin hole is manufactured by two holes of residue on star sensor；
S7, the mounting pin screw at two pin holes, and tightened by plain cushion, spring washer, nut and apply screw-down torque；
S8, dispensing sealing is carried out to screw and pin screw.
Wherein, the step S6 is manufactured according to the pin hole that following rule carries out satellite structure：
Due to：Length l=n (plain cushion quantity) × t3 (plain cushion thickness)+t1+ (0.5~0.75) × t2 for selling section, in formula：
T1 is installation foot thickness, and t2 is the installation foot thickness of mounting surface structure；Therefore
Sell screw length l1=l+b (screw thread segment length), wherein b=a (groove width)+t3 (plain cushion thickness)+t4 (bullets
Mat thickness)+(1.5~2) × t5 (nut thickness).
Compared with prior art, the present invention has following advantageous effect：
1, the present invention is carrying out star sensor when being assembled on satellite, can ensure that star sensor high precision high stability degree fills
Match, there is the wider scope of application in engineering；
2, the method for the present invention is simple, implementation cost is cheap, stable accuracy.
Description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 be in the spaceborne star sensor high precision high stability degree installation method of the embodiment of the present invention star sensor in satellite knot
Assembling schematic diagram on structure.
Fig. 2 is that screw assembly signal is sold in the spaceborne star sensor high precision high stability degree installation method of the embodiment of the present invention
Figure.
Fig. 3 is the flow chart of the spaceborne star sensor high precision high stability degree installation method of the embodiment of the present invention.
In figure：
1 is star sensor；
2 be celestial body structure；
3 be pin screw；
4 be the plain cushion of Φ 6；
5 be the plain cushion of Φ 5；
6 be the spring washer of Φ 5；
7 be the nut of M5.
Specific implementation mode
With reference to specific embodiment, the present invention is described in detail.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in Figure 1-Figure 3, an embodiment of the present invention provides a kind of spaceborne star sensor high precision high stability degree installation sides
Method, including steps are as follows：
S1, processing and fabricating star sensor mounting structure is molded using carbon fibre material, and screw thread is reserved in corresponding position
The interface embedded part of brill is matched in tapping；
S2, to the star sensor mounting structure at two corresponding positions of diagonal mounting hole of 1 accurate measurement prism of star sensor
Carry out with beat, tapping process, formation two screw holes；
S3, star sensor is mounted on satellite structure 2 simultaneously by two screws and step S2 two screw holes formed
Carry out precision coarse adjustment；
S4, precision measure is carried out to star sensor and carries out precision accurate adjustment；
S5, precision are adjusted to claimed range, are tightened diagonal screw and are applied the torque of requirement；
S6, satellite structure progress pin hole is manufactured by two holes of residue on star sensor；
S7, the mounting pin screw 3 at two pin holes, 3 one end of pin screw sequentially pass through the plain cushion 4, pin hole, Φ 5 of Φ 6
Plain cushion 5, spring washer 6 be threaded with nut 7, tighten nut 7 and apply screw-down torque；
S8, dispensing sealing is carried out to screw and pin screw.
The step S6 is manufactured according to the pin hole that following rule carries out satellite structure：
It is calculated in the step according to the installation foot thickness t1 of star sensor, the installation foot thickness t2 of mounting surface structure
Sell the length specification of screw；Length l=n (plain cushion quantity) × t3 (plain cushion thickness)+t1+ (0.5~0.75) × t2 of section is sold,
Therefore pin screw length l1=l+b (screw thread segment length), wherein b=a (groove width)+t3 (plain cushion thickness)+t4 (spring washer thickness)
+ (1.5~2) × t5 (nut thickness).
When being originally embodied in the assembly of the high-precisions single machines such as satellite enterprising planet sensor, star sensor three can be effectively ensured
A rotational freedom is especially the precision stability on optical axis pointing direction, and the above technology is set in practical application especially engineering
In meter very intuitively, conveniently, it can effectively ensure that the repetition installation accuracy of star sensor.
In conclusion the present invention is realized when being assembled on carrying out star sensor star by the way of " screw+pin screw "
The high precision high stability degree of star sensor fills star, and the design of satellites technology creation of Rotating Platform for High Precision Star Sensor is subsequently equipped with for China
One new design method, there is the wider scope of application in engineering.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (2)
1. spaceborne star sensor high precision high stability degree installation method, which is characterized in that include the following steps：
S1, processing and fabricating star sensor mounting structure is molded using carbon fibre material, and thread tapping is reserved in corresponding position；
S2, the star sensor mounting structure at two corresponding positions of diagonal mounting hole of star sensor accurate measurement prism is matched
It beats, tapping process, forms two screw holes；
S3, star sensor is mounted on satellite structure by two screws and step S2 two screw holes formed and carries out essence
Spend coarse adjustment；
S4, precision measure is carried out to star sensor and carries out precision accurate adjustment；
S5, precision are adjusted to claimed range, are tightened diagonal screw and are applied the torque of requirement；
S6, satellite structure progress pin hole is manufactured by two holes of residue on star sensor；
S7, the mounting pin screw at two pin holes, and tightened by plain cushion, spring washer, nut and apply screw-down torque；
S8, dispensing sealing is carried out to screw and pin screw.
2. spaceborne star sensor high precision high stability degree installation method according to claim 1, which is characterized in that the step
Rapid S6 is manufactured according to the pin hole that following rule carries out satellite structure：
Due to：Length l=n (plain cushion quantity) × t3 (plain cushion thickness)+t1+ (0.5~0.75) × t2 for selling section, in formula：T1 is
Installation foot thickness, t2 are the installation foot thickness of mounting surface structure；Therefore
Sell screw length l1=l+b (screw thread segment length), wherein (spring washer is thick by b=a (groove width)+t3 (plain cushion thickness)+t4
Degree)+(1.5~2) × t5 (nut thickness).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810202225.3A CN108583935B (en) | 2018-03-12 | 2018-03-12 | High-precision and high-stability mounting method for satellite-borne star sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810202225.3A CN108583935B (en) | 2018-03-12 | 2018-03-12 | High-precision and high-stability mounting method for satellite-borne star sensor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108583935A true CN108583935A (en) | 2018-09-28 |
| CN108583935B CN108583935B (en) | 2020-07-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810202225.3A Active CN108583935B (en) | 2018-03-12 | 2018-03-12 | High-precision and high-stability mounting method for satellite-borne star sensor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117963167A (en) * | 2024-04-02 | 2024-05-03 | 北京航空航天大学 | Pose adjusting method combining coarse adjustment and fine adjustment of space coiled stretching arm |
Citations (5)
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|---|---|---|---|---|
| US5878358A (en) * | 1994-03-17 | 1999-03-02 | Mp Research Ltd. | Data processor for selecting data elements having the highest magnitude values and storing them in ascending order |
| US8265804B1 (en) * | 2009-05-29 | 2012-09-11 | The Boeing Company | Method and system for controlling a vehicle |
| CN104443435A (en) * | 2014-11-21 | 2015-03-25 | 上海卫星工程研究所 | Star sensor mounting structure for thermal deformation isolation and control |
| CN204555988U (en) * | 2015-03-19 | 2015-08-12 | 北京航天计量测试技术研究所 | A kind of high repetitive positioning accuracy mechanism of vacuum plant hatch door |
| 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 |
-
2018
- 2018-03-12 CN CN201810202225.3A patent/CN108583935B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5878358A (en) * | 1994-03-17 | 1999-03-02 | Mp Research Ltd. | Data processor for selecting data elements having the highest magnitude values and storing them in ascending order |
| US8265804B1 (en) * | 2009-05-29 | 2012-09-11 | The Boeing Company | Method and system for controlling a vehicle |
| CN104443435A (en) * | 2014-11-21 | 2015-03-25 | 上海卫星工程研究所 | Star sensor mounting structure for thermal deformation isolation and control |
| CN204555988U (en) * | 2015-03-19 | 2015-08-12 | 北京航天计量测试技术研究所 | A kind of high repetitive positioning accuracy mechanism of vacuum plant hatch door |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 朱华: "《基于半刚性连接的提高星敏感器指向精度的安装设计》", 《中国空间科学技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117963167A (en) * | 2024-04-02 | 2024-05-03 | 北京航空航天大学 | Pose adjusting method combining coarse adjustment and fine adjustment of space coiled stretching arm |
| CN117963167B (en) * | 2024-04-02 | 2024-05-28 | 北京航空航天大学 | Pose adjusting method combining coarse adjustment and fine adjustment of space coiled stretching arm |
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| Publication number | Publication date |
|---|---|
| CN108583935B (en) | 2020-07-14 |
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