CN106542114A - Horizontal barycenter high accuracy ensuring method of the tiling tank satellite in parallel in the AIT stages - Google Patents
Horizontal barycenter high accuracy ensuring method of the tiling tank satellite in parallel in the AIT stages Download PDFInfo
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- CN106542114A CN106542114A CN201610957694.7A CN201610957694A CN106542114A CN 106542114 A CN106542114 A CN 106542114A CN 201610957694 A CN201610957694 A CN 201610957694A CN 106542114 A CN106542114 A CN 106542114A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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Abstract
The invention provides a kind of horizontal barycenter high accuracy ensuring method of tiling tank satellite in parallel in the AIT stages, including：In the Standard stage, Form and position error, the apogee engine support alignment error of tank installing plate are controlled；It is welded the stage in propulsion system, control tank error in mounting position, apogee engine installation site and error in pointing；In the whole star general assembly stage, quality and barycenter of the solar array in deployed condition are controlled；Before dispatching from the factory, the horizontal barycenter test of whole star is carried out by the whole star barycenter test equipment of high accuracy.The present invention implements multinomial horizontal barycenter safeguard measure in whole star AIT each stages, horizontal barycenter of the satellite in outspreading sailboard original state is controlled near origin, and improve the determination precision (less than or equal to 1mm) of the horizontal barycenter of satellite, reduce the horizontal barycenter change of Satellite Orbit Maneuver section, so as to reduce the disturbance torque of apogee engine generation, guarantee that safety becomes rail, meanwhile, save propellant.
Description
Technical field
The present invention relates to satellite general technical field, in particular it relates to a kind of tiling tank satellite in parallel is in AIT
The horizontal barycenter high accuracy ensuring method in (Assembly Integration and Test, general assembly, integrated and test) stage.
Background technology
Determine that on the horizontal barycenter of outspreading sailboard moment satellite precision affects larger to have tank Form and position error, solar array exhibition
Open state barycenter error, apogee engine position and error in pointing, barycenter test error, the wherein impact of tank Form and position error
It is to be caused by the particularity of tank tiling layout in parallel.During Satellite Orbit Maneuver section apogee motor firing, when whole star matter
When the heart is not put on motor power axis in distant, disturbance torque can be produced；With the consumption of propellant, barycenter determines precision meeting
It is deteriorated, i.e., error is constantly exaggerated, the disturbance torque that apogee engine is produced can become big therewith；For tank tiling in parallel is defended
For star, the determination error of horizontal barycenter can be further amplified in the uneven discharge of propellant.Therefore, during satellite AIT
Tank Form and position error, Stretching of solar wings state barycenter error, apogee engine position and error in pointing, barycenter test are missed
Difference implements control, is to reduce the effective means that the horizontal barycenter of outspreading sailboard moment satellite determines precision.
At present, general high rail satellite is controlled to apogee engine position and error in pointing, and centroid of satellite test is missed
Difference is in 2-3mm, but the system approach do not found through the whole star AIT stages determines the report of precision to ensure the horizontal barycenter of satellite
Or technology.
The content of the invention
For defect of the prior art, it is an object of the invention to provide a kind of tiling tank satellite in parallel is in the AIT stages
Horizontal barycenter high accuracy ensuring method.
According to horizontal barycenter high accuracy ensuring method of the tank satellite in the AIT stages that tile in parallel that the present invention is provided, bag
Include following steps：
Step 1：In the Standard stage, controlled by way of Combined machining tank mounting surface to satellite and the rocket parting surface away from
From the combined planar degree that the depth of parallelism and multiple tank mounting surfaces of error and satellite and the rocket parting surface are formed；By repair and pad
The mode adjustment of realizing to apogee engine support, the distance for controlling apogee engine support to satellite and the rocket parting surface misses
Difference, and satellite and the rocket parting surface the depth of parallelism；
Step 2：It is welded the stage in propulsion system, tank position is measured by three-coordinate instrument, and is implemented according to tank position
Adjustment to tank, controls tank distributing position error；By transit survey apogee engine position and sensing, with repair
Implement the adjustment to apogee engine, control apogee engine error in mounting position and error in pointing with the mode of pad；
Step 3：In whole star general assembly stage, quality and barycenter of the actual measurement solar windsurfing in deployed condition, it is desirable to quality test
Error is less than or equal to 0.2kg, and barycenter test error is less than or equal to 3mm；
Step 4：Before dispatching from the factory, the horizontal barycenter test of whole star is carried out by the whole star barycenter test equipment of high accuracy, ground is horizontal
The test error of barycenter test system is less than or equal to 0.5mm.
Preferably, in the Standard stage, control tank mounting surface is less than or equal to the range error of satellite and the rocket parting surface
The parallelism error of 0.5mm and satellite and the rocket parting surface is less than or equal to 1.0mm, and the combined planar degree that multiple tank mounting surfaces are formed is missed
Difference is less than or equal to 0.5mm and the satellite and the rocket point less than or equal to 0.5mm, the range error of apogee engine support to satellite and the rocket parting surface
Parallelism error from face is less than or equal to 0.1mm.
Preferably, it is welded the stage in propulsion system, control tank distributing position error is less than or equal to 0.5mm, apogee is sent out
Motivation error in mounting position is less than or equal to 0.2mm and error in pointing is less than or equal to 1 '.
Compared with prior art, the present invention has following beneficial effect：
The present invention implements multinomial horizontal barycenter safeguard measure in whole star AIT each stages, by satellite in outspreading sailboard initial shape
The horizontal barycenter of state is controlled near origin, and improves the determination precision (less than or equal to 1mm) of the horizontal barycenter of satellite, is reduced and is defended
Star becomes the horizontal barycenter change of rail section, so as to reduce the disturbance torque of apogee engine generation, it is ensured that safety becomes rail, meanwhile,
Save propellant.
Description of the drawings
Detailed description non-limiting example made with reference to the following drawings by reading, the further feature of the present invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the schematic flow sheet of method in the present invention；
Fig. 2 is certain satellite model apogee engine and its support scheme of installation.
In figure：
1- apogee engines.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, some changes and improvements can also be made.These belong to the present invention
Protection domain.
The present invention tiles tank satellite in AIT ranks by solving the parallel connection that the technical scheme that its technical problem is adopted is to provide
The horizontal barycenter high accuracy ensuring method of section, it is specific as follows：
1) in the Standard stage, the distance that tank mounting surface to satellite and the rocket parting surface is controlled by way of Combined machining is missed
Difference is less than or equal to 1.0mm, the group that multiple tank mounting surfaces are formed less than or equal to the parallelism error of 0.5mm and satellite and the rocket parting surface
Close flatness error and be less than or equal to 0.5mm；The adjustment to apogee engine support is realized by way of repair and pad, is controlled
The range error of apogee engine support processed to satellite and the rocket parting surface is less than or equal to 0.5mm and the depth of parallelism of satellite and the rocket parting surface is missed
Difference is less than or equal to 0.1mm.
2) it is welded the stage in propulsion system, tank position is measured by three-coordinate instrument and implements the adjustment to tank accordingly,
Control tank distributing position error is less than or equal to 0.5mm；By transit survey apogee engine position and sensing, and
Implement the adjustment to apogee engine in the way of repair and pad, control apogee engine error in mounting position less than etc.
1 ' is less than or equal in 0.2mm and error in pointing.
3) in the whole star general assembly stage, quality and barycenter of the actual measurement solar windsurfing in deployed condition, it is desirable to quality test error
Less than or equal to 0.2kg, barycenter test error is less than or equal to 3mm.
4), before dispatching from the factory, horizontal barycenter test, the horizontal barycenter test in ground are carried out by the whole star barycenter test equipment of high accuracy
The test error of system is less than or equal to 0.5mm.
Specifically, four propellant tanks are separately mounted on two pieces of tank installing plates, two using tiling layout in parallel
The position of oxidant tank represents that with A1 and B1 two incendiary agent tank positions are represented with A2 and B2, is symmetrically distributed in radius for r
On the circle of=960mm.
In the Standard stage, to 4 tank mounting surface compositions on tank installing plate by way of Combined machining
Plane is combined processing, makes the range error of tank mounting surface to satellite and the rocket parting surface less than or equal to 0.5mm, with satellite and the rocket parting surface
Parallelism error be less than or equal to 1.0mm, the combined planar degree error of the plane of 4 tank mounting surfaces composition is less than or equal to
0.5mm；The adjustment to apogee engine support is realized by way of repair and pad, makes to send out on apogee engine support
The mounting flange face of motivation is less than or equal to 0.1mm, apogee engine mounting surface and star with the parallelism error of satellite and the rocket parting surface
Arrow parting surface range error is less than or equal to 0.5mm.
It is welded the stage in propulsion system, tank position is measured by three-coordinate instrument and implements the adjustment to tank accordingly, made
The installation site of tank meets 960 ± 0.5mm of distribution radius, the requirement of 30 ± 0.05 ° of distribution angle；It is remote by transit survey
Place engine location and sensing, and implement the adjustment to apogee engine in the way of repair and pad, obtain after making heat mark
The thrust vectoring for arriving is coaxial with satellite+Z axis (shown in Fig. 2), and the installation site deviation of X and Y-direction under co-ordinates of satellite is less than or equal to
0.2mm, motor power vector are better than 1 ' with satellite+Z axis angular deviation.
In whole star general assembly stage, quality and barycenter of the actual measurement solar windsurfing in deployed condition, it is desirable to which quality test error is little
In equal to 0.2kg, barycenter test error is less than or equal to 3mm, controls installation accuracy of the solar array on star.
Before dispatching from the factory, horizontal barycenter test, the horizontal barycenter test system in ground are carried out by the whole star barycenter test equipment of high accuracy
The test error of system is less than or equal to 0.5mm.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make a variety of changes within the scope of the claims or change, this not shadow
Ring the flesh and blood of the present invention.In the case where not conflicting, the feature in embodiments herein and embodiment can any phase
Mutually combine.
Claims (3)
1. horizontal barycenter high accuracy ensuring method of a kind of tiling tank satellite in parallel in the AIT stages, it is characterised in that include as
Lower step：
Step 1：In the Standard stage, the distance that tank mounting surface to satellite and the rocket parting surface is controlled by way of Combined machining is missed
Difference, and satellite and the rocket parting surface the depth of parallelism and multiple tank mounting surfaces formed combined planar degree；By repair and the side of pad
Formula realizes adjustment to apogee engine support, control apogee engine support to satellite and the rocket parting surface range error and
The depth of parallelism of satellite and the rocket parting surface；
Step 2：It is welded the stage in propulsion system, tank position is measured by three-coordinate instrument, and is implemented to storage according to tank position
The adjustment of case, controls tank distributing position error；By transit survey apogee engine position and sensing, with repair and pad
The mode of piece implements the adjustment to apogee engine, control apogee engine error in mounting position and error in pointing；
Step 3：In whole star general assembly stage, quality and barycenter of the actual measurement solar windsurfing in deployed condition, it is desirable to quality test error
Less than or equal to 0.2kg, barycenter test error is less than or equal to 3mm；
Step 4：Before dispatching from the factory, the horizontal barycenter test of whole star, the horizontal barycenter in ground are carried out by the whole star barycenter test equipment of high accuracy
The test error of test system is less than or equal to 0.5mm.
2. horizontal barycenter high accuracy ensuring method of the tiling tank satellite in parallel according to claim 1 in the AIT stages, its
Be characterised by, in the Standard stage, control tank mounting surface to satellite and the rocket parting surface range error be less than or equal to 0.5mm and
The parallelism error of satellite and the rocket parting surface is less than or equal to 1.0mm, the combined planar degree error that multiple tank mounting surfaces are formed less than etc.
In 0.5mm, the range error of apogee engine support to satellite and the rocket parting surface is less than or equal to the flat of 0.5mm and satellite and the rocket parting surface
Row degree error is less than or equal to 0.1mm.
3. horizontal barycenter high accuracy ensuring method of the tiling tank satellite in parallel according to claim 1 in the AIT stages, its
It is characterised by, is welded the stage in propulsion system, control tank distributing position error is less than or equal to 0.5mm, apogee engine peace
Holding position error is less than or equal to 0.2mm and error in pointing is less than or equal to 1 '.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610957694.7A CN106542114B (en) | 2016-11-03 | 2016-11-03 | Lateral mass center high-precision ensuring method of the parallel connection tiling tank satellite in the AIT stage |
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| CN201610957694.7A CN106542114B (en) | 2016-11-03 | 2016-11-03 | Lateral mass center high-precision ensuring method of the parallel connection tiling tank satellite in the AIT stage |
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| CN106542114B CN106542114B (en) | 2019-05-03 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791957A (en) * | 2018-06-14 | 2018-11-13 | 上海卫星工程研究所 | A kind of lateral barycenter high-precision real-time identification method during Satellite Orbit Maneuver |
| CN111562124A (en) * | 2020-05-07 | 2020-08-21 | 上海宇航系统工程研究所 | Precision measurement method for storage tank flat-laying configuration spacecraft |
| CN112705920A (en) * | 2020-12-16 | 2021-04-27 | 中国科学院微小卫星创新研究院 | Satellite assembling method |
| CN113148235A (en) * | 2020-01-09 | 2021-07-23 | 中国空间技术研究院 | Method for adjusting transverse mass center of satellite of parallel storage box |
| CN116395148A (en) * | 2023-03-20 | 2023-07-07 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
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| CN103693213A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Magnetic tape type satellite mass center regulating mechanism |
| CN104401506A (en) * | 2014-10-23 | 2015-03-11 | 上海卫星工程研究所 | Zero-counterweight barycenter deploying method for parallel tiling tank satellite |
| CN104458123A (en) * | 2014-11-03 | 2015-03-25 | 上海卫星工程研究所 | Method for calculating satellite barycenter by utilizing mass and barycenter information of part |
| CN106516167A (en) * | 2016-11-03 | 2017-03-22 | 上海卫星工程研究所 | High precision propellant filling method for high orbit satellite with parallel-connection flat-laid storage tanks |
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| CN103693213A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Magnetic tape type satellite mass center regulating mechanism |
| CN104401506A (en) * | 2014-10-23 | 2015-03-11 | 上海卫星工程研究所 | Zero-counterweight barycenter deploying method for parallel tiling tank satellite |
| CN104458123A (en) * | 2014-11-03 | 2015-03-25 | 上海卫星工程研究所 | Method for calculating satellite barycenter by utilizing mass and barycenter information of part |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791957A (en) * | 2018-06-14 | 2018-11-13 | 上海卫星工程研究所 | A kind of lateral barycenter high-precision real-time identification method during Satellite Orbit Maneuver |
| CN108791957B (en) * | 2018-06-14 | 2020-10-27 | 上海卫星工程研究所 | High-precision real-time identification method for transverse mass center during satellite orbit transfer |
| CN113148235A (en) * | 2020-01-09 | 2021-07-23 | 中国空间技术研究院 | Method for adjusting transverse mass center of satellite of parallel storage box |
| CN111562124A (en) * | 2020-05-07 | 2020-08-21 | 上海宇航系统工程研究所 | Precision measurement method for storage tank flat-laying configuration spacecraft |
| CN112705920A (en) * | 2020-12-16 | 2021-04-27 | 中国科学院微小卫星创新研究院 | Satellite assembling method |
| CN116395148A (en) * | 2023-03-20 | 2023-07-07 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
| CN116395148B (en) * | 2023-03-20 | 2023-09-15 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
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