CN109050977B - High-orbit satellite final assembly method based on double-component unified propulsion system - Google Patents
High-orbit satellite final assembly method based on double-component unified propulsion system Download PDFInfo
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- CN109050977B CN109050977B CN201810709132.XA CN201810709132A CN109050977B CN 109050977 B CN109050977 B CN 109050977B CN 201810709132 A CN201810709132 A CN 201810709132A CN 109050977 B CN109050977 B CN 109050977B
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- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000003466 welding Methods 0.000 claims abstract description 30
- 230000002427 irreversible effect Effects 0.000 claims abstract description 4
- 238000005192 partition Methods 0.000 claims description 9
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000009413 insulation Methods 0.000 claims description 6
- 239000003990 capacitor Substances 0.000 claims description 5
- 238000001514 detection method Methods 0.000 claims description 4
- 239000003973 paint Substances 0.000 claims description 2
- 238000013102 re-test Methods 0.000 claims description 2
- 238000003754 machining Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000010354 integration Effects 0.000 description 4
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
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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
- B64G1/40—Arrangements or adaptations of propulsion systems
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Abstract
The invention provides a high orbit satellite final assembly method based on a two-component unified propulsion system, which comprises the steps of star structure assembly, propulsion product welding and thermal control product final assembly, wherein the star structure assembly and the propulsion product welding are implemented in two stages, namely I stage and II stage, and the star structure assembly I stage, the propulsion product welding I stage, the star structure assembly II stage and the propulsion product welding II stage are implemented in sequence; the thermal control products comprise a propulsion thermal control product and a star structure thermal control product, and are alternately implemented in the whole assembly process according to the principle that the process is irreversible. The process of the invention is beneficial to improving the final assembly efficiency and ensuring the final assembly precision and the product quality. Through engineering practice, the assembly process of the invention has good harmony, high assembly efficiency, and powerful guarantee on product installation precision and redundancy control.
Description
Technical Field
The invention relates to a satellite assembly process, which takes the assembly of a certain high orbit satellite platform as a prototype and is suitable for the process of a satellite based on a two-component unified propulsion system.
Background
The satellite two-component unified propulsion system has the advantages that the matching quantity of products is large, the layout of the propulsion component assemblies is compact, and the connecting pipelines between the component assemblies are inserted in the star structure in a high-density mode, so that the assembly processes of the products among the three systems, namely the structure, the thermal control system and the propulsion system, are mutually influenced, and the complete independence of the assembly processes cannot be realized.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a high-orbit satellite assembly method based on a two-component unified propulsion system, which meets the requirements of high-efficiency and intensive assembly efficiency, ensures the assembly precision of a satellite structure, promotes the realization and stable control of the assembly precision of a product, and relates to the assembly process of the satellite structure assembly, the propulsion of product welding and the integration of a thermal control product.
The technical scheme adopted by the invention is as follows:
a high orbit satellite final assembly method based on a two-component unified propulsion system comprises the following steps:
the star structure assembling and the propelling product welding are implemented in two main stages I/II, and a propelling product welding process is inserted between the two structure assembling stages.
The precision of the outer surface mechanical interface of the star structure is completed before the stage II of propelling product welding by combined processing.
The thermal control product is inserted in the whole assembly process according to the principle that the process is irreversible.
The storage tank and the gas cylinder are preassembled in the process of the star structure assembling stage I, formal assembling is carried out in the process of the propelling product welding assembling stage I, and a storage tank precision retest and adjustment link is set.
And the attitude control thruster is precisely assembled in place at one time before the stage II of propelling the product welding.
The engine is pre-assembled in place before the stage II of propelling the product welding and assembling, and is subjected to fine assembly in place before leakage detection.
And finally implementing a thermal control product and fixing a pipeline after pushing leak detection.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a high orbit satellite final assembly process based on a two-component unified propulsion system, and relates to implementation of high-density cross assembly of a satellite structure, thermal control and propulsion products. The final assembly of the star structure and the propulsion product is implemented in different places/fields, and the thermal control product is also implemented in the star structure and the propulsion product according to design requirements, so that the characteristics of high integration, interactive alternate implementation and back-and-forth transportation of star structure assembly, propulsion product welding and thermal control product integration are formed, the final assembly process is comprehensively optimized and designed, and the final assembly efficiency, the product installation precision and redundancy control are ensured. The star structure and the propulsion system product are subjected to final assembly in two stages in a cross implementation mode, and the integration of the thermal control system product runs through the whole final assembly process according to the special requirements of an irreversible procedure. The process of the invention is beneficial to improving the final assembly efficiency and ensuring the final assembly precision and the product quality. Through engineering practice, the assembly process of the invention has good harmony, high assembly efficiency, and powerful guarantee on product installation precision and redundancy control.
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 a schematic view of a star structure and propulsion components provided by an embodiment of the present invention;
FIG. 2 is a schematic diagram of an assembly process provided by an embodiment of the present invention;
FIG. 3 is a schematic diagram of states of various stages provided by the embodiment of the present invention;
wherein (a) is a star structure assembly I stage state schematic;
(b) the state of the I stage of welding the propulsion product is indicated;
(c) assembling a star structure with a II stage state schematic;
(d) the state of the propulsion product in the welding II stage is indicated;
fig. 4 is a schematic diagram of a main structure of a star body and propulsion components according to an embodiment of the present invention.
In the figure: 1-a top plate; 2-southeast side plate; 3-northeast side plate; 4-south side plate; 5-star main structure; 6-propelling the product; 7-southwest side plate; 8-northwest side plate; 9-north side plate; 10-a gas cylinder; 11-upper spacer frame; 12-attitude control thrusters; 13-a storage tank; 14-mounting an instrument mounting plate; 15-air volume; 16-a tank mounting plate; 17-lower instrument mounting plate; 18-a lower bulkhead; 19-a base plate; 20-bearing cylinder; 21-a ring line; 22-a remote site engine; 23-a propulsion assembly.
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 it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
FIG. 1 is a schematic diagram of a star structure and propulsion components, and propulsion products are all mounted on the star main structure.
The star body main structure 5 adopts a structural composition form of a central bearing cylinder 20+ an upper partition frame 11/a lower partition frame 18+ a bottom plate 19, the plane section is hexagonal, the star body main structure divides the longitudinal space into 3 spaces through the bottom plate 19, a lower instrument mounting plate 17, an upper instrument mounting plate 14 and the top plate 1, the longitudinal space is divided into 2 spaces through the bottom plate 19, a storage tank mounting plate 16 and the top plate 1, and 14 spaces are formed in total.
Other structures of the star include various side plates: the side plate comprises a southeast side plate 2, a northeast side plate 3, a south side plate 4, a southwest side plate 7, a northwest side plate 8 and a north side plate 9.
The propelling product consists of a large component (a storage tank 13, an air bottle 10 and an air capacitor 15), a small component (a control valve and the like), a thruster (an attitude control thruster 12 and a remote engine 22) and a pipeline, and the large component, the small component and the thruster are connected through the pipeline and realize the flow of propelling working media. The propelling small parts are installed on the bottom plate 19 and the storage box installation plate 16, the gas cylinder 10 is installed on the inner side of the bearing cylinder 20, the four storage boxes 13 are installed on the storage box installation plate 16, and the annular pipeline 12 is inserted into structural products such as the upper partition frame 11, the lower partition frame 18 and the bottom plate, as shown in fig. 4.
The thermal control product consists of a propulsion thermal control product and a star-structure thermal control product, wherein the propulsion thermal control product consists of a heating sheet, a thermistor and a multilayer thermal insulation assembly, the heating sheet and the thermistor are adhered to the propulsion products such as a storage tank, an air bottle, an air capacitor, a propulsion small assembly, a thruster and the like, and the surfaces of all the propulsion products are coated with the multilayer thermal insulation assembly. The star-structure thermal control product consists of paint, a heating sheet, a thermistor and a multi-layer heat insulation assembly.
The general assembly process adopted by the invention is shown in the embodiment of fig. 2, after the assembly is completed in the star structure assembly I stage, the product propelling welding I stage is implemented, namely, the connecting pipelines of the storage tank, the gas cylinder, the annular pipeline, the storage tank, the gas cylinder and the gas capacitor are implemented, after the whole assembly is completed in the star structure, the product propelling welding II stage is implemented, and the thermal control implementation and the star assembly precision measurement and adjustment of the product are inserted in the assembly process.
The star structure assembly stage I corresponds to M1 to M14 in fig. 2; the stage I of the propulsion product welding corresponds to M17-M25 in FIG. 2; the star structure assembling stage II corresponds to M28-M35 in FIG. 2; the propulsion product weld ii stage corresponds to M38 through M48 in fig. 2. The corresponding state after assembly of the stages is shown in fig. 3.
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 or 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. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. A high orbit satellite assembly method based on a two-component unified propulsion system is characterized by comprising the steps of star structure assembly, propulsion product welding and thermal control product assembly, wherein the star structure assembly and the propulsion product welding are implemented in two stages, namely I stage and II stage, and the star structure assembly I stage, the propulsion product welding I stage, the star structure assembly II stage and the propulsion product welding II stage are implemented in sequence; the thermal control product comprises a propulsion thermal control product and a star structure thermal control product, and is implemented in the whole assembly process according to the principle that the process is irreversible, wherein: finishing the general assembly of a star main structure, the pre-assembly of a large part of a propelling product and the assembly of a thermal control product on the large part of the propelling product at the stage I of the assembly of the star structure;
the propulsion product welding I stage completes the assembly of a large propulsion product component and the welding of a pipeline, the preassembly of a small propulsion product component and a thruster and the assembly of a heat control product on a welded pipeline;
the assembly of other structures, the assembly of a small component of a propulsion product and a thruster and the assembly of a thermal control product on the star structure are completed in the assembly II stage of the star structure;
the propulsion product welding stage II is used for completing assembly of other propulsion products, propulsion heat control products and pipeline welding;
the propelling product mainly comprises a large part, a small part, a thruster and a pipeline, wherein the large part, the small part and the thruster are connected through the pipeline, the propelling working medium flows, the small part is arranged on a bottom plate and a storage box mounting plate, an upper partition frame and a lower partition frame are of an open structure, a gas cylinder is arranged on the inner side of a force bearing cylinder, 4 storage boxes are arranged on the storage box mounting plate, and the pipeline penetrates through the upper partition frame, the lower partition frame and a cabin plate, wherein the large part comprises a storage box, a gas cylinder and a gas capacitor; the small component comprises a control valve; the thruster comprises a position control thruster and a remote engine, the storage tank and the gas cylinder are preassembled in the process of the stage I of assembling the star body structure, formal assembly is carried out in the process of the stage I of welding and assembling the propulsion product, and a storage tank star-assembling precision retest and adjustment link is arranged; the attitude control thruster is precisely assembled in place for one time before the stage II of propelling the product welding; and the remote engine is preassembled before the stage II of propelling product welding, after propelling welding is completed, the engine is subjected to finish assembling before leakage detection, and the final implementation and pipeline fixation of the thermal control product are performed after propelling leakage detection.
2. The high-orbit satellite assembly method based on the two-component unified propulsion system as claimed in claim 1, wherein the star main structure adopts a structural composition form of a central bearing cylinder, an upper/lower partition frame and a bottom plate, the cross section of the star main structure is hexagonal, the star structure divides the longitudinal space into 3 spaces through the bottom plate, a lower instrument mounting plate, an upper instrument mounting plate and a top plate, and divides the longitudinal space into 2 spaces through the bottom plate, a storage tank mounting plate and the top plate, so that 14 spaces are formed in total; other structures of the star include side panels around the main structure.
3. The method for assembling the high orbit satellite based on the two-component unified propulsion system of claim 1, wherein the precision of the outer surface mechanical interface of the star structure is implemented in the assembly II stage of the star structure through combined machining.
4. The assembly method of the high orbit satellite based on the two-component unified propulsion system as claimed in claim 1, wherein the propulsion thermal control product comprises a heating sheet, a thermistor and a multi-layer heat insulation assembly, the heating sheet and the thermistor are adhered to a storage tank, a gas cylinder, a gas capacitor, a propulsion small assembly and a thruster, and the multi-layer heat insulation assembly is coated on the surface of all the propulsion products; the star-structure thermal control product consists of paint, a heating sheet, a thermistor and a multi-layer heat insulation assembly.
5. The method for assembling a high-orbit satellite based on a two-component unified propulsion system as claimed in claim 1, wherein the assembling of the star structure and the welding of the propulsion products are implemented at different sites.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810709132.XA CN109050977B (en) | 2018-07-02 | 2018-07-02 | High-orbit satellite final assembly method based on double-component unified propulsion system |
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| CN201810709132.XA CN109050977B (en) | 2018-07-02 | 2018-07-02 | High-orbit satellite final assembly method based on double-component unified propulsion system |
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| CN109050977A CN109050977A (en) | 2018-12-21 |
| CN109050977B true CN109050977B (en) | 2020-07-14 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110061343B (en) * | 2019-04-11 | 2020-12-08 | 上海卫星工程研究所 | Combined supporting structure for large antenna of deep space probe |
| CN112705920B (en) * | 2020-12-16 | 2021-08-10 | 中国科学院微小卫星创新研究院 | Satellite assembling method |
| CN112918705B (en) * | 2021-03-12 | 2022-07-12 | 深圳航天东方红卫星有限公司 | Thermal control system and method of integrated propulsion subsystem |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
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| CN102372092A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Configuration for low-earth-orbit remote sensing satellite and mounting method thereof |
| CN106134364B (en) * | 2009-09-29 | 2013-09-04 | 北京卫星制造厂 | A kind of satellite automated mounting plate |
| CN104058102A (en) * | 2014-06-26 | 2014-09-24 | 上海卫星工程研究所 | Eight-rod-connecting type non-contact satellite platform configuration and assembling method |
| CN203996926U (en) * | 2014-04-29 | 2014-12-10 | 上海卫星工程研究所 | A kind of satellite structure of response fast |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN107738760A (en) * | 2017-09-19 | 2018-02-27 | 上海卫星工程研究所 | Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134364B (en) * | 2009-09-29 | 2013-09-04 | 北京卫星制造厂 | A kind of satellite automated mounting plate |
| CN102372092A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Configuration for low-earth-orbit remote sensing satellite and mounting method thereof |
| CN203996926U (en) * | 2014-04-29 | 2014-12-10 | 上海卫星工程研究所 | A kind of satellite structure of response fast |
| CN104058102A (en) * | 2014-06-26 | 2014-09-24 | 上海卫星工程研究所 | Eight-rod-connecting type non-contact satellite platform configuration and assembling method |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN107738760A (en) * | 2017-09-19 | 2018-02-27 | 上海卫星工程研究所 | Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure |
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