CN104354874A - Unitization structure assembling method for disassembly and reassembly through flexible traction - Google Patents
Unitization structure assembling method for disassembly and reassembly through flexible traction Download PDFInfo
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- CN104354874A CN104354874A CN201410381753.1A CN201410381753A CN104354874A CN 104354874 A CN104354874 A CN 104354874A CN 201410381753 A CN201410381753 A CN 201410381753A CN 104354874 A CN104354874 A CN 104354874A
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Abstract
The invention discloses a unitization structure assembling method for disassembly and reassembly through flexible traction. The method comprises the following steps: assembling an electronic cabin, namely establishing a reference on a platform bottom plate, mounting each plate in place, performing adhesion, and scribing a quadrant line; assembling a propulsion cabin, namely assembling the propulsion cabin and the electronic cabin in parallel, establishing a complete satellite reference, riveting all shells of the propulsion cabin, and performing combination processing; butting the electronic cabin with the propulsion cabin, namely arranging the propulsion cabin on the butting surface of star arrows, hoisting the propulsion cabin, and aligning the quadrant line of the electronic cabin with the complete satellite reference; performing combination processing, namely establishing a coordinate system by taking the complete satellite reference on the propulsion cabin as the reference, and milling a plane; performing disassembly, reassembly and precision re-measurement on cabin sections, namely performing disassembly, reassembly and precision re-measurement on the electronic cabin for two times. According to the method, the independence of the cabin sections can be realized, the assembly period is shortened, the precision of all parts under the complete satellite reference after all cabin bodies are butted is guaranteed, the disassembly and reassembly precision of each cabin section is achieved, the separation positioning engagement of the cabins is avoided, and long-time overhead operation is avoided.
Description
Technical field
The present invention relates to a kind of flexible drawing to carry out decomposing the having unit structure assembly method reassembled, belong to space product Standard technical field.
Background technology
Satellite structure portion dress is the assembling of structure subsystem, under satisfied installation connection provides the prerequisite of integral structure precision, also provides the mounting interfaces such as high-precision satellite-rocket docking, solar wing, equipment, antenna, propulsion system.
Standard is a key link in whole satellite production process, serves the effect of taking over from the past and setting a new course for the future.Brought forward: Standard is by the structure carrier that be connected to become meet requirements of accuracy requirement by part; Qi Hou: Standard is not only simple is connected to become carrier by part, also will relate to celestial body structural entity precision, multiple mechanism, equipment attachment face precision, the quality assurance problem of the aspects such as the mechanical property of the entirety of celestial body and safety assurance, the precision of its propulsion system of loading after directly affecting, capacity weight and safety.
Summary of the invention
Technical matters to be solved by this invention is: for overcoming the deficiencies in the prior art, a kind of flexible drawing is provided to carry out decomposing the having unit structure assembly method reassembled, realize the section makeup of space product structure cabin with this to join, and make the structure of each cabin section and interface meet the accuracy requirement under the standard of whole satellite-based.
Technical solution of the present invention is:
Flexible drawing carries out decomposing the having unit structure assembly method reassembled, and it is characterized in that: structure to be assembled is divided into electronic compartment and propulsion module two cabin sections, and this assembly method step is:
The first step: electronic compartment, propulsion module concurrent assembly
Electronic compartment assembles: on platform floor, build benchmark, first platform floor and the platform cabin dividing plate of electronic compartment bottom are installed afterwards, secondly load ceiling board and the dividing plate on electronic compartment top are installed, again outer panel and load ceiling board are installed, outer panel comprises the+Y side plate ,-Y side plate ,+Z side plate and the-Z side plate that are connected with platform cabin dividing plate, after above-mentioned each structural slab is in place, glueds joint pin bush between plate, and carve quadrant line on electronic compartment outer panel;
Propulsion module assembles: set up and record whole satellite-based standard, riveting each housing of propulsion module and Combined machining, install the hydrazine bottle rack in propulsion module after trial assembly, adjust whole satellite-based accurate, assembling is used for the hydrazine bottle rack pull bar fixing hydrazine bottle rack;
Second step: electronic compartment docks with propulsion module
Propulsion module is placed on satellite-rocket docking face, electronic compartment is lifted by flexible hanger, accurate for benchmark with whole satellite-based, is alignd by electronic compartment quadrant line with whole satellite-based standard, ensure that right alignment is not more than φ 0.5, electronic compartment is docked with propulsion module, checks electronic compartment and propulsion module butt-joint clearance, when the two gap is less than 0.1mm, tie bolt is installed, and then the strut joint and strut assembly that connect electronic compartment are installed, measure satellite-rocket docking size, the installation of adjustment strut assembly; With pin, the hole on platform floor is connected with the hole on propulsion module, glueds joint two cabin connecting pin guidees; Set up the optical reference of solar wing: accurate by above-mentioned whole satellite-based, sticky prism square on platform floor, ensure that accurate three coordinates in three seamed edges of prism square and whole satellite-based are parallel, utilize prism square that windsurfing driver train support and windsurfing driver train are installed;
3rd step: Combined machining
Accurate for benchmark with satellite-based whole on propulsion module, determine axis of revolution 0 ° of direction of numerically-controlled machine tool, set up system of axes, milling be provided with solar wing ± Y side plate, the load ceiling board (14) of camera is installed and load ceiling board (12) ,+Z side plate (16) of antenna is installed, milling drilling also records data;
4th step: section decomposition in cabin reassembles and precision repetition measurement
Before each structural slab decomposes to electronic compartment be provided with solar wing ± lower surface of Y side plate and propulsion module carries out the precision repetition measurement of a size, repetition measurement value is as a reference value, then to carrying out twice decomposition between electronic compartment and two cabins, reassembling and precision repetition measurement, contrast decomposition reassembles front and back precision change, if variation error controls between ± 0.01mm, then verify that flexible drawing carries out decomposing the assembly precision good stability reassembled; If variation error do not drop on ± 0.01mm between, then get back to the first step, till repetition measurement value controls between ± 0.01mm.
In electronic compartment fitting process, the method that platform floor is built benchmark is: with the intersection point of the diagonal line line of platform floor for coordinate origin, platform floor face is built Y-axis and Z axis, sets up Z axis with vertical platform base plate direction.
Determine that the method for whole satellite-based standard is in propulsion module assembling: the mid point getting two pin-and-hole lines on the lower surface of propulsion module is coordinate origin, X-axis is perpendicular to satellite-rocket docking face, Z, Y-axis are positioned on the lower surface of propulsion module, and Z, Y direction are determined by the angle of two pin-and-hole lines of centres and coordinate axle.
In electronic compartment and propulsion module docking operation, before the installation of tie bolt, to assembly stress be eliminated, avoid assembly connection point to concentrate as stress, when electronic compartment and propulsion module attaching screw are tightened with dynamometry, must carry out symmetrically.
Milling in Combined machining process is undertaken by following parameters: a. cutter rotating speed 200-300 rev/min; B. feed 50-60mm/ divides; C. cutting depth≤0.1mm; Lathe is undertaken by counterboring with step core drill mode when boring machining hole; During D≤the φ 6 of aperture, each cutter footpath increment is not more than 3; During φ 6< aperture D≤φ 10, each cutter footpath increment is not more than 2; During φ 10< aperture D≤φ 15, each cutter footpath increment is not more than 1.5.
The present invention's advantage is compared with prior art:
(1) the present invention each cabin section independence, concurrent assembly, saved the time of setting up of cabin section, shortens assembly period;
(2) propulsion module of the present invention is directly installed processing according to whole satellite-based standard and be ensure that the precision of propulsion module under the standard of whole satellite-based; Electronic compartment is assembled by inverting reference, and by quadrant groove, the accuracy requirement of guarantee electronic compartment under the standard of whole satellite-based is installed to neat satellite-based standard, by the crucial accuracy requirement of Combined machining guarantee electronic compartment under the standard of whole satellite-based under whole starlike state after two cabin docking, avoid the accumulated error progressively increased in fitting process;
(3) the present invention two cabin is located by connecting to adopt and installs locating dowel pin at propulsion module, electronic compartment glueds joint the method location of pin bush location according to the actual relative position in two cabins, the splicing of guide adopts direct Opposite direction connection, improves the safety performance of product, without the need to producing special celestial body turning device;
(4) invention unit makeup is joined, and the equal <1.5m of single cabin height, single cabin assembling stage personnel not be used in the enterprising line operate of lift car, avoid long-time aloft work, greatly improve the safety of production.
Accompanying drawing explanation
Fig. 1 is electronic compartment of the present invention and propulsion module structural representation;
Fig. 2 is propulsion module front view of the present invention;
Fig. 3 is electronic compartment birds-eye view of the present invention;
Fig. 4 is hydrazine bottle rack unit construction schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing and be that the present invention will be further described for embodiment.
Flexible drawing carries out decomposing the having unit structure assembly method reassembled, and structure to be assembled is divided into electronic compartment and propulsion module two cabin sections, and this assembly method step is:
The first step: electronic compartment, propulsion module concurrent assembly
Electronic compartment assembles: on platform floor 18, build benchmark, with the intersection point of the diagonal line line of platform floor 18 for coordinate origin, platform floor 18 builds Y-axis and Z axis, set up Z axis with vertical platform base plate 18 direction; On the vertical Z direction of principal axis of platform floor 18, the long dividing plate of installation+Z 3, the long dividing plate of the long dividing plate 5, two of-Z are centrosymmetric; Installing+Z breviseptum 17 and-Z breviseptum 8 perpendicular on two long dividing plate directions, median septum 4 is installed on simultaneously perpendicular between two long dividing plates, forms a plane with ± Z breviseptum; Installed load ceiling board 14 on above-mentioned 5 pieces of platform cabin dividing plates; Load ceiling board 14 is built as the benchmark on platform floor 18, and the long dividing plate 10 in the load cabin that attachment face is vertical on load ceiling board 14 and load cabin breviseptum 11 two pieces of dividing plates; Perpendicular to Z-direction ,+Z side plate 16 ,-Z side plate 9 are being installed afterwards; + Y side plate 7 ,-Y side plate 13 are installed perpendicular to Y direction, are positioned at the little side plate of+Y 6, the little side plate 15 of-Y in+Y side plate 7 ,-Y side plate 13 respectively, perpendicular to X-direction installed load ceiling board 12, after above structural slab is in place, be fixedly connected with each structural slab and glued joint pin bush between plate, forming one electronic compartment; Electronic compartment ± Y side plate and ± Z side plate on carve Y-axis and Z axis quadrant line.
Propulsion module assembles: set up and record whole satellite-based standard, three-dimensional system of coordinate is set up in the satellite-rocket docking face be connected with propulsion module lower frame 21, the mid point getting two pin-and-hole lines on satellite-rocket docking face (i.e. the lower surface of propulsion module) is coordinate origin, X-axis is perpendicular to satellite-rocket docking face, Z, Y-axis is positioned on satellite-rocket docking face, Z, Y direction is determined by the angle of two pin-and-hole lines of centres and coordinate axle, riveted joint propulsion module housing 1 also Combined machining, hydrazine bottle rack 2 is installed after trial assembly, the fastening mode of symmetrical assembling is taked to carry out, pad is used between hydrazine bottle rack 2 and propulsion module housing 1, guarantee the low stress assembling of hydrazine bottle rack 2, adjust whole satellite-based accurate, the hydrazine bottle rack pull bar (hydrazine bottle rack assembly 23 comprises hydrazine bottle rack 2 and hydrazine bottle rack pull bar) being used for fixing hydrazine bottle rack 2 is installed, by monitoring the lower frame 21 satellite-rocket docking size of propulsion module and regulating assembly relation, realize the assembling of propulsion module low stress.
Second step: electronic compartment docks with propulsion module
Propulsion module is placed on satellite-rocket docking face, electronic compartment is lifted by flexible hanger, accurate for benchmark with whole satellite-based, electronic compartment quadrant line is alignd with whole satellite-based standard, ensure that right alignment is not more than φ 0.5, electronic compartment is docked with propulsion module, check electronic compartment and propulsion module butt-joint clearance, when the two gap is less than 0.1mm, tie bolt is installed, the installation of tie bolt can not be had a contest, assembly stress will be eliminated before the installation of i.e. tie bolt, assembly connection point is avoided to concentrate as stress, the link bolt hole of file propulsion module upper ledge 20 can be repaiied, when electronic compartment and propulsion module attaching screw are tightened with dynamometry, must carry out symmetrically.And then the strut joint and strut assembly 24 that connect electronic compartment are installed, measure satellite-rocket docking size, the installation of adjustment strut assembly 24; The glue (914A, 914B are two kinds of components of 914 lining cements) of 0.6h ~ 0.8h allotment in advance weight ratio 914A:914B: aluminium powder=6:1:6, regulate the flowing power of glue to find Qi Yuyu to glued joint face by engineer testing interpolation, proportioning thickening agent to fill, the equilibrium point between adhesive strength; By controlling to join glue in advance, reducing glue flowing power, avoiding gummosis, achieve oppositely (dorsad direction, the earth's core) sticky guide, ensure intersegmental location, cabin, reseting precision; With pin, the hole on platform floor (18) is connected with the hole on propulsion module, glueds joint two cabin connecting pin 19 guidees; Set up the optical reference of solar wing: accurate by above-mentioned whole satellite-based, sticky prism square on platform floor 18, ensure that accurate three coordinates in 3 seamed edges of prism square and whole satellite-based are parallel, utilize prism square that windsurfing driver train support and windsurfing driver train are installed.
3rd step: Combined machining:
Solar wing is installed on celestial body ± Y side plate, camera is installed on load ceiling board 14, load ceiling board 12 and+Z side plate are provided with antenna, accurate for benchmark with satellite-based whole on propulsion module, the axis of revolution being numerically-controlled machine tool with+Z quadrant 0 ° of direction, set up system of axes, milling ± Y side plate, load ceiling board 14, load ceiling board 12 and+Z side plate, drilling also records data.Milling is undertaken by following parameters: a. cutter rotating speed 200-300 rev/min; B. feed 50-60mm/ divides; C. cutting depth≤0.1mm; Lathe is undertaken by counterboring with step core drill mode when boring machining hole; During D≤the φ 6 of aperture, each cutter footpath increment is not more than 3; During φ 6< aperture D≤φ 10, each cutter footpath increment is not more than 2; During φ 10< aperture D≤φ 15, each cutter footpath increment is not more than 1.5.
4th step: section decomposition in cabin reassembles and precision repetition measurement
(do not need all structural slabs all to decompose before each structural slab decomposes, for the structural slab gluedd joint, then without the need to splitting), to electronic compartment be provided with solar wing ± lower surface (i.e. satellite-rocket docking face) of Y side plate and propulsion module carries out the precision repetition measurement of a size, repetition measurement value is as a reference value, then to carrying out twice decomposition between electronic compartment and two cabins, reassembling and precision repetition measurement, contrast decomposition reassembles front and back precision change, if variation error controls between ± 0.01mm, then verify that flexible drawing carries out decomposing the assembly precision good stability reassembled; If variation error do not drop on ± 0.01mm between, then get back to the first step, till repetition measurement value controls between ± 0.01mm.
The unexposed technology of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (5)
1. flexible drawing carries out decomposing the having unit structure assembly method reassembled, and it is characterized in that: structure to be assembled is divided into electronic compartment and propulsion module two cabin sections, and this assembly method step is:
The first step: electronic compartment, propulsion module concurrent assembly
Electronic compartment assembles: on platform floor (18), build benchmark, first platform floor (18) and the platform cabin dividing plate of electronic compartment bottom are installed afterwards, secondly load ceiling board (14) and the dividing plate on electronic compartment top are installed, again outer panel and load ceiling board (12) are installed, outer panel comprises the+Y side plate (7) ,-Y side plate (13) ,+Z side plate (16) and-Z side plate (9) that are connected with platform cabin dividing plate, after above-mentioned each structural slab is in place, glued joint pin bush between plate, and carve quadrant line on electronic compartment outer panel;
Propulsion module assembles: set up and record whole satellite-based standard, riveting each housing of propulsion module and Combined machining, install the hydrazine bottle rack (2) in propulsion module after trial assembly, adjust whole satellite-based accurate, assembling is used for the hydrazine bottle rack pull bar fixing hydrazine bottle rack;
Second step: electronic compartment docks with propulsion module
Propulsion module is placed on satellite-rocket docking face, electronic compartment is lifted by flexible hanger, accurate for benchmark with whole satellite-based, electronic compartment quadrant line is alignd with whole satellite-based standard, ensure that right alignment is not more than φ 0.5, electronic compartment is docked with propulsion module, check electronic compartment and propulsion module butt-joint clearance, when the two gap is less than 0.1mm, tie bolt is installed, and then the strut joint and strut assembly (24) that connect electronic compartment are installed, measure satellite-rocket docking size, the installation of adjustment strut assembly (24); With pin, the hole on platform floor (18) is connected with the hole on propulsion module, glueds joint two cabin connecting pin (19) guidees; Set up the optical reference of solar wing: accurate by above-mentioned whole satellite-based, at the upper sticky prism square of platform floor (18), ensure that accurate three coordinates in three seamed edges of prism square and whole satellite-based are parallel, utilize prism square that windsurfing driver train support and windsurfing driver train are installed;
3rd step: Combined machining
Accurate for benchmark with satellite-based whole on propulsion module, determine axis of revolution 0 ° of direction of numerically-controlled machine tool, set up system of axes, milling be provided with solar wing ± Y side plate, the load ceiling board (14) of camera is installed and load ceiling board (12) ,+Z side plate (16) of antenna is installed, milling drilling also records data;
4th step: section decomposition in cabin reassembles and precision repetition measurement
Before each structural slab decomposes to electronic compartment be provided with solar wing ± lower surface of Y side plate and propulsion module carries out the precision repetition measurement of a size, repetition measurement value is as a reference value, then to carrying out twice decomposition between electronic compartment and two cabins, reassembling and precision repetition measurement, contrast decomposition reassembles front and back precision change, if variation error controls between ± 0.01mm, then verify that flexible drawing carries out decomposing the assembly precision good stability reassembled; If variation error do not drop on ± 0.01mm between, then get back to the first step, till repetition measurement value controls between ± 0.01mm.
2. a kind of flexible drawing as claimed in claim 1 carries out decomposing the having unit structure assembly method reassembled, it is characterized in that: in electronic compartment fitting process, the method that platform floor (18) is built benchmark is: with the intersection point of the diagonal line line of platform floor (18) for coordinate origin, Y-axis and Z axis are built in platform floor (18) face, sets up Z axis with vertical platform base plate (18) direction.
3. a kind of flexible drawing as claimed in claim 1 carries out decomposing the having unit structure assembly method reassembled, it is characterized in that: determine that the method for whole satellite-based standard is in propulsion module assembling: the mid point getting two pin-and-hole lines of the lower surface of propulsion module is coordinate origin, X-axis is perpendicular to the lower surface of propulsion module, Z, Y-axis are positioned on the lower surface of propulsion module, and Z, Y direction are determined by the angle of two pin-and-hole lines of centres and coordinate axle.
4. a kind of flexible drawing as claimed in claim 1 carries out decomposing the having unit structure assembly method reassembled, it is characterized in that: in electronic compartment and propulsion module docking operation, assembly stress will be eliminated before the installation of tie bolt, assembly connection point is avoided to concentrate as stress, when electronic compartment and propulsion module attaching screw are tightened with dynamometry, must symmetry carry out.
5. a kind of flexible drawing as claimed in claim 1 carries out decomposing the having unit structure assembly method reassembled, and it is characterized in that: the milling in Combined machining process is undertaken by following parameters: a. cutter rotating speed 200-300 rev/min; B. feed 50-60mm/ divides; C. cutting depth≤0.1mm; Lathe is undertaken by counterboring with step core drill mode when boring machining hole; During D≤the φ 6 of aperture, each cutter footpath increment is not more than 3; During φ 6< aperture D≤φ 10, each cutter footpath increment is not more than 2; During φ 10< aperture D≤φ 15, each cutter footpath increment is not more than 1.5.
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| CN107380483A (en) * | 2017-07-05 | 2017-11-24 | 上海宇航系统工程研究所 | A kind of spacecraft configuation |
| CN108791960A (en) * | 2018-07-10 | 2018-11-13 | 上海微小卫星工程中心 | A kind of fixing device for star sensor |
| CN110525688A (en) * | 2019-08-06 | 2019-12-03 | 北京空间飞行器总体设计部 | A kind of in-orbit restructural expansible satellite system |
| CN112077368A (en) * | 2020-08-17 | 2020-12-15 | 北京卫星制造厂有限公司 | Multi-degree-of-freedom pull rod posture measuring, adjusting and positioning method |
| 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 |
| CN114234836A (en) * | 2021-11-16 | 2022-03-25 | 北京卫星制造厂有限公司 | Method for assembling and assembling sealing cabin structure and sealing cabin structure |
| CN117268675A (en) * | 2023-09-20 | 2023-12-22 | 北京理工大学 | Spacecraft equipment installation precision deviation compensation method |
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| CN117268675A (en) * | 2023-09-20 | 2023-12-22 | 北京理工大学 | Spacecraft equipment installation precision deviation compensation method |
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