CN104354874B - 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 PDF

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Publication number
CN104354874B
CN104354874B CN201410381753.1A CN201410381753A CN104354874B CN 104354874 B CN104354874 B CN 104354874B CN 201410381753 A CN201410381753 A CN 201410381753A CN 104354874 B CN104354874 B CN 104354874B
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China
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electronic compartment
cabin
propelling module
plate
assembling
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CN201410381753.1A
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Chinese (zh)
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CN104354874A (en
Inventor
戴璐
胡溶溶
李传辉
李志云
刘德利
宫顼
侯伟
马宁
孙天峰
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北京卫星制造厂
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Priority to CN201410381753.1A priority Critical patent/CN104354874B/en
Publication of CN104354874A publication Critical patent/CN104354874A/en
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Publication of CN104354874B publication Critical patent/CN104354874B/en

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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

A kind of flexible drawing carries out decomposing the having unit structure assembly method reassembling

Technical field

The present invention relates to a kind of flexible drawing carries out decomposing the having unit structure assembly method reassembling, belong to space flight Product structure mounting technology field.

Background technology

Satellite structure portion dress is the assembling of structure subsystem, provides overall structure precision meeting to install to connect Under the premise of, also provide high-precision satellite-rocket docking, solar wing, equipment, antenna, propulsion system etc. to install and connect Mouthful.

Standard is a key link in whole satellite production process, serves the effect taken over from the past and set a new course for the future. Brought forward: Standard is the structure carrier being connected to become satisfaction needs by required precision by part;Qi Hou: Standard, not only simply by the carrier that is connected to become of part, is also involved in celestial body structure overall precision, many The quality of the aspects such as individual mechanism, equipment installed surface precision, the mechanical property of the entirety of celestial body and safety assurance is protected Barrier problem, it directly affects the propulsion system loading afterwards, the precision of payload and safety.

Content of the invention

The technical problem to be solved is: for overcoming the deficiencies in the prior art, provides a kind of flexibility to lead Introduce row and decompose the having unit structure assembly method reassembling, the makeup of space product structure bay section is realized with this and joins, And make the structure of each bay section and interface meet the required precision under the standard of whole satellite-based.

The technical solution of the present invention is:

A kind of flexible drawing carry out decomposing the having unit structure assembly method reassembling it is characterised in that: to be assembled Structure be divided into electronic compartment and two bay sections of propelling module, this assembly method step is:

The first step: electronic compartment, propelling module concurrent assembly

Electronic compartment assembles: builds benchmark on platform floor, installs the platform floor of electronic compartment bottom afterwards first Secondly with platform cabin dividing plate, load Ceiling and the dividing plate on electronic compartment top are installed, install again outer panel and Load ceiling board, outer panel includes+y side plate ,-y side plate ,+z side plate and the-z being connected with platform cabin dividing plate Side plate, after above-mentioned each structural slab is installed in place, glueds joint set pin sleeve between plate, and carves on electronic compartment outer panel Quadrant line;

Propelling module assembles: sets up and record whole satellite-based standard, the riveting each housing of propelling module Combined machining, trial assembly Hydrazine bottle rack in propelling module is installed afterwards, the whole satellite-based of adjustment is accurate, assembles and props up for the hydrazine bottle fixing hydrazine bottle rack Frame pull bar;

Second step: electronic compartment is docked with propelling module

Propelling module is placed on satellite-rocket docking face, electronic compartment is lifted by flexible hanger, with whole satellite-based standard as base Standard, electronic compartment quadrant line is alignd with whole satellite-based standard it is ensured that axiality be not more than φ 0.5, by electronic compartment with push away Enter cabin docking, check electronic compartment and propelling module butt-joint clearance, when the two gap is less than 0.1mm, the company of installation Connecting bolt, and then the strut joint connecting electronic compartment and strut assembly are installed, measure satellite-rocket docking size, adjust The installation of whole strut assembly;With pin, the hole on platform floor is connected with the hole on propelling module, glueds joint two cabins even Pin guide;Set up the optical reference of solar wing: accurate by above-mentioned whole satellite-based, viscous vertical on platform floor Square mirror, it is ensured that three seamed edges of prism square are parallel with whole satellite-based three coordinates of standard, installs windsurfing using prism square Drive mechanism support and windsurfing drive mechanism;

3rd step: Combined machining

On the basis of whole satellite-based standard on propelling module, determine 0 ° of direction of gyroaxis of Digit Control Machine Tool, set up coordinate System, milling is provided with the ± y side plate of solar wing, is provided with the load Ceiling (14) of camera and is provided with The load ceiling board (12) of antenna ,+z side plate (16), milling drilling record data;

4th step: bay section decomposition reassembles and precision repetition measurement

Before each structural slab decomposes the ± y side plate of solar wing and the lower surface of propelling module are provided with to electronic compartment Carry out the precision repetition measurement of a size, repetition measurement value, as a reference value, is then carried out between electronic compartment and two cabins Decompose twice, reassemble and precision repetition measurement, contrast decomposition reassembles the change of before and after's precision, if variation error controls Between ± 0.01mm, then checking flexible drawing carries out decomposing the assembly precision good stability reassembling;If become Change error and decline between ± 0.01mm, then return to the first step, until repetition measurement value controls in ± 0.01mm Between till.

In electronic compartment assembling process, the method building benchmark on platform floor is: with the diagonal of platform floor The intersection point of line is coordinate origin, builds y-axis and z-axis, with vertical platform base plate side on platform floor face To setting up z-axis.

Determine in propelling module assembling that the accurate method in whole satellite-based is: take two pin-and-holes on the lower surface of propelling module to connect The midpoint of line is coordinate origin, and x-axis is located at the lower surface of propelling module perpendicular to satellite-rocket docking face, z, y-axis On, z, y-axis direction to be determined by the angle of two pin-and-hole lines of centres and reference axis.

In electronic compartment and propelling module docking operation, erection stress to be eliminated before the installation of connecting bolt, it is to avoid dress Join tie point as stress concentration, electronic compartment is tightened with propelling module attachment screw and during dynamometry it is necessary to symmetrically enter OK.

Milling during Combined machining is carried out by following parameters: 200-300 rev/min of a. cutter rotating speed;b. Feed 50-60mm/ divides;C. cutting depth≤0.1mm;Lathe is entered by counterboring with step core drill mode when boring processing hole OK;During aperture d≤φ 6, each knife footpath increment is not more than 3;During φ 6 < aperture d≤φ 10, each knife footpath Increment is not more than 2;During φ 10 < aperture d≤φ 15, each knife footpath increment is not more than 1.5.

Present invention advantage compared with prior art is:

(1) present invention each bay section independence, concurrent assembly, have saved the installation time of bay section, shorten assembling week Phase;

(2) propelling module of the present invention directly ensure that propelling module under the standard of whole satellite-based according to the quasi- installation processing of whole satellite-based Precision;Electronic compartment passes through to change benchmark assembling, and ensures electricity by install accurate to neat satellite-based of quadrant groove Required precision under the standard of whole satellite-based for the sub- cabin, after two cabin docking, under whole starlike state, Combined machining ensures electricity Crucial required precision under the standard of whole satellite-based for the sub- cabin, it is to avoid the accumulated error incrementally increasing in assembling process;

(3) present invention two cabin is located by connecting and installs alignment pin using in propelling module, and electronic compartment is according to the reality in two cabins Border relative position glueds joint the method positioning of set pin sleeve positioning, and the splicing of guide, using being directly opposite connection, carries The high security performance of product, need not produce special celestial body turning device;

(4) invention unit makeup is joined, and highly all < 1.5m, single cabin assembling stage personnel not be used in liter in single cabin Operated on fall car, it is to avoid long-time work high above the ground, greatly improved the security of production.

Brief description

Fig. 1 is electronic compartment of the present invention and propelling module structural representation;

Fig. 2 is propelling module front view of the present invention;

Fig. 3 is electronic compartment top view of the present invention;

Fig. 4 is hydrazine bottle rack modular construction schematic diagram of the present invention.

Specific embodiment

Below in conjunction with the accompanying drawings and be that the present invention will be further described for embodiment.

A kind of flexible drawing carries out decomposing the having unit structure assembly method reassembling, and structure to be assembled is divided into electricity Sub- cabin and two bay sections of propelling module, this assembly method step is:

The first step: electronic compartment, propelling module concurrent assembly

Electronic compartment assembles: builds benchmark on platform floor 18, with the friendship of the diagonal line of platform floor 18 Point is coordinate origin, builds y-axis and z-axis, with vertical platform base plate 18 direction on platform floor 18 face Set up z-axis;The installation long dividing plate of+z 3, the long dividing plate of-z 5 on the vertical z-axis direction of platform floor 18, two Long dividing plate is centrosymmetric;In installation+z breviseptum 17 and-z breviseptum 8 on two long dividing plate directions, Between median septum 4 is installed on both perpendicular to two long dividing plates, constitute a plane with ± z breviseptum;Upper State installed load Ceiling 14 on 5 pieces of platform cabin dividing plates;Load Ceiling 14 is built such as platform floor Benchmark on 18, and the long dividing plate 10 of the vertical load cabin of installed surface and load cabin are short on load Ceiling 14 11 two pieces of dividing plates of dividing plate;Perpendicular to z-axis direction ,+z side plate 16 ,-z side plate 9 are being installed afterwards;Perpendicular to Y-axis direction is installed+y side plate 7 ,-y side plate 13, is respectively mounted in+y side plate 7 ,-y side plate 13 The little side plate of+y 6, the little side plate of-y 15, perpendicular to x-axis direction installed load ceiling board 12, above structural slab After being installed in place, it is fixedly connected each structural slab and glueds joint set pin sleeve between plate, form one electronic compartment;In electricity Y-axis and z-axis quadrant line are carved on ± y the side plate in sub- cabin and ± z side plate.

Propelling module assembles: sets up and record whole satellite-based accurate, in the satellite-rocket docking face being connected with propelling module lower frame 21 On set up three-dimensional system of coordinate, take two pin-and-hole lines on satellite-rocket docking face (i.e. the lower surface of propelling module) Midpoint is coordinate origin, and perpendicular to satellite-rocket docking face, z, y-axis are located on satellite-rocket docking face x-axis, z, y Direction of principal axis to be determined by the angle of two pin-and-hole lines of centres and reference axis, and riveting propelling module housing 1 simultaneously combines Processing, installs hydrazine bottle rack 2 after trial assembly, take the mode of symmetrical assembling fastening to carry out, in hydrazine bottle rack 2 Using pad it is ensured that the low stress of hydrazine bottle rack 2 assembles and between propelling module housing 1;Adjust whole satellite-based accurate, Install that (hydrazine bottle rack assembly 23 includes hydrazine bottle rack 2 He for the hydrazine bottle rack pull bar of fixing hydrazine bottle rack 2 Hydrazine bottle rack pull bar), by monitoring the lower frame 21 satellite-rocket docking size of propelling module and adjusting assembly relation, real Existing propelling module low stress assembling.

Second step: electronic compartment is docked with propelling module

Propelling module is placed on satellite-rocket docking face, electronic compartment is lifted by flexible hanger, with whole satellite-based standard as base Standard, electronic compartment quadrant line is alignd with whole satellite-based standard it is ensured that axiality be not more than φ 0.5, by electronic compartment with push away Enter cabin docking, check electronic compartment and propelling module butt-joint clearance, when the two gap is less than 0.1mm, the company of installation Connecting bolt, the installation of connecting bolt can not be had a contest, and that is, erection stress to be eliminated before the installation of connecting bolt, keeps away Exempt from assembly connection point as stress concentration, can repair the link bolt hole of file propelling module upper ledge 20, electronic compartment with push away Enter cabin attachment screw tighten with during dynamometry it is necessary to symmetrically carry out.And then the strut joint connecting electronic compartment is installed And strut assembly 24, measure satellite-rocket docking size, the installation of adjustment strut assembly 24;0.6h~0.8h in advance Allotment weight is than 914a:914b: (914a, 914b are the two of 914 bonding agents to the glue of aluminium powder=6:1:6 Kind of component), added by engineer testing, proportioning thickener adjust glue mobility find neat with splicing face Filling, the equalization point between glue-joint strength;Join glue in advance by controlling, reduce glue mobility, it is to avoid stream Glue is it is achieved that reverse (dorsad the earth's core direction) glues guide it is ensured that positioning between bay section, reseting precision;With Hole on platform floor (18) is connected by pin with the hole on propelling module, glueds joint two cabin connecting pin 19 guide;Build The optical reference of vertical solar wing: accurate by above-mentioned whole satellite-based, viscous prism square on platform floor 18 it is ensured that 3 seamed edges of prism square are parallel with whole satellite-based three coordinates of standard, install windsurfing drive mechanism using prism square and prop up Frame and windsurfing drive mechanism.

3rd step: Combined machining:

Solar wing is installed on celestial body ± y side plate, and camera is installed on load Ceiling 14, load ceiling board 12 are provided with antenna with+z side plate, on the basis of whole satellite-based standard on propelling module, with+z quadrant as Digit Control Machine Tool 0 ° of direction of gyroaxis, set up coordinate system, milling ± y side plate, load Ceiling 14, load ceiling board 12 and+z side plate, drilling record data.Milling is carried out by following parameters: a. cutter rotating speed 200-300 Rev/min;B. feed 50-60mm/ divides;C. cutting depth≤0.1mm;Lathe is pressed ladder when boring processing hole and is expanded Hole mode is carried out;During aperture d≤φ 6, each knife footpath increment is not more than 3;During φ 6 < aperture d≤φ 10, Knife footpath increment is not more than 2 every time;During φ 10 < aperture d≤φ 15, each knife footpath increment is not more than 1.5.

4th step: bay section decomposition reassembles and precision repetition measurement

(do not need all to decompose all structural slabs, for the structure gluedd joint before each structural slab decomposes Plate, then need not split), to the lower surface being provided with the ± y side plate of solar wing and propelling module of electronic compartment (i.e. Satellite-rocket docking face) carry out the precision repetition measurement of a size, repetition measurement value as a reference value, then to electronic compartment and Decomposed twice between two cabins, reassembled and precision repetition measurement, contrast decomposition is reassembled the change of before and after's precision, if Variation error controls between ± 0.01mm, then checking flexible drawing carries out decomposing the assembly precision reassembling stably Property is good;If variation error is simultaneously declined between ± 0.01mm, return to the first step, until repetition measurement value controls Till between ± 0.01mm.

The present invention is not disclosed technology and belongs to general knowledge as well known to those skilled in the art.

Claims (5)

1. a kind of flexible drawing carry out decomposing the having unit structure assembly method reassembling it is characterised in that: to be installed The structure joined is divided into electronic compartment and two bay sections of propelling module, and this assembly method step is:
The first step: electronic compartment, propelling module concurrent assembly
Electronic compartment assembles: builds benchmark on platform floor (18), installs the flat of electronic compartment bottom afterwards first Platform base plate (18) and platform cabin dividing plate, secondly install load Ceiling (14) and the dividing plate on electronic compartment top, Outer panel and load ceiling board (12) are installed again, outer panel includes the+y side plate being connected with platform cabin dividing plate (7) ,-y side plate (13) ,+z side plate (16) and-z side plate (9), after above-mentioned each structural slab is installed in place, Glued joint set pin sleeve between plate, and quadrant line is carved on electronic compartment outer panel;
Propelling module assembles: sets up and record whole satellite-based standard, the riveting each housing of propelling module Combined machining, trial assembly Hydrazine bottle rack (2) in propelling module is installed afterwards, the whole satellite-based of adjustment is accurate, assembles the hydrazine for fixing hydrazine bottle rack Bottle rack pull bar;
Second step: electronic compartment is docked with propelling module
Propelling module is placed on satellite-rocket docking face, electronic compartment is lifted by flexible hanger, with whole satellite-based standard as base Standard, electronic compartment quadrant line is alignd with whole satellite-based standard it is ensured that axiality be not more than φ 0.5mm, by electronic compartment with Propelling module docks, and checks electronic compartment and propelling module butt-joint clearance, when the two gap is less than 0.1mm, installs Connecting bolt, and then the strut joint connecting electronic compartment and strut assembly (24) are installed, measure satellite-rocket docking chi Very little, the installation of adjustment strut assembly (24);With pin by the hole on platform floor (18) and propelling module Hole connects, and glueds joint two cabin connecting pin (19) guidees;Set up the optical reference of solar wing: by above-mentioned whole Satellite-based is accurate, in the upper viscous prism square of platform floor (18) it is ensured that three seamed edges of prism square and whole satellite-based standard three Individual coordinate is parallel, installs windsurfing drive mechanism support and windsurfing drive mechanism using prism square;
3rd step: Combined machining
On the basis of whole satellite-based standard on propelling module, determine 0 ° of direction of gyroaxis of Digit Control Machine Tool, set up coordinate System, milling is provided with the ± y side plate of solar wing, is provided with the load Ceiling (14) of camera and is provided with The load ceiling board (12) of antenna ,+z side plate (16), milling drilling record data;
4th step: bay section decomposition reassembles and precision repetition measurement
Before each structural slab decomposes the ± y side plate of solar wing and the lower surface of propelling module are provided with to electronic compartment Carry out the precision repetition measurement of a size, repetition measurement value, as a reference value, is then carried out between electronic compartment and two cabins Decompose twice, reassemble and precision repetition measurement, contrast decomposition reassembles the change of before and after's precision, if variation error controls Between ± 0.01mm, then checking flexible drawing carries out decomposing the assembly precision good stability reassembling;If become Change error and decline between ± 0.01mm, then return to the first step, until repetition measurement value controls in ± 0.01mm Between till.
2. a kind of flexible drawing carries out decomposing the having unit structure assembling side reassembling as claimed in claim 1 Method it is characterised in that: in electronic compartment assembling process, the method building benchmark on platform floor (18) is: With the intersection point of the diagonal line of platform floor (18) as coordinate origin, on platform floor (18) face Build y-axis and z-axis, z-axis is set up with vertical platform base plate (18) direction.
3. a kind of flexible drawing carries out decomposing the having unit structure assembling side reassembling as claimed in claim 1 Method it is characterised in that: determine in propelling module assembling that the accurate method in whole satellite-based is: take the lower surface of propelling module The midpoint of two pin-and-hole lines is coordinate origin, and x-axis is located at perpendicular to the lower surface of propelling module, z, y-axis On the lower surface of propelling module, z, y-axis direction to be determined by the angle of two pin-and-hole lines of centres and reference axis.
4. a kind of flexible drawing carries out decomposing the having unit structure assembling side reassembling as claimed in claim 1 Method it is characterised in that: in electronic compartment and propelling module docking operation, assembling to be eliminated before the installation of connecting bolt Stress, it is to avoid assembly connection point as stress concentration, tighten and during dynamometry by electronic compartment and propelling module attachment screw, Must symmetrically carry out.
5. a kind of flexible drawing carries out decomposing the having unit structure assembling side reassembling as claimed in claim 1 Method it is characterised in that: the milling during Combined machining is carried out by following parameters: a. cutter rotating speed 200-300 Rev/min;B. feed 50-60mm/ divides;C. cutting depth≤0.1mm;Lathe is pressed ladder when boring processing hole and is expanded Hole mode is carried out;During aperture d≤φ 6mm, each knife footpath increment is not more than 3mm;φ 6mm < aperture d During≤φ 10mm, each knife footpath increment is not more than 2mm;During φ 10mm < aperture d≤φ 15mm, often Secondary knife footpath increment is not more than 1.5mm.
CN201410381753.1A 2014-08-05 2014-08-05 Unitization structure assembling method for disassembly and reassembly through flexible traction CN104354874B (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN110525688B (en) * 2019-08-06 2020-09-25 北京空间飞行器总体设计部 On-orbit reconfigurable extensible satellite system

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KR20010058824A (en) * 1999-12-30 2001-07-06 이계철 Satellite motion control testing experiment
EP0957335B1 (en) * 1998-05-11 2006-04-12 Vought Aircraft Industries, Inc. System and method for assembling an aircraft
CN102224393A (en) * 2008-11-21 2011-10-19 空中客车作业有限公司 Structural element for a fuselage cell structure of an aircraft, comprising at least one positioning aid
CN102519441A (en) * 2011-12-06 2012-06-27 南京航空航天大学 Method for measuring positioning points based on laser tracker in docking process of airplane parts
CN103434653A (en) * 2013-08-22 2013-12-11 北京航空航天大学 Aircraft component digitized flexible assembling measuring method based on laser tracking measuring technique
FR2992292A1 (en) * 2012-06-25 2013-12-27 Aircelle Sa Device and method for assembling a fixed push-inverter structure of an aircraft propulsion assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0957335B1 (en) * 1998-05-11 2006-04-12 Vought Aircraft Industries, Inc. System and method for assembling an aircraft
KR20010058824A (en) * 1999-12-30 2001-07-06 이계철 Satellite motion control testing experiment
CN102224393A (en) * 2008-11-21 2011-10-19 空中客车作业有限公司 Structural element for a fuselage cell structure of an aircraft, comprising at least one positioning aid
CN102519441A (en) * 2011-12-06 2012-06-27 南京航空航天大学 Method for measuring positioning points based on laser tracker in docking process of airplane parts
FR2992292A1 (en) * 2012-06-25 2013-12-27 Aircelle Sa Device and method for assembling a fixed push-inverter structure of an aircraft propulsion assembly
CN103434653A (en) * 2013-08-22 2013-12-11 北京航空航天大学 Aircraft component digitized flexible assembling measuring method based on laser tracking measuring technique

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