CN103164584A - Calculation method of coordination accuracy based on key characteristics - Google Patents
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Abstract
The invention discloses a calculation method of the coordination accuracy based on the key characteristics. The calculation method of the coordination accuracy based on the key characteristics is characterized in that on the basis of construction of key characteristic data, the manufacturing standard of parts and assembly positioning calculation are unified, digital simulating calculation is conducted on the overall process from model frame installation and manufacturing to assembly and butt joint of aircraft components, and therefore the calculation method of the coordination accuracy based on the key characteristics strives to discover uncoordinated showing before an aircraft is actually manufactured and assembled. The calculation method of the coordination accuracy based on the key characteristics has the advantages that objective technical and economic benefits can be brought, for example, a tolerance design is carried out and quantitative information is provided for enterprise technician, a traditional tolerance distribution method is changed, the quantity of standard process equipment is reduced, the assembly quality and the production efficiency of the aircraft are obviously improved, the development risks of a new aircraft is reduced and the like.
Description
Technical field
The present invention relates to a kind of airplane component and coordinate counter, particularly based on the coordinating order of accuracy computing method of key characteristic.
Background technology
Exchanging coordination is the central issue of aircraft manufacturing process planning, and reasonably Allowance Design is to realize exchanging the important guarantee of coordinating, and directly affects workmanship, assembly yield and the manufacturing cost of aircraft product.The manufacturing of common mechanical part adopts the tolerance fit system can guarantee the exchange coordination requirement of product, and aircaft configuration is many by a large amount of joint faces, the technique rigidity is little, the sheet metal component or the nonmetal thin-walled parts that easily produce distortion in processing, assembling process form, and have the advantages that quantity is many, complex-shaped, the size transfer route is long.Therefore in the aircraft manufacturing field, the basic process of aircraft assembling is: part → establishment → section part → parts → parts docking → aircraft, so the structural unit of aircraft needs experience different station and type frame in assembling process.Positioning datum due to airplane parts in manufacture process and this part positioning datum when assembly is not necessarily consistent, and the positioning datum on aircraft components different shaped frame is also not necessarily identical, has caused aircraft components still can produce larger coordination error when docking.Traditional tolerance is theoretical to be calculated is that the coordination route that the shape link forms that moves by part produces on each technological equipment is formulated each makeup ring process allowance, and its account form can adopt extremum method or probabilistic method.This mode according to two-dimentional coordination route formulation tolerance is to a kind of simplification of Complex Assembly coordination problem and approximate to a certain extent, there is certain limitation, for example: different process method, the different Assembly of the parts of making links are together the time, only consider the manufacturing tolerance of links, can not react the factor that in whole manufacture process, dimensional tolerence changes; For positions such as atypical structure such as fuselage integral tank edges, if calculate complicated, loaded down with trivial details according to the coordination route computing method.At present, it is monte carlo simulation methodology that the tolerance computing method mostly adopt the computer-experiment simulation means, according to the tolerance regularity of distribution of determining, dimension chain is carried out sampling simulation, and the method is also the main flow account form that present business software adopts.
In recent years, aircraft industry begins to introduce business CAT software and is used for tolerance analysis research, comprises the Vis/VSA of Siemens company and the 3DCS software of DCS company.These softwares can directly be set up the Digital Assembly Technique model on the 3D of product digital-to-analogue, its major function comprise Datum reference frames definition under three-dimensional assembly mode, size and form and position tolerance definition, physical dimension chain automatically generate, based on the size fluctuation simulation of Monte Carlo method and Contribution Analysis etc.Although these softwares supporting structure dimension chain are well found the solution function and are applied to widely automobile manufacture industry, but and the aircraft coordinating order of accuracy that is not suitable for having under process dimension chain or process dimension chain and physical dimension chain acting in conjunction impact calculates, the shape error of moving of the size under therefore can't coordinating frock, position, shape is carried out quantitative analysis: for example in aircraft manufacturing, the manufacturing of sheet metal component and multiple material spare has still adopted more technique to move the shape link, and the gauge in kind that the joint location device in the general assembly type frame of large parts etc. still adopt is installed and coordinates.Totally it seems, these softwares still can not play a role in the aircraft manufacturing Tolerance Allocation fully.
Summary of the invention
Technical matters to be solved by this invention is take TOLERANCE ANALYSIS software as instrument, on the basis of definition key characteristic, manufacturing benchmark and the reference for assembling of airplane parts to be unified coordinating order of accuracy and the assembly yield of calculating aircraft.By in the design phase, each link of aircraft manufacturing process being carried out reasonable distribution and the simulation optimization of process allowance, analysis is on the distortion contributor of sensitizing range and affect geometrical factor, set up cover aircraft manufacturing digitizing tolerance computing method, strengthen the agility of design decision, the ability of engineering iteration is provided for design and issue.
For above-mentioned technical matters, the present invention takes following technical scheme, and the coordinating order of accuracy computing method based on key characteristic is characterized in that, according to the division foundation of the assembly technology parting plane key characteristic group corresponding with the type frame; The installation process of parts fixation, manufacture process, tool positioner is considered as respectively an assembling process; According to assembly technology, manufacturing benchmark and the reference for assembling of part are unified; Unified benchmark is loaded in the Digital Assembly Technique model of each station; Simulation calculation is carried out in docking to the aircraft components under the multistation effect; The step of simulation calculation is as follows:
1) selected evaluating objects position, namely need calculate the position of coordinating error;
2) according to aircraft rigger skill and station, build the key characteristic group, the topological data of setting up the key characteristic group is related;
3) in VSA software, set up the foozle of type shut die type;
4) in VSA software, set up the location and installation error of type frame steady arm;
5) in VSA software, set up the digital process model of type frame;
6) according to reference for assembling and the assemble sequence of type frame, set up the assembly process model of first type frame;
7) according to the assembly technology of master unit, select the assemble sequence of each part and the reference for installation of each part;
8) according to the manufacturing technical feature of part, selected part is made benchmark;
9) calculate the transformed error that part is made benchmark and this part reference for installation, utilization VSA software is set up Datum reference frames, the feature of this part and is carried in size and form and position tolerance on feature;
10) according to assembly technology, part is positioned in order on the steady arm of frock and creates position constraint in VSA software, set up the Digital Assembly Technique model take frock as target;
11) according to evaluating objects, set up and to measure and to use monte carlo method to carry out emulation, the coordination position rigging error of calculating first component on first station;
12) set up the assembly process model of second type frame according to above-mentioned steps, error is carried on the feature of coordinating the position in should the key characteristic group of station and set up and measure, calculate the rigging error of second station; Until complete the parts assembling after combination successively on n type frame;
13) according to the part manufacturing process characteristics of coordinating parts, selected part is made benchmark;
14) calculate the transformed error that the part of coordinating parts is made benchmark and this part reference for installation;
15) set up the Digital Assembly Technique model of coordinating first station of parts;
16) take and the master unit same way as, set up the assembly process model take first station as target, calculate the coordination error of coordinating parts;
17) by that analogy, until complete the assembling of coordinating parts after combination successively on N type frame;
18) last, set up the process modeling of parts docking with the error link, calculate the docking of master unit and coordination parts and coordinate error.
Described key characteristic group is the set that consists of part digital-to-analogue in the Digital Assembly Technique model and be labeled in scale error on digital-to-analogue, form and position tolerance:
K i Represent corresponding part
iThe set of key characteristic,
k ij The expression part
iUpper certain key characteristic; Part
iUpper all key characteristics can be expressed as
Therefore, the key characteristic set of considering on certain station when aircraft assembles can be expressed as:
And
,
h=1,2 ....
tThe expression station
wUpper part number.
Aircraft components assembling need to be completed by a plurality of type frame/stations, and the key characteristic group that therefore assembling process that should aircraft components is produced is:
, wherein
w=1,2 ....
nRepresent the station quantity that experiences in this aircraft components assembling process.
In like manner, the key characteristic group that the coordination parts of this aircraft is produced can be expressed as:
, wherein
K p Expression is coordinated parts at station
pUpper all key characteristic set,
p=1,2 ....
mThe station quantity that experiences when the parts assembling is coordinated in expression.
The described topological data of setting up the key characteristic group is related, is crucial special new group corresponding to certain parts is considered as node, comes topology association between data of description with the non-directed graph in graph theory between the key characteristic group
T =
G(
E ,
V ),
V The expression node is the key characteristic group of parts,
E Line between expression limit or node namely needs to carry out coordinating order of accuracy and calculates between parts, can build on this basis the data of overall aircraft key characteristic group.
The present invention is on the basis that builds the key characteristic data, calculate mutually unified with assembling and positioning the manufacturing benchmark of part, the type frame is installed made the digitalized artificial calculating of carrying out overall process to aircraft components assembling docking, make every effort to find that inharmonic manifesting is characteristic of the present invention before the assembling of aircraft Practical manufacturing.Can bring objective technology and economic benefit, as providing quantitative information for the enterprise technology personnel carry out Allowance Design, change traditional Tolerance Allocation method, reduce standard tooling quantity, obviously improve the development risk of aircraft assembly quality and production efficiency and the new machine of reduction etc.
Description of drawings
Fig. 1 is wing key characteristic group schematic diagram.
Fig. 2 is process flow diagram of the present invention.
Fig. 3 has between Large Aircraft Components in the present invention to coordinate crucial non-directed graph.
Embodiment
Now the invention will be further described in conjunction with the accompanying drawings and embodiments, and referring to Fig. 1, Fig. 2 and Fig. 3, the coordinating order of accuracy computing method based on key characteristic is characterized in that, according to the division foundation of the assembly technology parting plane key characteristic group 101 corresponding with the type frame; The installation process of parts fixation, manufacture process, tool positioner is considered as an assembling process 102; According to assembly technology, manufacturing benchmark and the reference for assembling of part are unified 103; Unified benchmark is loaded in the Digital Assembly Technique model of each station 104; Simulation calculation 105 is carried out in docking to the aircraft components under the multistation effect.The step of simulation calculation is as follows:
1) selected evaluating objects position, namely need calculate the position of coordinating error;
2) according to aircraft rigger skill and station, build the key characteristic group, the topological data of setting up the key characteristic group is related;
3) in VSA software, set up the foozle of several type frame steady arm tolerance models;
4) in VSA software, set up the location and installation error of several type frame steady arm models;
5) in VSA software, set up the digital process model of several type framves;
6) according to reference for assembling and the assemble sequence of type frame, set up the assembly process model of first type frame;
7) according to the assembly technology of master unit, select the assemble sequence of each part and the reference for installation of each part;
8) according to the manufacturing technical feature of part, selected part is made benchmark;
9) calculate the transformed error that part is made benchmark and this part reference for installation, utilization VSA software is set up Datum reference frames, the feature of this part and is carried in size and form and position tolerance on feature;
10) according to assembly technology, part is positioned in order on the steady arm of frock and creates position constraint in VSA software, set up the Digital Assembly Technique model take frock as target;
11) according to evaluating objects, set up and to measure and to use monte carlo method to carry out emulation, the coordination position rigging error of calculating first component on first station;
12) set up the assembly process model of second type frame according to above-mentioned steps, error is carried on the feature of coordinating the position in should the key characteristic group of station and set up and measure, calculate the rigging error of second station; Until complete the parts assembling after combination successively on N type frame;
13) calculate the manufacturing technical feature of coordinating component parts, selected part is made benchmark;
14) calculate the transformed error of coordinating component parts manufacturing benchmark and this part reference for installation;
15) set up the Digital Assembly Technique model of coordinating first station of parts;
16) take and the first component same way as, set up the assembly process model take first station as target, calculate the coordination error of coordinating parts;
17) by that analogy, until complete the assembling of coordinating parts after combination successively on N type frame;
18) set up at last the process modeling of parts docking with the error link, calculate the docking of master unit and coordination parts and coordinate error.
Embodiment:Using the present invention carries out should holding following cardinal rule and definition when the accuracy of aircraft assembly coordination is calculated:
Manufacture process or one-step installation process are called assembling process one time.Referring to Fig. 2, be exactly once that the pin pilot hole on the mould is an assembling process of mould and the shaping plate of benchmark as the panel beating rib in the manufacture process of carrying out rubber pocket hydroforming behind location on mould, and the pilot hole on sheet metal part employing location-plate (frock) position the process of assembling also referred to as an assembling process.According to the division foundation of the assembly technology parting plane key characteristic group 101 corresponding with the type frame; The installation process of parts fixation, manufacture process, tool positioner is considered as an assembling process 102; According to assembly technology, manufacturing benchmark and the reference for assembling of part are unified 103; Unified benchmark is loaded in the Digital Assembly Technique model of each station 104; Simulation calculation 105 is carried out in docking to the aircraft components under the multistation effect.
The installation process of type frame is also as the assembling process of " product ".Main contents are two aspects:
1) Organization of Data of key characteristic group
The key characteristic definition: key characteristic refers to that it is the digitizing tolerance model that tolerance analysis is calculated needs consideration that the larger characteristic of impact is coordinated in aircraft assembling exchange, the key characteristic group
KRefer to by the part digital-to-analogue that forms tolerance chain and be labeled in the set of scale error on digital-to-analogue, form and position tolerance.As shown in Figure 1, wing
K wParts are by integral wing tank
K 3, the droope snoot inner segment
K 1, the outer section of droope snoot
K 2, the wing outside
K 4, the wing flap parts
K 5With the aileron parts
K 6Consist of covering k Deng subassembly
21, beam k
22,Joint k
23With lining k
2nDeng being the outer section of droope snoot
K 2Vital part, be key characteristic group Element of a set:
And
The aircraft components assembling need to be completed by a plurality of type framves (station), and therefore concerning certain station, its corresponding key characteristic group is:
Wherein
Aircraft is coordinated to refer between the aircaft configuration unit in the degree of consistency of dimensional parameters that cooperatively interacts out.If the key characteristic group corresponding certain parts is considered as node, can come with the non-directed graph in graph theory the topology between data of description related between the key characteristic group
T =
G(
E ,
V ),
V The expression node is the key characteristic group of parts,
E Expression limit (line between node) is to need to carry out coordinating order of accuracy between parts to calculate, and can build on this basis the data of overall aircraft key characteristic group.Fig. 3 has represented to have between Large Aircraft Components the non-directed graph of the key coordinated.
Adjacency matrix between its node is as follows:
2) part is made the unification of benchmark and reference for assembling
Often meet the inconsistent phenomenon of reference for assembling of manufacturing benchmark and this part of part in the aircraft assembling, produce larger coordination error when having caused the aircraft components docking.The present invention unifies manufacturing benchmark and the assembling and positioning benchmark of part, calculates the error of benchmark conversion, is carried on the feature of part when the tolerance modeling, and coordinating order of accuracy calculates and adopted the Vis/VSA software of Siemens company.
Aircraft manufacturing based on key characteristic is coordinated error calculation method, and calculation procedure is as follows:
1) selected evaluating objects position, namely need calculate the position of coordinating error, as the right alignment in the gap of body joint end face and Wing Joint end face, joint group aperture etc.;
2) according to aircraft rigger skill and station, build the key characteristic group, the topological data of setting up the key characteristic group is related;
3) in VSA software, set up the foozle model of several type frame steady arms;
4) in VSA software, set up the location and installation error model of several type frame steady arms;
5) in VSA software, set up the digital process model of several type framves;
6) according to reference for assembling and the assemble sequence of type frame, set up the assembly process model of first type frame;
7) according to the assembly technology of body parts, select the assemble sequence of each part and the reference for installation of each part;
8) according to the manufacturing technical feature of part, selected part is made benchmark;
9) calculate the transformed error that part is made benchmark and this part reference for installation, utilization VSA software is set up Datum reference frames (DRF), the feature (Feature) of this part and is carried in size and form and position tolerance on feature;
10) according to assembly technology, part is positioned in order on the steady arm of frock and creates position constraint in VSA software, set up the Digital Assembly Technique model take frock as target;
11) according to evaluating objects, set up and measure (Measurement) and use monte carlo method to carry out emulation, calculate the coordination position rigging error S of body parts on first station
11(tolerance range intermediate value and bandwidth);
12) in like manner, set up the assembly process model of second type frame according to above-mentioned steps, with error S
11Be carried on the feature of coordinating the position in should the key characteristic group of station and set up and measure, calculate the rigging error S of second station
12Until complete the parts assembling after combination successively on N type frame, its rigging error is S
1n
13) according to the manufacturing technical feature of coordinating the airfoil member part, selected part is made benchmark;
14) calculate the transformed error of coordinating airfoil member part manufacturing benchmark and this part reference for installation;
15) set up the Digital Assembly Technique model of coordinating first station of airfoil member;
16) take and the body parts same way as, set up the assembly process model take first station as target, calculate the coordination error S that coordinates airfoil member
* 21
17) by that analogy, until complete the assembling of coordinating airfoil member after combination successively on m type frame, its rigging error is S
* 2m
18) at last with S
2n, S
* 2mSet up the process modeling of parts docking for the error link, calculate the coordination error S of body parts and airfoil member.
The present invention adopts TOLERANCE ANALYSIS software VSA (Visualization ﹠amp; Simulation Analysis)
The coordinating order of accuracy analysis calculation method of Facing Digital aircraft manufacturing assembling of the present invention, before being intended to airplane component actual production assembling, build the key characteristic group of parts and use CAT software analysis simulation assembly yield, i.e. the size fluctuation of aircraft coordination place is positioned at the possibility of regularity technical conditions (as exchanging the elastic deformation amount who coordinates requirement, maximum repair amount, permission) scope.
Claims (3)
1. based on the coordinating order of accuracy computing method of key characteristic, it is characterized in that, according to the division foundation of the assembly technology parting plane key characteristic group corresponding with the type frame; The installation process of parts fixation, manufacture process, tool positioner is considered as an assembling process; According to assembly technology, manufacturing benchmark and the reference for assembling of part are unified; Unified benchmark is loaded in the Digital Assembly Technique model of each station; Simulation calculation is carried out in docking to the aircraft components under the multistation effect; The step of simulation calculation is as follows:
1), selected evaluating objects position, namely need calculate the position of coordinating error;
2), according to aircraft rigger skill and station, build the key characteristic group, the topological data of setting up the key characteristic group is related;
3), in VSA software, set up the foozle of type shut die type;
4), in VSA software, set up the location and installation error of type frame steady arm;
5), in VSA software, set up the digital process model of type frame;
6), according to reference for assembling and the assemble sequence of type frame, set up the assembly process model of first type frame;
7), according to the assembly technology of master unit, the assemble sequence of selected each part and the reference for installation of each part;
8), according to the manufacturing technical feature of part, selected part is made benchmark;
9), calculate the transformed error that part is made benchmark and this part reference for installation, utilization VSA software is set up Datum reference frames, the feature of this part and is carried in size and form and position tolerance on feature;
10), according to assembly technology, part is positioned in order on the steady arm of frock and creates position constraint in VSA software, set up the Digital Assembly Technique model take frock as target;
11), according to evaluating objects, set up and to measure and to use monte carlo method to carry out emulation, the coordination position rigging error of calculating first component on first station;
12), set up the assembly process model of second type frame according to above-mentioned steps, error is carried on the feature of coordinating the position in should the key characteristic group of station and set up and measure, calculate the rigging error of second station; Until complete the parts assembling after combination successively on N type frame;
13), according to the part manufacturing process characteristics of coordinating parts, selected part is made benchmark;
14), calculate the transformed error that the part of coordinating parts is made benchmark and this part reference for installation;
15), set up the Digital Assembly Technique model of coordinating first station of parts;
16), take and the master unit same way as assembly process model of foundation take first station as target, the coordination error of calculating coordination parts;
17), by that analogy, until complete the assembling of coordinating parts after combination successively on N type frame;
18), at last, set up the process modeling of parts docking with the error link, calculate the docking coordination error of master unit and coordination parts.
2. the coordinating order of accuracy computing method based on key characteristic according to claim 1, is characterized in that, described key characteristic group refers to by the part digital-to-analogue that forms tolerance chain and is labeled in the set of scale error on digital-to-analogue, form and position tolerance;
The key characteristic set:
K i Represent corresponding part
iThe set of key characteristic,
k ij The expression part
iUpper certain key characteristic; Part
iUpper all key characteristics can be expressed as
Therefore, the key characteristic set of considering on certain station when aircraft assembles can be expressed as:
And
,
h=1,2 ....
tThe expression station
wUpper part number;
The key characteristic group: aircraft components assembling need to be completed by a plurality of type frame/stations, and the key characteristic group that therefore assembling process that should aircraft components is produced is:
, wherein
w=1,2 ....
nRepresent the station quantity that experiences in this aircraft components assembling process;
Coordinate the key characteristic group of parts: the key characteristic group that the coordination parts of this aircraft are produced can be expressed as:
, wherein
K p Expression is coordinated parts at station
pUpper all key characteristic set,
p=1,2 ....
mThe station quantity that experiences when the parts assembling is coordinated in expression.
3. coordinating order of accuracy computing method based on key characteristic according to claim 1, it is characterized in that, described topological data association of setting up the key characteristic group, be that crucial special new group corresponding to certain parts is considered as node, come the topology between data of description related with the non-directed graph in graph theory between the key characteristic group
T =
G(
E ,
V ),
V The expression node is the key characteristic group of parts,
E Line between expression limit or node namely needs to carry out coordinating order of accuracy and calculates between parts, can build on this basis the data of overall aircraft key characteristic group.
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| CN111931340A (en) * | 2020-07-06 | 2020-11-13 | 重庆诚智鹏科技有限责任公司 | Tolerance management system and management method |
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| CN103895876A (en) * | 2014-03-27 | 2014-07-02 | 浙江大学 | Regional characteristic guiding based evaluation method of wing wall plate and framework assembly gaps |
| CN103895876B (en) * | 2014-03-27 | 2015-12-02 | 浙江大学 | The wing wallboard guided based on provincial characteristics and the evaluation method in Skeleton assembly gap |
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| CN111152934A (en) * | 2020-01-07 | 2020-05-15 | 通航国际（西安）飞机技术有限公司 | Coordination control method for LE700 aircraft assembly tool |
| CN111931340A (en) * | 2020-07-06 | 2020-11-13 | 重庆诚智鹏科技有限责任公司 | Tolerance management system and management method |
| CN113779803A (en) * | 2021-09-16 | 2021-12-10 | 南京航空航天大学 | Machining and assembling interaction method based on dynamic tolerance |
| CN113779803B (en) * | 2021-09-16 | 2024-02-27 | 南京航空航天大学 | Machining and assembling interaction method based on dynamic tolerance |
| CN114880796A (en) * | 2022-04-29 | 2022-08-09 | 沈阳飞机工业（集团）有限公司 | Tolerance analysis method for aircraft assembly process optimization |
| CN114880796B (en) * | 2022-04-29 | 2024-04-16 | 沈阳飞机工业（集团）有限公司 | Tolerance analysis method for aircraft assembly process optimization |
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