CN103942364A - Automatic modeling technology for typical matching structure in aircraft manufacturing tool - Google Patents
Automatic modeling technology for typical matching structure in aircraft manufacturing tool Download PDFInfo
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- CN103942364A CN103942364A CN201410108659.9A CN201410108659A CN103942364A CN 103942364 A CN103942364 A CN 103942364A CN 201410108659 A CN201410108659 A CN 201410108659A CN 103942364 A CN103942364 A CN 103942364A
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- semantic model
- outer ginseng
- supporting structure
- pine
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Abstract
Disclosed is an automatic modeling technology for a typical matching structure in an aircraft manufacturing tool. The technology mainly comprises the following steps: (1) defining a formalization expression of an automatic selection and positioning method of components of the typical matching structure, (2) reading and explaining a semantic model, (3) positioning and installing the components, and (4) generating a final model of the components. By the application of the automatic modeling technology, automatic modeling of the common typical matching structure in the aircraft manufacturing tool can be achieved, and development efficiency of the aircraft manufacturing tool is improved.
Description
Technical field
The present invention is typical supporting structure Auto-Modelling Technology in a kind of aircraft manufacturing frock, belongs to aircraft manufacturing design of technological arrangement field.
Background technology
A large amount of various types of technological equipments that are applicable to its structure and production feature in aircraft manufacturing process, are used.In order to shorten the Aircraft Production preparatory period, general, special standard component and the typical parts of a large amount of employings in these frocks, and the typical supporting structure with fixed correlation relation being formed by these elements.Between the composed component of typical case's supporting structure, have strict incidence relation, but under certain situation, each element is again independently in frock general structure, in assembly parts structure tree, does not occur integral member, but each component of composition integral member.In mechanical design field, existing technical method is by generating respectively independent component, re-uses design system function and completes assembly constraint and realize, the manual operation that this process need is loaded down with trivial details.How quick calling and these yuan of assembly is installed is one of key issue in the research of aircraft manufacturing frock automated design engineering.
Summary of the invention
In order to solve the technical matters of above-mentioned existence, the present invention proposes a kind of tool typical supporting structure Auto-Modelling Technology based on structure connection relation, the method technology can be used for realizing the automatic modeling of common typical supporting structure in aircraft manufacturing frock, thereby has improved the development efficiency of aircraft manufacturing frock.
The object of the invention is to be achieved through the following technical solutions:
Typical supporting structure Auto-Modelling Technology in a kind of aircraft manufacturing frock, is characterized in that: comprise the steps: 1) define automatically choosing and the formalization representation of localization method of typical supporting structure composed component; 2) semantic model reads and explains; 3) element location and installation; 4) element final mask generates.
Described step 1) defines automatically choosing with the method for the formalization representation of localization method of typical supporting structure composed component: in typical supporting structure, each element type determines, automatically choosing with localization method G of element can formalization representation be:
d＝G(t,C,E) ①
Wherein d represents the cad model (often representing with the form of document) after this standard component or typical parts are accurately located in its assembly parts design space, concrete data content and structure and plateform system are closely related, t representation element type, and C represents process conditions, E represents the outer ginseng collection of pine, and operator G is defined as:
The definition of each operator of formula in 2. sees below literary composition explanation.
Described step 2) the semantic model method that reads and explain is: semantic model reads and explains γ
m
s＝γ(t) ③
Wherein m
sfor the corresponding semantic model of element number (or type code name) t.
(1) tight outer ginseng is calculated τ
E
t＝τ
s(C) ④
Wherein E
ttight outer ginseng corresponding to process conditions C required while use for this element collects, and tight outer ginseng is determined by " input ".
(2) rule searching solves χ
R＝χ
s(E
t,E) ⑤
Wherein R is rule searching, by tight outer ginseng collection E
tjoin collection E outward with pine and determine, the outer ginseng of pine can't help " inputs " such as process conditions determine, mostly be some empirical datas, still need manually to preset or key entry alternately.The effect of rule searching is in the time of given specification not, will, according to outside input and querying condition, automatically determine the specification of element.
(3) parameter line solves ρ
L＝ρ(m
s,E
t,E) ⑥
Wherein L is parameter line, and parameter set is by semantic model m
s, tight outer ginseng collection E
tjoin collection E outward with pine and determine, determine the major parameter of element according to parameter set, in semantic model, find its corresponding parameter line.
(4) element mid-module generates
Wherein m
ifor mid-module, mid-module is by semantic model m
sdetermine with parameter line L, by the parameters value of the parameter line generating, assignment is to the shape expression formula in element semantic model, thus generation mid-module.
(5) specification structure ζ
s＝ζ(m
s,L) ⑧
Wherein s is component specification, and component specification is by semantic model m
sdetermine with parameter line L, can determine component specification according to the data of parameter line in semantic model.
The method of described step 3) element location and installation is:
(1) benchmark B
B＝B
i(C,E) ⑨
Wherein B is the positioning datum of element in typical supporting structure, is determined by process conditions C and the outer ginseng collection of pine E.
(2) element location P
P＝P
i(m
c,B) ⑩
Wherein, realizing the basis of locating is localizing objects m
cconversion between the calculating of the target benchmark at place and element benchmark and target benchmark.
The method that affiliated step 4) element final mask generates is: element final mask generates λ
d＝λ(m
i,P)
Wherein d is the cad model after element is accurately located in its assembly parts design space, by mid-module m
idetermine with location Calculation result P.
Beneficial effect of the present invention: the invention provides a kind of tool typical supporting structure Auto-Modelling Technology based on structure connection relation, its beneficial effect is as follows: realized the automatic modeling of common typical supporting structure in aircraft manufacturing frock, thereby improved the development efficiency of aircraft manufacturing frock.
Brief description of the drawings
Fig. 1 is typical supporting structure automatic modeling schematic diagram.
Fig. 2 is pressure plate structure figure.
Fig. 3 is that semantic model reads and explain algorithm pattern.
Fig. 4 is element location and installation algorithm pattern.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail; the present embodiment is to implement under taking invention technical scheme as prerequisite; provided detailed embodiment and concrete implementation procedure, but protection scope of the present invention is not limited to following embodiment.
Figure 1 shows that the aircraft manufacturing tool typical supporting structure automatic modeling principle that the present invention proposes, its concrete implementation step is as follows:
Step 1) defines automatically choosing with the method for the formalization representation of localization method of typical supporting structure composed component: in typical supporting structure, each element type determines, automatically choosing with localization method G of element can formalization representation be:
d＝G(t,C,E) ①
Wherein d represents the cad model (often representing with the form of document) after this standard component or typical parts are accurately located in its assembly parts design space, concrete data content and structure and plateform system are closely related, t representation element type, and C represents process conditions, E represents the outer ginseng collection of pine, and operator G is defined as:
The definition of each operator of formula in 2. sees below literary composition explanation.
Step 2) the semantic model method that reads and explain is: semantic model reads and explains γ
m
s＝γ(t) ③
Wherein m
sfor the corresponding semantic model of element number (or type code name) t.
(1) tight outer ginseng is calculated τ
E
t＝τ
s(C) ④
Wherein E
ttight outer ginseng corresponding to process conditions C required while use for this element collects, tight outer ginseng is determined by " input ", as bolt parameter d d and h2 in Fig. 2, respectively by calculating such as specified mounting hole, seal face and installed surfaces: determine diameter of bolt dd by the diameter of mounting hole; Seal face and installed surface are one group of parallel plane, and both spatial vertical distances are Z-direction coordinate value difference h2 in Fig. 2.
(2) rule searching solves χ
R＝χ
s(E
t,E) ⑤
Wherein R is rule searching, by tight outer ginseng collection E
tjoin collection E outward with pine and determine, the outer ginseng of pine can't help " inputs " such as process conditions determine, as bolt parameter h1 and h3 etc. in Fig. 2, mostly be some empirical datas, still need manually to preset or key entry alternately.The effect of rule searching is in the time of given specification not, will, according to outside input and querying condition, automatically determine the specification of element.
(3) parameter line solves ρ
L＝ρ(m
s,Et,E) ⑥
Wherein L is parameter line, and parameter set is by semantic model m
s, tight outer ginseng collection E
tjoin collection E outward with pine and determine, determine the major parameter of element according to parameter set, in semantic model, find its corresponding parameter line.
(4) element mid-module generates
Wherein m
ifor mid-module, mid-module is by semantic model m
sdetermine with parameter line L, by the parameters value of the parameter line generating, assignment is to the shape expression formula in element semantic model, thus generation mid-module.
(5) specification structure ζ
s＝ζ(m
s,L) ⑧
Wherein s is component specification, and component specification is by semantic model m
sdetermine with parameter line L, can determine component specification according to the data of parameter line in semantic model.
Semantic model reads and explains algorithm flow as shown in Figure 3.
The method of step 3) element location and installation is:
(1) benchmark B
B＝B
i(C,E) ⑨
Wherein B is the positioning datum of element in typical supporting structure, is determined by process conditions C and the outer ginseng collection of pine E.
(2) element location P
P＝P
i(m
c,B) ⑩
Wherein, realizing the basis of locating is localizing objects m
cconversion between the calculating of the target benchmark at place and element benchmark and target benchmark.
Element location and installation algorithm flow as shown in Figure 4.
The method that step 4) element final mask generates is: element final mask generates λ
d＝λ(m
i,P)
Wherein d is the cad model after element is accurately located in its assembly parts design space, by mid-module m
idetermine with location Calculation result P.
Claims (1)
1. a typical supporting structure Auto-Modelling Technology in aircraft manufacturing frock, is characterized in that: comprise the steps: 1) define automatically choosing and the formalization representation of localization method of typical supporting structure composed component; 2) semantic model reads and explains; 3) element location and installation; 4) element final mask generates;
Wherein, described step 1) defines automatically choosing with the method for the formalization representation of localization method of typical supporting structure composed component: in typical supporting structure, each element type determines, automatically choosing with localization method G of element can formalization representation be:
d＝G(t,C,E) ①
Wherein d represents the cad model (often representing with the form of document) after this standard component or typical parts are accurately located in its assembly parts design space, concrete data content and structure and plateform system are closely related, t representation element type, and C represents process conditions, E represents the outer ginseng collection of pine, and operator G is defined as:
The definition of each operator of formula in 2. sees below literary composition explanation;
Described step 2) the semantic model method that reads and explain is: semantic model reads and explains γ
m
s＝γ(t) ③
Wherein m
sfor the corresponding semantic model of element number (or type code name) t;
(1) tight outer ginseng is calculated τ
E
t＝τ
s(C) ④
Wherein E
ttight outer ginseng corresponding to process conditions C required while use for this element collects, and tight outer ginseng is determined by " input ";
(2) rule searching solves χ
R＝χ
s(E
t,E) ⑤
Wherein R is rule searching, by tight outer ginseng collection E
tjoin collection E outward with pine and determine, the outer ginseng of pine can't help " inputs " such as process conditions determine, mostly be some empirical datas, still need manually to preset or key entry alternately; The effect of rule searching is in the time of given specification not, will, according to outside input and querying condition, automatically determine the specification of element;
(3) parameter line solves ρ
L＝ρ(m
s,E
t,E) ⑥
Wherein L is parameter line, and parameter set is by semantic model m
s, tight outer ginseng collection E
tjoin collection E outward with pine and determine, determine the major parameter of element according to parameter set, in semantic model, find its corresponding parameter line;
(4) element mid-module generates
Wherein m
ifor mid-module, mid-module is by semantic model m
sdetermine with parameter line L, by the parameters value of the parameter line generating, assignment is to the shape expression formula in element semantic model, thus generation mid-module;
(5) specification structure ζ
s＝ζ(m
s,L) ⑧
Wherein s is component specification, and component specification is by semantic model m
sdetermine with parameter line L, can determine component specification according to the data of parameter line in semantic model;
Wherein, the method for described step 3) element location and installation is:
(1) benchmark B
B＝B
i(C,E) ⑨
Wherein B is the positioning datum of element in typical supporting structure, is determined by process conditions C and the outer ginseng collection of pine E;
(2) element location P
P＝P
i(m
c,B) ⑩
Wherein, realizing the basis of locating is localizing objects m
cconversion between the calculating of the target benchmark at place and element benchmark and target benchmark;
Wherein, the method that affiliated step 4) element final mask generates is: element final mask generates λ
d＝λ(m
i,P)
Wherein d is the cad model after element is accurately located in its assembly parts design space, by mid-module m
idetermine with location Calculation result P.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104850724A (en) * | 2015-06-17 | 2015-08-19 | 沈阳飞机工业（集团）有限公司 | Rapid airplane template design system and method |
| CN105988430A (en) * | 2015-01-30 | 2016-10-05 | 西门子（中国）有限公司 | Method and device for generating production process semantic model |
| CN107256009A (en) * | 2017-06-30 | 2017-10-17 | 武汉理工大学 | A kind of Digital product model Intelligent assembly system based on deep learning |
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| US20040039465A1 (en) * | 2002-08-23 | 2004-02-26 | Boyer Larry Paul | Modular tooling approach to major structural repair |
| CN102117367A (en) * | 2011-03-14 | 2011-07-06 | 沈阳飞机工业（集团）有限公司 | Visual simulation system for airplane assembly site |
| CN102411333A (en) * | 2011-11-18 | 2012-04-11 | 上海交通大学 | Fast numerical control machining process system for complex parts of airplane |
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2014
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040039465A1 (en) * | 2002-08-23 | 2004-02-26 | Boyer Larry Paul | Modular tooling approach to major structural repair |
| CN102117367A (en) * | 2011-03-14 | 2011-07-06 | 沈阳飞机工业（集团）有限公司 | Visual simulation system for airplane assembly site |
| CN102411333A (en) * | 2011-11-18 | 2012-04-11 | 上海交通大学 | Fast numerical control machining process system for complex parts of airplane |
Non-Patent Citations (1)
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105988430A (en) * | 2015-01-30 | 2016-10-05 | 西门子（中国）有限公司 | Method and device for generating production process semantic model |
| CN105988430B (en) * | 2015-01-30 | 2019-09-13 | 西门子（中国）有限公司 | The method and apparatus for generating production process semantic model |
| CN104850724A (en) * | 2015-06-17 | 2015-08-19 | 沈阳飞机工业（集团）有限公司 | Rapid airplane template design system and method |
| CN104850724B (en) * | 2015-06-17 | 2018-03-23 | 沈阳飞机工业（集团）有限公司 | Aircraft model quick design system and method |
| CN107256009A (en) * | 2017-06-30 | 2017-10-17 | 武汉理工大学 | A kind of Digital product model Intelligent assembly system based on deep learning |
| CN107256009B (en) * | 2017-06-30 | 2019-08-02 | 武汉理工大学 | A kind of Digital product model Intelligent assembly system based on deep learning |
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Application publication date: 20140723 |