CN102855362B - A kind of method that inspection pipeline based on computer-aided design (CAD) assembles - Google Patents
A kind of method that inspection pipeline based on computer-aided design (CAD) assembles Download PDFInfo
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Abstract
The invention belongs to Design of digital field, relate to the pipeline assembly test Fixture Design method based on computer-aided design (CAD) of the pipeline component processing in a kind of aeromotor, gas turbine.The present invention sets up the parametrization 3-dimensional digital spare part model of pipeline assembly test frock, and sets up the general assembly digital model of the parametrization pipeline assembly test frock of associated.Reserve the interface matched with parameter extraction program.The parameter extraction program of the secondary language development based on correspondence is utilized under 3 d modeling software, utilize circulation automatic access 3 d modeling software bottom database, go the feature identifying conduit digital product model, automatic extraction interrelated geometrical parameters, feed back to the geometric feature sizes of the spare part model of characteristic parameter and then driving pipeline assembly test frock, and automatically upgrade fitted position, the assembly relation of the general assembly model of pipeline assembly test frock, automatic analysis can be carried out to part, pipeline assembly test frock digital modeling process can be completed fast.
Description
Technical field
The invention belongs to Design of digital field, the method that the inspection pipeline based on computer-aided design (CAD) relating to the pipeline component processing in a kind of aeromotor, gas turbine assembles.
Background technology
In order to save space on engine and gas turbine, the overlapped intersection of various circuit design, in order to avoid pipeline is interfered mutually, the spatial geometric shape of conduit is very complicated.Pipeline component is wide in variety in addition, substantial amounts, size are different in size, has tighter manufacturing tolerance requirement.After guiding-tube bend is shaping, carries out welding with various pipe adapter and flange and detection is carried out to its position and check and accept, respective line parts assembly test frock must be had for this reason to have coordinated this work.The relevant tool of current pipeline component is all rely on the manual two-dimensional design of Fixture Design personnel, because pipeline locus is complicated, characterize each section of accurate locus of pipeline, when two-dimensional design, projection relation is complicated, and needing abundant space imagination and jig Design experience, repeatedly can reach requirement through repeatedly adjusting.Because design efforts would is large, catheter space is complicated in addition, causes design efficiency low, and designing quality is difficult to ensure.
Summary of the invention
The object of the invention is to propose a kind of inspection Fixture Design efficiency high, the method that the measured inspection pipeline based on computer-aided design (CAD) of matter assembles.
Technical solution of the present invention
1). in Computerized three-dimensional design software, set up a general assembly model, a pipeline tool base plate spare part is set up in general assembly model, ensure that the lower left corner intersection point of upper surface of base plate spare part overlaps with the absolute initial point of general assembly model, base plate spare part length direction overlaps with the absolute coordinate system X-axis of general assembly model, base plate spare part Width overlaps with the absolute coordinate system Y-axis of general assembly model, XOY plane is formed at base plate spare part upper surface, fit on first section of bearing spare part on base plate spare part, latter end bearing spare part and interlude prop up block spare part, ensure first section of bearing spare part, latter end bearing spare part and interlude prop up block spare part lower surface and base plate spare part upper surface is fitted,
2). plant at base plate spare part upper surface and put technological ball spare part, technological ball spare part centre of sphere distance absolute coordinate system ZOY plane is whole value Δ X, technological ball spare part centre of sphere distance absolute coordinate system ZOX plane is whole value Δ Y, and ensures that technological ball spare part centre of sphere distance absolute coordinate system XOY plane is whole value Δ Z.
3). pipeline spare part is assembled in this general assembly model in the mode of absolute initial point; And in pipeline spare part, choose two sections in pipeline spare part, form a plane R along Z-direction difference in height minimum tube section, in general assembly model, retrain this plan range technological ball spare part centre of sphere is a whole value Δ 1, choose the some particular cross section of pipeline spare part to the given whole value Δ 2 of the technological ball spare part centre of sphere, and ensure that the axis of this section and the technological ball spare part centre of sphere are also whole value Δs 3, and the angle of the axis of this section and X-axis is a whole value Φ;
4). determine the projected angle θ 0 of XOY plane on first section of axis of pipeline spare part and base plate spare part, the absolute altitude value Z1 of first section of end face centre point of pipeline spare part, according to projected angle θ 0 and absolute altitude value Z1, to determine angle of pitch β 0 and the height value H0 of first section of bearing spare part, first section of bearing spare part digital-to-analogue is driven to mate with first section of end face of pipeline spare part;
H0＝Z1+δ1*SINθ0－δ2*COSθ0
β0＝θ0
Section bearing spare part feature height value headed by H0
Z1 is the height value of first section of end face centre point distance XOY plane of pipeline spare part
Section bearing spare part angle of pitch angle value headed by β 0
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
5). by the starting point X1 of the axis of first section of pipeline spare part, Y1, Z1 and terminal point coordinate X2, Y2, Z2, calculate absolute X, Y, Z coordinate figure XD1, the YD1 of the section of informing against bearing spare part two dowel hole, 0 and XD2, YD2,0, wherein
XD1＝X1+δ1*COSθ0*COSα0+δ2*SINθ0*COSα0+δ3*COSα0-δ4*SINα0
YD1＝Y1+δ1*COSθ0*SINα0+δ2*SINθ0*SINα0+δ3*SINα0+δ4*COSα0
XD2＝X1+δ1*COSθ0*COSα0+δ2*SINθ0*COSα0+δ3*COSα0+δ4*SINα0
YD2＝Y1+δ1*COSθ0*SINα0+δ2*SINθ0*SINα0+δ3*SINα0-δ4*COSα0
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
Headed by δ 3, section bearing spare part is along its Width side and its two dowel holes line of centres vertical range
The half of section bearing spare part two dowel hole axis vertical range along its length headed by δ 4
α 0 is axis projection line and X-axis angulation value in XOY plane of first section of pipeline spare part, gets acute angle.
6). determine each interlude of pipeline spare part and the pitching angle theta 1 of base plate spare part upper surface, and the absolute altitude value Zm of this straight-line segment intermediate point, to determine that interlude props up the physical dimension value of block spare part.
H1＝Zm-(0.5*D+Ψ)/COSθ1
β1＝θ1
H1 is that interlude props up block spare part feature height value
Zm is the absolute Z value of some interlude pipeline axis intermediate points of pipeline spare part
D is the interlude external diameter of pipeline spare part
Ψ is the locus degree tolerance that each interlude of pipeline spare part needs to control, aeroengine pipeline processing empirical value
β 1 interlude props up block spare part angle of pitch angle value
7). by the intermediate point Xm of the interlude axis of pipeline spare part, Ym, Zm, project to plate upper surface, extrapolates absolute X, Y, Z coordinate figure XD3, YD3 that interlude props up block spare part two dowel hole, and 0 and XD4, YD4,0, wherein
XD3＝Xm+(λ0-D/2-λ1*Tanγ)SINγ+λ1/COSγ
YD3＝Ym-(λ0-D/2-λ1*Tanγ)*COSγ
XD4＝Xm+(λ0+λ2-D/2+λ1*Tanγ)SINγ-λ1/COSγ
YD4＝Ym-(λ0+λ2-D/2+λ1*Tanγ)*COSγ
λ 0 for interlude prop up block spare part side along its length with its nearside dowel hole vertical range
D is the interlude face of cylinder external diameter of pipeline spare part
λ 1 props up two dowel hole axis of block spare part, along the half of its Width vertical range for interlude
λ 2 props up two dowel hole axis, along its length vertical ranges of block spare part for interlude
γ is the projection line of a certain interlude axis of pipeline spare part in XOY plane, with X-axis angle, gets acute angle
Successively all interludes of pipeline spare part are all finished
8). determine the projected angle θ 2 of XOY plane on the latter end axis of pipeline spare part and base plate spare part, the absolute altitude value Z6 of the end face centre point of pipeline spare part latter end, determine angle of pitch β 2 and the height value H2 of latter end bearing spare part according to projected angle θ 2 and absolute altitude value Z6, drive latter end bearing spare part digital-to-analogue to mate with pipeline spare part latter end end face;
H2＝Z6+δ1*SINθ0－δ2*COSθ0
β2＝θ2
H2 is pipeline latter end bearing spare part feature height value
Z6 is the height value of the latter end end face centre point distance XOY plane of pipeline spare part
β 2 is latter end bearing spare part angle of pitch angle value
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
9). by the starting point X5 of the axis of pipeline spare part latter end, Y5, Z5 and terminal point coordinate X6, Y6, Z6, extrapolate absolute X, Y, Z coordinate figure XD5, the YD5 of latter end bearing spare part two dowel hole, 0 and XD6, YD6,0, wherein
XD5＝X6+δ1*COSθ0*COSα1+δ2*SINθ0*COSα1+δ3*COSα1-δ4*SINα1
YD5＝Y6+δ1*COSθ0*SINα1+δ2*SINθ0*SINα1+δ3*SINα1+δ4*COSα1
XD6＝X6+δ1*COSθ0*COSα1+δ2*SINθ0*COSα1+δ3*COSα1+δ4*SINα1
YD6＝Y6+δ1*COSθ0*SINα1+δ2*SINθ0*SINα1+δ3*SINα1-δ4*COSα1
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
δ 3 is that latter end bearing spare part is along its Width side and its two dowel holes line of centres vertical range
δ 4 is the half of latter end bearing spare part two dowel hole axis vertical range along its length
α 1 is axis projection line and X-axis angulation value in XOY plane of pipeline spare part latter end, gets acute angle.
The advantage that the present invention has and beneficial effect
Present invention accomplishes the designing requirement of assembly test fixture of all kinds of combustion of aeromotor, lube pipe, to complex geometry, manufacturing tolerance requires tight, and the assembling of all kinds of pipeline component, type position detect Fixture Design and make breakthrough change.Refine the mentality of designing of designer's traditional design pipeline assembly test welding tooling on ordinary days, simplify and solidify its design effectively flow process, carry out necessary data analysis, deduce out each parameter relation, establish algorithm.Set up the parametrization 3-dimensional digital spare part model of pipeline assembly test frock, and set up the general assembly digital model of the parametrization pipeline assembly test frock of associated.Reserve the interface matched with parameter extraction program.The parameter extraction program of the secondary language development based on correspondence is utilized under 3 d modeling software, utilize circulation automatic access 3 d modeling software bottom database, go the feature identifying conduit digital product model, automatic extraction interrelated geometrical parameters, feed back to the geometric feature sizes of the spare part model of characteristic parameter and then driving pipeline assembly test frock, and automatically upgrade the fitted position of the general assembly model of pipeline assembly test frock, assembly relation, the quick computer-aided design (CAD) scheme of the pipeline Fixture Design of tailor for this reason, automatic analysis can be carried out to part, pipeline assembly test frock digital modeling process can be completed fast.And pass through the utilization of the combination mounting technology to standardization, seriation enterprise mark frock element, significantly improve the standardization of Fixture Design, greatly reduce the assembly test frock manufacturing cost of pipeline component, maintenance cost.
By enforcement of the present invention, meet the assembly test Fixture Design of engine gas machine pipeline component.The precision and stability of fixture system is guaranteed by the technological means of automatic analysis, calculating, calibration integration.In the design process, by accurate calculation and analysis methods, determine the scope of the accuracy & error of frock scheme, and arrange best frock layout, liberate the both hands of designer, reduce the labour intensity of designer, greatly reduce manual intervention, designing quality improves greatly.Also for the tasks such as the assembling of frock, the detection of part provide technology efficiently to help.The present invention is used widely in the assembly test Fixture Design work of aeromotor, the various pipeline component of gas turbine, has promotional value very much.Such Fixture Design flow process of thorough change, realizes aeromotor, the digitizing of gas turbine pipeline component processing tool, the Automation Design.
Accompanying drawing explanation
Fig. 1 is process flow diagram of the present invention;
Fig. 2 is frock general assembly model 1 structural representation of the present invention;
Fig. 3 is tool base plate spare part 2 of the present invention and frock general assembly model 1 absolute coordinate system relation schematic diagram;
Fig. 4 is the relation schematic diagram that the present invention chooses that in pipeline spare part 7 two sections form R plane and technological ball spare part 6 centre of sphere in pipeline spare part 7 along Z-direction difference in height minimum tube section;
Fig. 5 is the relation schematic diagram that the present invention chooses the some particular cross section of pipeline spare part 7 and particular segment axis difference technological ball spare part 6 centre of sphere;
Fig. 6 is that the present invention utilizes the first segment data of pipeline spare part 7, determines the physical dimension schematic diagram of first section of bearing spare part 3;
Fig. 7 the present invention utilizes the first segment data of pipeline spare part 7, determines the schematic diagram of the spatial relation of first section of bearing spare part 3;
Fig. 8 is that the present invention utilizes pipeline spare part 7 interlude data, determines the physical dimension schematic diagram of middle each block spare part 5;
Fig. 9 is that the present invention utilizes pipeline spare part 7 interlude data, determines the schematic diagram of the spatial relation of middle each block spare part 5.
Embodiment
1. in Computerized three-dimensional design software, set up a general assembly model 1, a pipeline tool base plate spare part 2 is set up in general assembly model 1, ensure that the lower left corner intersection point of upper surface of base plate spare part 2 overlaps with the absolute initial point of general assembly model 1, base plate spare part 2 length direction overlaps with the absolute coordinate system X-axis of general assembly model 1, base plate spare part 2 Width overlaps with the absolute coordinate system Y-axis of general assembly model 1, XOY plane is formed at base plate spare part 2 upper surface, fit on first section of bearing spare part 3 on base plate spare part 2, latter end bearing spare part 4 and interlude prop up block spare part 5, ensure first section of bearing spare part 3, latter end bearing spare part 4 and interlude prop up block spare part 5 lower surface and base plate spare part 2 upper surface is fitted,
2. plant at base plate spare part 2 upper surface and put technological ball spare part 6, technological ball spare part 6 centre of sphere distance absolute coordinate system ZOY plane is whole value Δ X, technological ball spare part 6 centre of sphere distance absolute coordinate system ZOX plane is whole value Δ Y, and ensures that technological ball spare part 6 centre of sphere distance absolute coordinate system XOY plane is whole value Δ Z.
3. pipeline spare part 7 is assembled in this general assembly model 1 in the mode of absolute initial point; And in pipeline spare part 7, choose two sections in pipeline spare part 7, form a plane R along Z-direction difference in height minimum tube section, in general assembly model 1, retrain this plan range technological ball spare part 6 centre of sphere is a whole value Δ 1, choose the some particular cross section of pipeline spare part 7 to the given whole value Δ 2 of technological ball spare part 6 centre of sphere, and ensure that the axis of this section and technological ball spare part 6 centre of sphere are also whole value Δs 3, and the angle of the axis of this section and X-axis is a whole value Φ;
4. determine the projected angle θ 0 of XOY plane on first section of axis of pipeline spare part 7 and base plate spare part 2, the absolute altitude value Z1 of first section of end face centre point of pipeline spare part 7, according to projected angle θ 0 and absolute altitude value Z1, to determine angle of pitch β 0 and the height value H0 of first section of bearing spare part 3, first section of bearing spare part 3 digital-to-analogue is driven to mate with first section of end face of pipeline spare part 7;
H0＝Z1+δ1*SINθ0－δ2*COSθ0
β0＝θ0
Section bearing spare part 3 feature height value headed by H0
Z1 is the height value of first section of end face centre point distance XOY plane of pipeline spare part 7
Section bearing spare part 3 angle of pitch angle value headed by β 0
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
When giving parameterized first section of bearing spare part 3 H0, β 0 two parameters, the crucial controlling feature of first section of bearing spare part 3 will upgrade, and it will mate with pipeline spare part 7 first sections of end faces, and namely first section of bearing spare part 3 completes deformation process.
5. by the starting point X1 of the axis of first section of pipeline spare part 7, Y1, Z1 and terminal point coordinate X2, Y2, Z2, calculate absolute X, Y, Z coordinate figure XD1, the YD1 of the section of informing against bearing spare part 3 liang of dowel holes 1,2,0 and XD2, YD2,0, wherein
XD1＝X1+δ1*COSθ0*COSα0+δ2*SINθ0*COSα0+δ3*COSα0-δ4*SINα0
YD1＝Y1+δ1*COSθ0*SINα0+δ2*SINθ0*SINα0+δ3*SINα0+δ4*COSα0
XD2＝X1+δ1*COSθ0*COSα0+δ2*SINθ0*COSα0+δ3*COSα0+δ4*SINα0
YD2＝Y1+δ1*COSθ0*SINα0+δ2*SINθ0*SINα0+δ3*SINα0-δ4*COSα0
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
Headed by δ 3, section bearing spare part 3 is along its Width side and its two dowel holes line of centres vertical range
The half of section bearing spare part 3 liang of dowel hole axis vertical range along its length headed by δ 4
α 0 is axis projection line and X-axis angulation value in XOY plane of first section of pipeline spare part 7, gets acute angle.
The absolute X of first section of bearing spare part 3 liang of dowel holes, Y, Z coordinate figure XD1, YD1,0 and XD2, YD2,0 gives the assembly relation expression formula set up between absolute coordinate system in first section of bearing spare part 3 liang of dowel holes and general assembly model 1, correct and unique locus that so first section of bearing spare part 3 just occupies in general assembly model 1.
6.. each interlude of pipeline spare part 7 and the pitching angle theta 1 of base plate spare part 2 upper surface is determined, and the absolute altitude value Zm of this straight-line segment intermediate point, to determine that interlude props up the physical dimension value of block spare part 5.
H1＝Zm-(0.5*D+Ψ)/COSθ1
β1＝θ1
H1 is that interlude props up block spare part 5 feature height value
Zm is the absolute Z value of some interlude pipeline axis intermediate points of pipeline spare part 7
D is the interlude external diameter of pipeline spare part 7
Ψ is the locus degree tolerance that each interlude of pipeline spare part 7 needs to control, aeroengine pipeline processing empirical value
β 1 interlude props up block spare part 5 angle of pitch angle value
When H1, β 1 two parameters are given parameterized interlude and are propped up block spare part 5, the crucial controlling feature that interlude props up block spare part 5 will upgrade, interlude props up block spare part 5 and matches with a certain section of intermediate duct feature of corresponding pipeline spare part 7, and namely interlude props up block spare part 5 and completes deformation process.
7. determine that pipeline interlude props up the rigging position of block spare part 5 in general assembly model 1.By the intermediate point Xm of pipeline spare part 7 interlude axis, Ym, Zm, project to base plate spare part 2 upper surface, extrapolates absolute X, Y, Z coordinate figure XD3, YD3 that interlude props up block spare part 5 liang of dowel holes, and 0 and XD4, YD4,0, wherein
XD3＝Xm+(λ0-D/2-λ1*Tanγ)SINγ+λ1/COSγ
YD3＝Ym-(λ0-D/2-λ1*Tanγ)*COSγ
XD4＝Xm+(λ0+λ2-D/2+λ1*Tanγ)SINγ-λ1/COSγ
YD4＝Ym-(λ0+λ2-D/2+λ1*Tanγ)*COSγ
λ 0 props up block spare part length direction and its nearside dowel hole vertical range for interlude props up block spare part 5 side edge
D is pipeline spare part 7 interlude diameter
λ 1 props up two dowel hole axis of block spare part 5, along the half of its Width vertical range for interlude
λ 2 props up two dowel hole axis, along its length vertical ranges of block spare part 5 for interlude
γ is the projection line of a certain interlude axis of pipeline spare part 7 in XOY plane, with X-axis angle, gets acute angle
Interlude is propped up the absolute X of block spare part 5 liang of dowel holes, Y, Z coordinate figure XD3, YD3,0 and XD4, YD4,0 gives interlude props up the assembly relation expression formula set up between absolute coordinate system in block spare part 5 liang of dowel holes and general assembly model 1, and so interlude props up correct and unique locus that block spare part 5 just occupies in general assembly model 1.
If more than one section of pipeline spare part 7 interlude, then repeat the 6th step, the 7th step, until all finish all for centre sections successively
8. determine the physical dimension of pipeline latter end bearing spare part 4.Determine the projected angle θ 2 of XOY plane on pipeline spare part 7 latter end axis and base plate spare part 2, the absolute altitude value Z6 of pipeline spare part 7 latter end end face centre point, determine the angle of pitch and the height value of latter end bearing spare part 4 according to projected angle θ 2 and absolute altitude value Z6, drive latter end bearing spare part 4 digital-to-analogue to mate with pipeline spare part 7 latter end end face.
Its physical dimension derivation graph of a relation is similar to first section of bearing spare part 3 physical dimension derivation graph of a relation;
H2＝Z6+δ3*SINθ2－δ4*COSθ2
β2＝θ2
H2 is latter end bearing spare part 4 feature height value
Z6 is the absolute Z value of pipeline spare part 7 latter end end face centre point
β 2 latter end bearing spare part 4 angle of pitch angle value
δ 3, δ 4 is that technology controlling and process is to stable constant value
When giving parameterized latter end bearing spare part 4 H2, β 2 two parameters, its crucial controlling feature will upgrade, and latter end bearing spare part 4 will mate with pipeline spare part 7 latter end end face, and namely latter end bearing spare part 4 completes deformation process.
9. determine the rigging position of pipeline latter end bearing spare part 4 in general assembly model 3.By the starting point X5 of pipeline spare part 7 latter end axis, Y5, Z5 and terminal point coordinate X6, Y6, Z6, extrapolate absolute X, Y, Z coordinate figure XD5, the YD5 of latter end bearing spare part 4 liang of dowel holes, 0 and XD6, YD6,0, wherein
Its locus derivation graph of a relation is similar to first section of bearing spare part 3 locus derivation graph of a relation;
XD5＝X6+δ1*COSθ0*COSα1+δ2*SINθ0*COSα1+δ3*COSα1-δ4*SINα1
YD5＝Y6+δ1*COSθ0*SINα1+δ2*SINθ0*SINα1+δ3*SINα1+δ4*COSα1
XD6＝X6+δ1*COSθ0*COSα1+δ2*SINθ0*COSα1+δ3*COSα1+δ4*SINα1
YD6＝Y6+δ1*COSθ0*SINα1+δ2*SINθ0*SINα1+δ3*SINα1-δ4*COSα1
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
δ 3 is that latter end bearing spare part 4 is along its Width side and its two dowel holes line of centres vertical range
δ 4 is the half of the two dowel hole axis vertical range along its length of latter end bearing spare part 4
α 1 is pipeline spare part 7 latter end axis projection line and X-axis angulation value in XOY plane, gets acute angle.
The absolute X of latter end bearing spare part 4 liang of dowel holes, Y, Z coordinate figure XD5, YD5,0 and XD6, YD6,0 gives the assembly relation expression formula set up between absolute coordinate system in its two dowel hole and general assembly model 1, so correct and unique locus of just occupying in general assembly model 1 of latter end bearing spare part 4.
10. in base plate spare part 2, by calculating each bearing spare part, the locus of block spare part makes the register pin pin-and-hole being mapped to base plate spare part 2 upper surface, and joins and make trip bolt threaded hole.
The GB register pin spare part 8 met the specification and GB screw spare part 9, in the corresponding locus by each register pin pin-and-hole and trip bolt threaded hole, are assembled in general assembly model 1 by 11. respectively.
Claims (1)
1., based on a pipeline assembly test Fixture Design method for computer-aided design (CAD), it is characterized in that,
1) in Computerized three-dimensional design software, set up a general assembly model (1), a pipeline tool base plate spare part (2) is set up in general assembly model (1), ensure that the lower left corner intersection point of the upper surface of base plate spare part (2) overlaps with the absolute initial point of general assembly model (1), base plate spare part (2) length direction overlaps with the absolute coordinate system X-axis of general assembly model (1), base plate spare part (2) Width overlaps with the absolute coordinate system Y-axis of general assembly model (1), XOY plane is formed at base plate spare part (2) upper surface, the upper fit on first section of bearing spare part (3) of base plate spare part (2), latter end bearing spare part (4) and interlude prop up block spare part (5), ensure first section of bearing spare part (3), latter end bearing spare part (4) and interlude prop up block spare part (5) lower surface and base plate spare part (2) upper surface is fitted,
2) technological ball spare part (6) is put in the cultivation of base plate spare part (2) upper surface, technological ball spare part (6) centre of sphere distance absolute coordinate system ZOY plane is whole value Δ X, technological ball spare part (6) centre of sphere distance absolute coordinate system ZOX plane is whole value Δ Y, and ensures that technological ball spare part (6) centre of sphere distance absolute coordinate system XOY plane is whole value Δ Z;
3) pipeline spare part (7) is assembled in this general assembly model (1) in the mode of absolute initial point, and in pipeline spare part (7), choose two sections along Z-direction difference in height minimum tube section at pipeline spare part (7) middle formation plane R, in general assembly model (1), this plan range technological ball spare part (6) centre of sphere of constraint is a whole value Δ 1, choose pipeline spare part (7) some particular cross section to the given whole value Δ 2 of technological ball spare part (6) centre of sphere, and ensure that the axis in described difference in height minimum tube section and technological ball spare part (6) centre of sphere are also whole value Δs 3, and the angle of the axis and X-axis of choosing pipeline spare part (7) some particular cross section line segment is a whole value Φ,
4) first section of axis of pipeline spare part (7) and the projected angle θ 0 of the upper XOY plane of base plate spare part (2) is determined, the absolute altitude value Z1 of first section of end face centre point of pipeline spare part (7), according to projected angle θ 0 and absolute altitude value Z1, to determine angle of pitch β 0 and the height value H0 of first section of bearing spare part (3), first section of bearing spare part (3) digital-to-analogue is driven to mate with first section of end face of pipeline spare part (7);
H0＝Z1-δ1*SINθ0－δ2*COSθ0
β0＝θ0
Section bearing spare part (3) feature height value headed by H0
Z1 is the height value of first section of end face centre point distance XOY plane of pipeline spare part (7)
Section bearing spare part (3) angle of pitch angle value headed by β 0
δ 1, δ 2 controls to stable constant value for pipeline assembly technology;
5) by the starting point X1 of the axis of first section of pipeline spare part (7), Y1, Z1 and terminal point coordinate X2, Y2, Z2, absolute X, the Y of the section of informing against bearing spare part (3) two dowel hole is calculated, Z coordinate figure XD1, YD1,0 and XD2, YD2,0, wherein
XD1＝X1+δ1*COSθ0*COSα0+δ2*SINθ0*COSα0+δ3*COSα0-δ4*SINα0
YD1＝Y1+δ1*COSθ0*SINα0+δ2*SINθ0*SINα0+δ3*SINα0+δ4*COSα0
XD2＝X1+δ1*COSθ0*COSα0+δ2*SINθ0*COSα0+δ3*COSα0+δ4*SINα0
YD2＝Y1+δ1*COSθ0*SINα0+δ2*SINθ0*SINα0+δ3*SINα0-δ4*COSα0
δ 1, δ 2 is for controlling to stable constant value for pipeline assembly technology
Headed by δ 3, section bearing spare part (3) is along its Width side and its two dowel holes line of centres vertical range
The half of section bearing spare part (3) two dowel hole axis vertical range along its length headed by δ 4
α 0 is axis projection line and X-axis angulation value in XOY plane of first section of pipeline spare part (7), gets acute angle;
6) each interlude of pipeline spare part (7) and the pitching angle theta 1 of base plate spare part (2) upper surface is determined, and the absolute altitude value Zm of this interlude intermediate point, to determine that interlude props up the physical dimension value of block spare part (5);
H1＝Zm-(0.5*D+Ψ)/COSθ1
β1＝θ1
H1 is that interlude props up block spare part (5) feature height value
Zm is the absolute Z value of some interlude pipeline axis intermediate points of pipeline spare part (7)
D is the interlude external diameter of pipeline spare part (7)
Ψ is the locus degree tolerance that each interlude of pipeline spare part (7) needs to control, aeroengine pipeline processing empirical value
β 1 interlude props up block spare part (5) angle of pitch angle value;
7) by the intermediate point Xm of the interlude axis of pipeline spare part (7), Ym, Zm, project to plate upper surface, extrapolate absolute X, Y, Z coordinate figure XD3, YD3 that interlude props up block spare part (5) two dowel hole, 0 and XD4, YD4,0, wherein
XD3＝Xm+(λ0-D/2-λ1*Tanγ)SINγ+λ1/COSγ
YD3＝Ym-(λ0-D/2-λ1*Tanγ)*COSγ
XD4＝Xm+(λ0+λ2-D/2+λ1*Tanγ)SINγ-λ1/COSγ
YD4＝Ym-(λ0+λ2-D/2+λ1*Tanγ)*COSγ
λ 0 for interlude prop up block spare part (5) side along its length with its nearside dowel hole vertical range
D is the interlude face of cylinder external diameter of pipeline spare part (7)
λ 1 props up two dowel hole axis of block spare part (5), along the half of its Width vertical range for interlude
λ 2 props up two dowel hole axis, along its length vertical ranges of block spare part (5) for interlude
γ is the projection line of a certain interlude axis of pipeline spare part (7) in XOY plane, with X-axis angle, gets acute angle
Successively all interludes of pipeline spare part (7) are all finished
8) the latter end axis of pipeline spare part (7) and the projected angle θ 2 of the upper XOY plane of base plate spare part (2) is determined, the absolute altitude value Z6 of the end face centre point of pipeline spare part (7) latter end, determine angle of pitch β 2 and the height value H2 of latter end bearing spare part (4) according to projected angle θ 2 and absolute altitude value Z6, drive latter end bearing spare part (4) digital-to-analogue to mate with pipeline spare part (7) latter end end face;
H2＝Z6+δ1*SINθ0－δ2*COSθ0
β2＝θ2
H2 is pipeline latter end bearing spare part (4) feature height value
Z6 is the height value of the latter end end face centre point distance XOY plane of pipeline spare part (7)
β 2 is latter end bearing spare part (4) angle of pitch angle value
δ 1, δ 2 controls to stable constant value for pipeline assembly technology;
9) by the starting point X5 of the axis of pipeline spare part (7) latter end, Y5, Z5 and terminal point coordinate X6, Y6, Z6, absolute X, the Y of latter end bearing spare part (4) two dowel hole is extrapolated, Z coordinate figure XD5, YD5,0 and XD6, YD6,0, wherein
XD5＝X6+δ1*COSθ0*COSα1+δ2*SINθ0*COSα1+δ3*COSα1-δ4*SINα1
YD5＝Y6+δ1*COSθ0*SINα1+δ2*SINθ0*SINα1+δ3*SINα1+δ4*COSα1
XD6＝X6+δ1*COSθ0*COSα1+δ2*SINθ0*COSα1+δ3*COSα1+δ4*SINα1
YD6＝Y6+δ1*COSθ0*SINα1+δ2*SINθ0*SINα1+δ3*SINα1-δ4*COSα1
δ 1, δ 2 controls to stable constant value for pipeline assembly technology
δ 3 is that latter end bearing spare part (4) is along its Width side and its two dowel holes line of centres vertical range
δ 4 is the half of latter end bearing spare part (4) two dowel hole axis vertical range along its length
α 1 is axis projection line and X-axis angulation value in XOY plane of pipeline spare part (7) latter end, gets acute angle.
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| CN105488294B (en) * | 2015-12-12 | 2018-08-24 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft tube runs performance simulation geometric data extraction method |
| CN107229779B (en) * | 2017-05-10 | 2020-07-28 | 中北大学 | UG expression suppression feature-based parametric modeling method for bullet warhead |
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| CN111897287B (en) * | 2020-06-17 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Conduit installation error modeling and compensating method based on digital quantity |
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| CN113182764B (en) * | 2021-03-31 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | CATIA-based flange plate positioning method facing pipe welding fixture |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101430732A (en) * | 2008-12-04 | 2009-05-13 | 上海交通大学 | Engine pipe laying system |
| CN201594263U (en) * | 2010-03-30 | 2010-09-29 | 中十冶集团有限公司 | Pipelining dynamic simulation device |
| CN102411662A (en) * | 2011-12-27 | 2012-04-11 | 北京航空航天大学 | Automatic configuring method and system for reconfigurable tooling of pipeline assembly welding |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101430732A (en) * | 2008-12-04 | 2009-05-13 | 上海交通大学 | Engine pipe laying system |
| CN201594263U (en) * | 2010-03-30 | 2010-09-29 | 中十冶集团有限公司 | Pipelining dynamic simulation device |
| CN102411662A (en) * | 2011-12-27 | 2012-04-11 | 北京航空航天大学 | Automatic configuring method and system for reconfigurable tooling of pipeline assembly welding |
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