CN102855362A - Computer aided design based pipeline assembly inspection fixture design method - Google Patents
Computer aided design based pipeline assembly inspection fixture design method Download PDFInfo
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Abstract
The invention belongs to the field of digitalized designs and relates to a computer aided design based pipeline assembly inspection fixture design method used for machining of pipeline parts of aero-engines and gas turbines. The method includes: setting a parametric three-dimensional digital component model of a pipeline assembly inspection fixture, setting a final assembly digital model of a parametric pipeline assembly inspection fixture associated with the parametric three-dimensional digital component model, reserving an interface matched with a parameter extraction procedure, using a parameter extraction procedure based on corresponding secondary language development under three-dimensional modeling software and cyclically and automatically accessing to a lowermost database of the three-dimensional modeling software to recognize characteristics of a guide pipe digital product model, automatically extracting related geometric parameters, feeding back characteristic parameters, driving geometric feature size of the component model of the pipeline assembly inspection fixture, and automatically updating the assembly relation and assembly size of the final assembly model of the pipeline assembly inspection fixture. By means of the computer aided design based pipeline assembly inspection fixture design method, parts can be analyzed automatically, and digital modeling of the pipeline assembly inspection fixture can be completed quickly.
Description
Technical field
The invention belongs to the Design of digital field, relate to the pipeline assembly test Fixture Design method based on computer-aided design (CAD) of the pipeline component processing usefulness in a kind of aeromotor, the gas turbine.
Background technology
In order to save the space, the overlapped intersection of various circuit design is interfered mutually for fear of pipeline on engine and the gas turbine, and the spatial geometric shape of conduit is very complicated.Pipeline component is wide in variety in addition, quantity is huge, the size is different in size, and tighter manufacturing tolerance requirement is arranged.After the guiding-tube bend moulding, with various pipe adapters with flange welds and examination is detected in its position, must there be respective line parts assembly test frock to cooperate this work of finishing for this reason.The relevant tool of pipeline component all is to rely on the manual two-dimensional design of Fixture Design personnel at present, because the pipeline locus is complicated, characterize the accurate locus of each section pipeline, when two-dimensional design, projection relation is complicated, and need abundant space imagination and jig Design experience, repeatedly can reach requirement through repeatedly adjusting.Because the design effort amount is large, the conduit spatial complex causes design efficiency low in addition, and designing quality is difficult to guarantee.
Summary of the invention
The objective of the invention is to propose a kind of check Fixture Design efficient high, the measured pipeline assembly test Fixture Design method based on computer-aided design (CAD) of matter.
Technical solution of the present invention
1). in the Computerized three-dimensional design software, set up a general assembly model, in the general assembly model, set up a pipeline frock base plate spare part, the lower left corner intersection point that guarantees the 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, form XOY plane at base plate spare part upper surface, first section bearing spare part of fit on the base plate spare part, latter end bearing spare part and interlude prop up the piece spare part, guarantee first section bearing spare part, latter end bearing spare part and interlude prop up piece spare part lower surface and base plate spare part upper surface is fitted;
2). put the technological ball spare part in the cultivation of base plate spare part upper surface, the technological ball spare part centre of sphere is whole value Δ X apart from absolute coordinate system ZOY plane, the technological ball spare part centre of sphere is whole value Δ Y apart from absolute coordinate system ZOX plane, and guarantees that the technological ball spare part centre of sphere is whole value Δ Z apart from the absolute coordinate system XOY plane.
3). the mode of pipeline spare part with absolute initial point is assembled in this general assembly model; And in the pipeline spare part, choose two sections and in the pipeline spare part, form a plane R along Z-direction difference in height minimum tube highway section, this plan range technological ball spare part centre of sphere of constraint is a whole value Δ 1 in the general assembly model, 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 guarantee that the axis of this section and the technological ball spare part centre of sphere also are 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 axis of pipeline spare part and the base plate spare part, the absolute altitude value Z1 of first section 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 bearing spare part, drive first section end face coupling of first section bearing spare part digital-to-analogue and pipeline spare part;
H0=Z1+δ1*SINθ0－δ2*COSθ0
β0=θ0
Section bearing spare part feature height value headed by the H0
Z1 is the height value on first section end face centre point distance X OY plane of pipeline spare part
Section bearing spare part luffing angle value headed by the β 0
5). by starting point X1, Y1, Z1 and terminal point coordinate X2, Y2, the Z2 of the axis of first section of pipeline spare part, calculate the absolute X of the section of informing against bearing spare part two dowel holes, Y, 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
Section bearing spare part is along its Width side and its two dowel holes line of centres vertical range headed by the δ 3
Section bearing spare part two dowel hole axis are along half of its length direction vertical range headed by the δ 4
6). determine the pitching angle theta 1 of each interlude and the base plate spare part upper surface of pipeline spare part, and the absolute altitude value Zm of this straight-line segment intermediate point, with the physical dimension value of determining that interlude props up the piece spare part.
H1=Zm-（0.5*D+Ψ）/COSθ1
β1=θ1
H1 is that interlude props up piece 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 need to be controlled, aeroengine pipeline processing empirical value
7). by the intermediate point Xm of the interlude axis of pipeline spare part, Ym, Zm projects to plate upper surface, extrapolates the absolute X that interlude props up piece spare part two dowel holes, Y, Z coordinate figure XD3, YD3,0 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
D is the interlude face of cylinder external diameter of pipeline spare part
γ is the projection line of a certain interlude axis of pipeline spare part on XOY plane, with the X-axis angle, gets acute angle and successively all interludes of pipeline spare part is all finished
8). determine the projected angle θ 2 of XOY plane on the latter end axis of pipeline spare part and the 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 and 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 on the latter end end face centre point distance X OY plane of pipeline spare part
9). by starting point X5, Y5, Z5 and terminal point coordinate X6, Y6, the Z6 of the axis of pipeline spare part latter end, extrapolate the absolute X of latter end bearing spare part two dowel holes, Y, 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
The advantage that the present invention has and beneficial effect
The present invention has satisfied the designing requirement of the assembly test anchor clamps of aeromotor all kinds of combustions, lube pipe, and to complex geometry, manufacturing tolerance requires tight, and the assembling of all kinds of pipeline components, type position are detected Fixture Design and made breakthrough change.Refine the on ordinary days mentality of designing of traditional design pipeline assembly test welding tooling of designer, simplify and solidify its effective design cycle, 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 that is complementary with the parameter extraction program.Under 3 d modeling software, utilize the parameter extraction program based on the secondary language development of correspondence, utilize circulation automatic access 3 d modeling software bottom database, go to identify the feature of conduit digital product model, automatically extract 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 for this reason formulating specially, can carry out automatic analysis to part, can finish fast pipeline assembly test frock digital modeling process.And by the utilization to the combination mounting technology of standardization, seriation enterprise mark frock element, the standardization that has significantly improved Fixture Design greatly reduces the assembly test frock manufacturing cost of pipeline component, maintenance cost.
By enforcement of the present invention, satisfied the assembly test Fixture Design of engine gas machine pipeline component.Guarantee the precision and stability of fixture system by automatic analysis, calculating, the integrated technological means of calibration.In design process, by accurate computational analysis method, determine the scope of the accuracy ﹠ error of frock scheme, and arranging best frock layout, the both hands of having liberated the designer have reduced designer's labour intensity, greatly reduced manual intervention, designing quality improves greatly.Also provide efficiently technology help for the assembling of frock, the tasks such as detection of part.The present invention is used widely in the assembly test Fixture Design work of aeromotor, the various pipeline components of gas turbine, and promotional value is arranged very much.Thoroughly change such Fixture Design flow process, realize digitizing, the Automation Design of aeromotor, gas turbine pipeline component processing tool.
Description of drawings
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 that frock base plate spare part 2 of the present invention concerns schematic diagram with frock general assembly model 1 absolute coordinate system;
Fig. 4 is that the present invention chooses two sections schematic diagram that concern that form R plane and technological ball spare part 6 centre ofs sphere along Z-direction difference in height minimum tube highway section in pipeline spare part 7 in pipeline spare part 7;
Fig. 5 is the schematic diagram that concerns that the present invention chooses pipeline spare part 7 some particular cross section and particular segment axis difference technological ball spare part 6 centre ofs sphere;
Fig. 6 is that the present invention utilizes pipeline spare part 7 first segment datas, determines the physical dimension schematic diagram of first section 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 bearing spare part 3;
Fig. 8 is that the present invention utilizes pipeline spare part 7 interlude data, the physical dimension schematic diagram of each piece spare part 5 in the middle of determining;
Fig. 9 is that the present invention utilizes pipeline spare part 7 interlude data, the schematic diagram of the spatial relation of each piece spare part 5 in the middle of determining.
Embodiment
1. in the Computerized three-dimensional design software, set up a general assembly model 1, in general assembly model 1, set up a pipeline frock base plate spare part 2, the lower left corner intersection point that guarantees 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 directions overlap with the absolute coordinate system X-axis of general assembly model 1, base plate spare part 2 Widths overlap with the absolute coordinate system Y-axis of general assembly model 1, form XOY plane at base plate spare part 2 upper surfaces, first section bearing spare part 3 of fit on base plate spare part 2, latter end bearing spare part 4 and interlude prop up piece spare part 5, guarantee first section bearing spare part 3, latter end bearing spare part 4 and interlude prop up piece spare part 5 lower surfaces and base plate spare part 2 upper surfaces are fitted;
2. plant at base plate spare part 2 upper surfaces and put technological ball spare part 6, technological ball spare part 6 centre ofs sphere are whole value Δ X apart from absolute coordinate system ZOY plane, technological ball spare part 6 centre ofs sphere are whole value Δ Y apart from absolute coordinate system ZOX plane, and guarantee that technological ball spare part 6 centre ofs sphere are whole value Δ Z apart from the absolute coordinate system XOY plane.
3. the mode of pipeline spare part 7 with absolute initial point is assembled in this general assembly model 1; And in pipeline spare part 7, choose two sections and in pipeline spare part 7, form a plane R along Z-direction difference in height minimum tube highway section, these plan range technological ball spare part 6 centre ofs sphere of constraint are a whole value Δ 1 in general assembly model 1, choose pipeline spare part 7 some particular cross section to the given whole value Δ 2 of technological ball spare part 6 centre ofs sphere, and guarantee that the axis of this section and technological ball spare part 6 centre ofs sphere also are 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 axis of pipeline spare part 7 and the base plate spare part 2, the absolute altitude value Z1 of first section 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 bearing spare part 3, drive first section end face coupling of first section bearing spare part 3 digital-to-analogues and pipeline spare part 7;
H0=Z1+δ1*SINθ0－δ2*COSθ0
β0=θ0
Section bearing spare part 3 feature height values headed by the H0
Z1 is the height value on first section end face centre point distance X OY plane of pipeline spare part 7
Section bearing spare part 3 luffing angle values headed by the β 0
When H0,0 two parameters of β are given parameterized first section bearing spare part 3, and the crucial controlling feature of first section bearing spare part 3 will upgrade, its will with 7 first sections end faces couplings of pipeline spare part, namely first section bearing spare part 3 finished deformation process.
5. by starting point X1, Y1, Z1 and terminal point coordinate X2, Y2, the Z2 of the axis of 7 first sections of pipeline spare parts, calculate the absolute X of 3 liang of dowel holes 1,2 of the section of informing against bearing spare part, Y, 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
Section bearing spare part 3 is along its Width side and its two dowel holes line of centres vertical range headed by the δ 3
Section bearing spare part 3 liang of dowel hole axis are along half of its length direction vertical range headed by the δ 4
The absolute X of 3 liang of dowel holes of first section bearing spare part, Y, Z coordinate figure XD1, YD1,0 and XD2, YD2,0 gives the assembly relation expression formula of setting up between the absolute coordinate system in 3 liang of dowel holes of first section bearing spare part and the general assembly model 1, correct and unique locus that so first section bearing spare part 3 just occupied in general assembly model 1.
6.. determine each interlude of pipeline spare part 7 and the pitching angle theta 1 of base plate spare part 2 upper surfaces, and the absolute altitude value Zm of this straight-line segment intermediate point, with the physical dimension value of determining that interlude props up piece spare part 5.
H1=Zm-（0.5*D+Ψ）/COSθ1
β1=θ1
H1 is that interlude props up piece spare part 5 feature height values
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 need to be controlled, aeroengine pipeline processing empirical value
When H1,1 two parameters of β are given parameterized interlude and are propped up piece spare part 5, the crucial controlling feature that interlude props up piece spare part 5 will upgrade, interlude props up piece spare part 5 and will be complementary with a certain section intermediate duct feature of corresponding pipeline spare part 7, and namely interlude props up piece spare part 5 and finished deformation process.
7. determine that the pipeline interlude props up the rigging position of piece spare part 5 in general assembly model 1.By the intermediate point Xm of pipeline spare part 7 interlude axis, Ym, Zm projects to base plate spare part 2 upper surfaces, extrapolates the absolute X that interlude props up 5 liang of dowel holes of piece spare part, Y, Z coordinate figure XD3, YD3,0 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
D is pipeline spare part 7 interlude diameters
γ is the projection lines of pipeline spare part 7 a certain interlude axis on XOY plane, with the X-axis angle, gets acute angle
Interlude is propped up the absolute X of 5 liang of dowel holes of piece spare part, Y, Z coordinate figure XD3, YD3,0 and XD4, YD4,0 gives interlude props up the assembly relation expression formula of setting up between the absolute coordinate system in 5 liang of dowel holes of piece spare part and the general assembly model 1, and interlude props up correct and unique locus that piece spare part 5 has just occupied in general assembly model 1 so.
If more than one section of pipeline spare part 7 interludes then repeated for the 6th step, the 7th step is until all finish all sections of centre 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 the base plate spare part 2, the absolute altitude value Z6 of pipeline spare part 7 latter end end face centre points, 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-analogues and mate with pipeline spare part 7 latter end end faces.
Its physical dimension derivation graph of a relation is similar to first section bearing spare part 3 physical dimension derivation graphs of a relation;
H2=Z6+δ3*SINθ2－δ4*COSθ2
β2=θ2
H2 is latter end bearing spare part 4 feature height values
Z6 is the absolute Z value of pipeline spare part 7 latter end end face centre points
When H2,2 two parameters of β are given parameterized latter end bearing spare part 4, and its crucial controlling feature will upgrade, latter end bearing spare part 4 will with pipeline spare part 7 latter end end faces coupling, namely latter end bearing spare part 4 has been finished deformation process.
9. determine the rigging position of pipeline latter end bearing spare part 4 in general assembly model 3.By starting point X5, Y5, Z5 and terminal point coordinate X6, Y6, the Z6 of pipeline spare part 7 latter end axis, extrapolate the absolute X of 4 liang of dowel holes of latter end bearing spare part, Y, Z coordinate figure XD5, YD5,0 and XD6, YD6,0, wherein
Its locus derivation graph of a relation is similar to first section bearing spare part 3 locus derivation graphs 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
The absolute X of 4 liang of dowel holes of latter end bearing spare part, Y, Z coordinate figure XD5, YD5,0 and XD6, YD6,0 give the assembly relation expression formula of setting up between the absolute coordinate system in its two dowel hole and the general assembly model 1, so correct and unique locus of just having occupied in general assembly model 1 of latter end bearing spare part 4.
10. in base plate spare part 2, make the register pin pin-and-hole that is mapped to base plate spare part 2 upper surfaces by the locus that calculates each bearing spare part, a piece spare part, and join and make the trip bolt threaded hole.
11. the corresponding locus by each register pin pin-and-hole and trip bolt threaded hole is assembled to GB register pin spare part 8 and the GB screw spare part 9 that meets the specification respectively in the general assembly model 1.
Claims (1)
1. the pipeline assembly test Fixture Design method based on computer-aided design (CAD) is characterized in that,
1) in the Computerized three-dimensional design software, sets up a general assembly model (1), in general assembly model (1), set up a pipeline frock base plate spare part (2), the lower left corner intersection point that guarantees 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), form XOY plane at base plate spare part (2) upper surface, at the upper first section bearing spare part of fit on (3) of base plate spare part (2), latter end bearing spare part (4) and interlude prop up piece spare part (5), guarantee first section bearing spare part (3), latter end bearing spare part (4) and interlude prop up piece spare part (5) lower surface and base plate spare part (2) upper surface is fitted;
2) put technological ball spare part (6) in the cultivation of base plate spare part (2) upper surface, technological ball spare part (6) centre of sphere is whole value Δ X apart from absolute coordinate system ZOY plane, technological ball spare part (6) centre of sphere is whole value Δ Y apart from absolute coordinate system ZOX plane, and guarantees that technological ball spare part (6) centre of sphere is whole value Δ Z apart from the absolute coordinate system XOY plane;
3) mode of pipeline spare part (7) with absolute initial point is assembled in this general assembly model (1); And in pipeline spare part (7), choose two sections and in pipeline spare part (7), form a plane R along Z-direction difference in height minimum tube highway section, this plan range technological ball spare part (6) centre of sphere of constraint is a whole value Δ 1 in general assembly model (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 guarantee that the axis of this section and technological ball spare part (6) centre of sphere also are whole value Δs 3, and the angle of the axis of this section and X-axis is a whole value Φ;
4) determine first section axis of pipeline spare part (7) and the projected angle θ 0 of the upper XOY plane of base plate spare part (2), the absolute altitude value Z1 of first section 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 bearing spare part (3), drive first section end face coupling of first section bearing spare part (3) digital-to-analogue and pipeline spare part (7);
H0=Z1+δ1*SINθ0－δ2*COSθ0
β0=θ0
Section bearing spare part (3) feature height value headed by the H0
Z1 is the height value on first section end face centre point distance X OY plane of pipeline spare part (7)
Section bearing spare part (3) luffing angle value headed by the β 0
δ 1, and δ 2 is for controlling to stable constant value for the pipeline assembly technology;
5) by starting point X1, Y1, Z1 and terminal point coordinate X2, Y2, the Z2 of the axis of first section of pipeline spare part (7), calculate the absolute X of the section of informing against bearing spare part (3) two dowel holes, Y, 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, and δ 2 is for controlling to stable constant value for the pipeline assembly technology
Section bearing spare part (3) is along its Width side and its two dowel holes line of centres vertical range headed by the δ 3
Section bearing spare part (3) two dowel hole axis are along half of its length direction vertical range headed by the δ 4
α 0 is axis projection line and X-axis angulation value on XOY plane of first section of pipeline spare part (7), gets acute angle;
6) determine the pitching angle theta 1 of each interlude and base plate spare part (2) upper surface of pipeline spare part (7), and the absolute altitude value Zm of this straight-line segment intermediate point, with the physical dimension value of determining that interlude props up piece spare part (5).
H1=Zm-（0.5*D+Ψ）/COSθ1
β1=θ1
H1 is that interlude props up piece 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) need to be controlled, aeroengine pipeline processing empirical value
β 1 interlude props up piece spare part (5) luffing angle value;
7) by the intermediate point Xm of the interlude axis of pipeline spare part (7), Ym, Zm projects to plate upper surface, extrapolates the absolute X that interlude props up piece spare part (5) two dowel holes, Y, Z coordinate figure XD3, YD3,0 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 piece spare part (5) side along its length direction and its nearside dowel hole vertical range for interlude
D is the interlude face of cylinder external diameter of pipeline spare part (7)
λ 1 props up two dowel hole axis of piece spare part (5) for interlude, along half of its Width vertical range
λ 2 props up two dowel hole axis of piece spare part (5) for interlude, along its length direction vertical range
γ is the projection line of a certain interlude axis of pipeline spare part (7) on XOY plane, with the X-axis angle, gets acute angle
Successively all interludes of pipeline spare part (7) are all finished
8) determine 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), 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 and 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 on the latter end end face centre point distance X OY plane of pipeline spare part (7)
β 2 is latter end bearing spare part (4) luffing angle value
δ 1, and δ 2 is for controlling to stable constant value for the pipeline assembly technology;
9) by starting point X5, Y5, Z5 and terminal point coordinate X6, Y6, the Z6 of the axis of pipeline spare part (7) latter end, extrapolate the absolute X of latter end bearing spare part (4) two dowel holes, Y, 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, and δ 2 is for controlling to stable constant value for the 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 latter end bearing spare part (4) two dowel hole axis along half of its length direction vertical range
α 1 is axis projection line and X-axis angulation value on XOY plane of pipeline spare part (7) latter end, gets acute angle.
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Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AECC AVIATION POWER CO,LTD. Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: XI'AN AVIATION POWER Co.,Ltd. |