CN104199383A - Aviation engine case part milling blank automatic generation method - Google Patents
Aviation engine case part milling blank automatic generation method Download PDFInfo
- Publication number
- CN104199383A CN104199383A CN201410381573.3A CN201410381573A CN104199383A CN 104199383 A CN104199383 A CN 104199383A CN 201410381573 A CN201410381573 A CN 201410381573A CN 104199383 A CN104199383 A CN 104199383A
- Authority
- CN
- China
- Prior art keywords
- casing
- line
- boss
- face
- profile
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 54
- 238000003801 milling Methods 0.000 title claims abstract description 41
- 238000007514 turning Methods 0.000 claims abstract description 29
- 238000005520 cutting process Methods 0.000 claims abstract description 18
- 230000007704 transition Effects 0.000 claims abstract description 11
- 238000000605 extraction Methods 0.000 claims abstract description 3
- 239000000284 extract Substances 0.000 claims description 19
- 239000007787 solid Substances 0.000 claims description 4
- 238000003860 storage Methods 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 18
- 238000005516 engineering process Methods 0.000 description 7
- 102100027668 Carboxy-terminal domain RNA polymerase II polypeptide A small phosphatase 1 Human genes 0.000 description 4
- 101710134395 Carboxy-terminal domain RNA polymerase II polypeptide A small phosphatase 1 Proteins 0.000 description 4
- 102100027667 Carboxy-terminal domain RNA polymerase II polypeptide A small phosphatase 2 Human genes 0.000 description 4
- 101710134389 Carboxy-terminal domain RNA polymerase II polypeptide A small phosphatase 2 Proteins 0.000 description 4
- 241000581364 Clinitrachus argentatus Species 0.000 description 4
- 230000002452 interceptive effect Effects 0.000 description 4
- PUPNJSIFIXXJCH-UHFFFAOYSA-N n-(4-hydroxyphenyl)-2-(1,1,3-trioxo-1,2-benzothiazol-2-yl)acetamide Chemical compound C1=CC(O)=CC=C1NC(=O)CN1S(=O)(=O)C2=CC=CC=C2C1=O PUPNJSIFIXXJCH-UHFFFAOYSA-N 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Landscapes
- Milling Processes (AREA)
Abstract
Disclosed is an aviation engine case part milling blank automatic generation method. The aviation engine case part milling blank automatic generation method is characterized by comprising performing characteristic recognition on an aviation engine case part to obtain the geometric information of case part characteristics; performing case and boss contour information extraction to obtain the rotary contour of a case and the rotary contour of a boss; performing offset and combination on the boss contour according to the process information such as the allowance required by the case milling and the width of a turning cutting tool to obtain the generalized boss contour; searching the case blank contour according to the rotary contour of the case and the generalized boss contour, setting rounded corner transition at the turning position of contour concave connection according to the rounded corner information of the case turning cutting tool and constructing a case part milling blank rotary contour line to automatically generate the case milling blank. According to the aviation engine case part milling blank automatic generation method, the aviation engine case part milling blank can be automatically and correctly generated, the generation efficiency is high, and the reliability is high.
Description
Technical field
The present invention relates to a kind of CAD/CAM technology, especially a kind of aero-engine casing machinery CNC processing technology, specifically a kind of aero-engine casing part milling blank automatic generation method.
Background technology
CAD, CAPP, CAM system are being brought into play very large effect respectively aspect modern product design, technological design and numerical control programming.After completing product design, enter technological design during the stage, often need according to the blank model of product parts model reverse part, as the basis of part process design.But existing CAD, CAM software can not generate the blank of a certain manufacturing procedure automatically, as certain step operation adopts the technique different from front step, when processing is only carried out the part of part, obtain the blank of partial operation, can only be by the method for manual modeling.Before and after considering, the processing technology of two steps, obtains current operation blank automatically, in CAD, CAM are integrated, has very important significance.
Casing is one of strength member of aeromotor, is " pedestal " of whole aeromotor: its inside is main shaft and blade, and the various annexes of outside connection, comprise oil pipe, cooling tube, control system etc., all very high to the requirement of intensity and precision.On case structure, be to take the circular ring structure that gyroscope wheel hub face is main body, the column that circumferentially distributes island boss, part thinnest part is only that 2-3mm is thick, belongs to archipelago small island complex thin-wall structural member.
In the digital control processing of casing, the shaping of its surperficial boss often adopts the method for milling, and the Transition rough before casing milling is generally the revolving meber after turning.Before Milling Process programming, need to build according to casing part model the milling blank of casing.Build at present casing milling blank and mainly by technologist, complete by hand, modeling process is complicated, length consuming time, and the required surplus of milling be provided with very large randomness.The situation incomplete same to the size of one deck boss, often determines the full-size of revolution sketch by eye-observation or the simple method of measuring, and need to take multiple measurements or revise, to guarantee reasonably to setover surplus, process is loaded down with trivial details, inefficiency.
Feature is the carrier of processing technology knowledge and experience, can effectively inherit processing technology knowledge and experience, based on feature, can realize process planning rapidly and efficiently.Feature identification technique is the bridge between product design and technological design, feature identification technique is according to the process characteristic of engine crankcase processing at present, aero-engine casing part machining feature is summarized as to casing ring groove and ring groove boss, method based on the expansion of seed face, casing part ring groove and boss feature are carried out to efficient identification, obtain the effective information of process decision.Aero-engine casing feature identification technique, for the automatic generation of aero-engine casing part milling blank is laid a good foundation.
The invention discloses a kind of aero-engine casing part milling blank automatic generation method, belong to CAD/CAM field.First the method carries out feature identification to aero-engine casing part, or directly reads the characteristic information of casing part, obtains the geological information of casing part feature; Then carry out casing and boss profile information and extract, obtain the revolution profile of casing and boss; According to the required surplus of casing milling and turning cutting tool width and other processes information, boss profile is setovered and merged, obtain Generalized Convex chaptrel wide; Again according to casing revolution profile and the wide search of Generalized Convex chaptrel casing blank profile, and according to casing turning cutting tool fillet information, turning point to the recessed connection of profile arranges round-corner transition, constructs casing part milling blank gyroscope wheel profile, automatically generates casing milling blank.The method can automatically, correctly generate aero-engine casing milling blank, the traditional blank structure of effective solution complex operation, the shortcoming that experience dependence is strong, and the technological parameters such as turning cutting tool fillet and the required surplus of milling can be accurately set, formation efficiency is high, reliability is strong, the blank generating both can be used as the final part model of turning processing, the initial blank that can be used as again milling has great importance in actual production.
Summary of the invention
The object of the invention is to build for current aero-engine casing part milling blank model that efficiency is low, the problem of the defect of poor accuracy, invent a kind of method that aero-engine casing part milling blank based on feature technology generates automatically.
Technical scheme of the present invention is:
The method that aero-engine casing part milling blank generates automatically, is characterized in that it comprises the following steps:
Step 1, identifies or reads casing feature, obtains the face geological information of casing;
Step 2, creates casing axis of rotation and sketch plane, extracts casing outline line;
Step 3, extracts boss gyroscope wheel profile, is rotated to sketch plane, and setovers by the required surplus of milling;
Step 4, according to turning cutting tool width, the distance between merging adjacent lands profile is less than the boss profile of cutter width, obtains Generalized Convex chaptrel wide;
Step 5, according to casing outline line and Generalized Convex chaptrel profile, search casing blank outline, and press turning cutting tool fillet information, and in the turning point of the recessed connection of profile, round-corner transition is set, obtain casing blank sketch profile;
Step 6, generates solid of revolution with casing blank sketch profile, obtains casing milling blank;
Described establishment casing axis of rotation and sketch plane, the method for extracting casing outline line is:
Extract the axis of rotation of a casing ring groove bottom surface, as casing axis, a bit to create plane on casing axis and this ring groove bottom surface, as the sketch plane of casing blank, sketch plane and casing face are asked to hand over and are obtained casing outline line.
The method of described extraction boss gyroscope wheel profile comprises the steps:
1) extract the direction line of end face and side.With boss end face central point and casing axis, make plane, as boss, hand over plane, boss hands over plane and boss end face and side to intersect, and intersection is respectively end face direction line and side surface direction line;
2) extract boss end face and side profile reference mark.With dichotomy, to boss end face outer annular edge, carry out discrete, obtain the unique point of boss end face outer annular edge, boss end face outer annular edge unique point is rotated to boss and hand over plane, find the point of end face direction line vertical range maximum as end face profile reference mark, find end face central point along the point of end face direction linear distance maximum, as boss side surfaces profile reference mark;
3) take end face profile reference mark is starting point, and the end face direction line of take is direction, and the distance of side profile reference mark to end face central point along end face direction line is that length extends to both sides is end face largest contours line as straight line; The two-end-point of end face largest contours line of take is starting point, and side surface direction line is direction, makes two straight lines crossing with casing ring groove bottom surface, and two straight lines are side largest contours line, and the combination of end face and side largest contours line is boss gyroscope wheel profile.
Described according to turning cutting tool width, merge the boss profile that distance between adjacent lands profile is less than cutter width, the method that obtains Generalized Convex chaptrel exterior feature is:
Compare between two the end points coordinate of sketch plane convex platform profile top line and side line, if two line endpoints overlap between two, delete a coincidence line; If two line endpoints does not overlap, and certain two end-point distances is less than the technological requirement of turning cutting tool width, as straight line, join two endpoints, the straight line of doing as the part of profile, add in boss outline line.Remove coincidence line, add the boss outline line combination connecting after straight line, be Generalized Convex chaptrel wide.
Described according to casing outline line and Generalized Convex chaptrel profile, search casing blank outline, and press turning cutting tool fillet information, and in the turning point of the recessed connection of profile, round-corner transition being set, the method that obtains casing blank sketch profile comprises the steps:
1) Generalized Convex chaptrel profile and casing outline line are decomposed with profile take-off point, obtain decomposing outline line;
2) to decomposing outline line, search in the counterclockwise direction.Concrete grammar is, the silhouette edge being connected with casing outline upper extreme point of take is an initial line, be made as current silhouette edge, find the limit being connected with the counterclockwise working direction end points of current silhouette edge, obtain the counterclockwise angle of itself and current silhouette edge, the limit of angle minimum is outline limit, is made as the front of working as of next round search; If minimum angle is less than 180 degree,, between two outline limits, be recessed connection, between both sides, by turning cutting tool fillet information, round-corner transition is set, fillet line is as the part storage of outline, so circulation, until when front is connected with casing outline lower extreme point, search finishes, and obtains casing blank outline.
The invention has the beneficial effects as follows:
The present invention can automatically, correctly generate aero-engine casing milling blank according to casing feature, efficiently solve traditional blank and build complex operation, shortcoming that experience dependence is strong, and the technological parameters such as turning cutting tool fillet and the required surplus of milling can be accurately set, have advantages of that formation efficiency is high, reliability is strong, the blank generating both can be used as the final part model of turning processing, the initial blank that can be used as again milling has great importance in actual production.
Accompanying drawing explanation
Fig. 1 is aero-engine casing part milling blank automatic generation method process flow diagram of the present invention.
Fig. 2 is aero-engine casing monnolithic case of the present invention and characterizing definition schematic diagram.In figure, A is ring groove end face, and B is ring groove side, and C is ring groove base angle face, and D is ring groove bottom surface, and E is casing end face, and F is casing inside surface, and TF is boss end face, and SF is boss side surfaces, and CF is boss base angle face.
Fig. 3 is that aero-engine casing profile of the present invention extracts schematic diagram.In figure, CA is casing axis, and SP is sketch plane, and COL is casing outline, and CIL is profile in casing.
Fig. 4 is that boss profile of the present invention extracts schematic diagram.In figure: a is boss profile schematic diagram, wherein MP is boss end face central point, and IP is that boss is handed over plane, TL is boss end face direction line, and SL is boss side surfaces direction line, and FP is boss end face outer annular edge unique point, TML is boss end face largest contours line, and SML is boss side surfaces largest contours line.B is that boss end face outer annular edge unique point rotates to boss and hands over floor map, and wherein TCP is boss end face profile reference mark, and SCP1, SCP2 are boss side surfaces profile reference mark, Ds1 be SCP1 to the distance of MP, Ds2 is that SCP2 is to the distance of MP; C is the rotation of boss outline line and biasing schematic diagram, and wherein SPL is boss contour line of sketch drawing, and BPL is boss biasing outline line.
Fig. 5 is that the present invention carries out discrete process flow diagram with dichotomy to boss end face outer annular edge.
Fig. 6 is the process flow diagram that the present invention obtains Generalized Convex chaptrel exterior feature.
Fig. 7 is the schematic diagram of Generalized Convex chaptrel exterior feature of the present invention.In figure, CSL is the intersection of casing ring groove side and sketch plane, and Cline is for connecting the straight line of different boss profiles, and COL is casing outer contour, and CIL is casing inner outline, and EBL is that Generalized Convex chaptrel is wide.
Fig. 8 is Generalized Convex chaptrel exterior feature of the present invention and the casing outline process flow diagram that take-off point decomposes by path.
Fig. 9 is the process flow diagram that minimum clamp horn cupping of the present invention is searched for casing blank outline counterclockwise.
Figure 10 is the schematic diagram that the present invention searches for casing blank outline.Wherein: Figure 10 a is for the Generalized Convex chaptrel after decomposing is wide and casing outline, and wherein CPT is contour path take-off point, and DPL is profile separatrix, and UEP is search starting point, i.e. casing outline upper extreme point, SD is the direction of take-off point place profile selection.The casing blank outline that Figure 10 b obtains for search, wherein CRL is the recessed connection of profile turning point round-corner transition line, CBO is the casing blank outline obtaining.Figure 10 c is fulcrum place counterclockwise minimum clamp horn cupping routing schematic diagram, wherein MO is current contour path, path 1,2,3 is three individual paths, and 3 ' is the tangential direction of circular arc path 3, and ∠ AOB, ∠ AOC, ∠ AOD are respectively the angle of three individual paths and current contour path.
Figure 11 is casing blank profile schematic diagram of the present invention.In figure, CSP is casing blank profile.
Figure 12 is the final effect figure of casing part milling blank of the present invention.
Embodiment
That the present invention is further illustrated in conjunction with the accompanying drawings and embodiments below.
An aero-engine casing milling blank automatic generation method based on feature, as shown in Figure 1, it comprises following steps to its flow process:
1, identify or read casing feature, obtain the face geological information of casing.
By identifying or read casing feature, obtain the face geological information of casing, as shown in Figure 2, in Fig. 2, A is that ring groove end face, B are ring groove side, and C is that ring groove base angle face, D are ring groove bottom surface, and E is casing end face, and F is casing inside surface; CF is boss base angle face, and SF is boss side surfaces, and TF is boss end face.The specific definition of aero-engine casing feature and recognition methods can be 201410188103.5 referring to application number, and denomination of invention is the Chinese patent of " aero-engine casing characteristic recognition method ".
2, extract casing axis, create sketch plane, extract casing outline line.
Extract the axis of rotation of arbitrary casing ring groove bottom surface, as the axis of casing, as shown in CA in Fig. 3.Cross and a bit create a plane on casing axis and casing ring groove bottom surface, as sketch plane, as shown in SP in Fig. 3.Sketch plane and casing inside surface intersect, and obtain casing inner outline, and as shown in CIL in Fig. 3, intersect sketch plane and casing end face, casing ring groove end face, side, base angle face, bottom surface, obtains casing outer contour, as shown in COL in Fig. 3.
3, the gyroscope wheel profile that extracts boss, rotates to sketch plane by boss gyroscope wheel profile, obtains contour line of sketch drawing, and contour line of sketch drawing is setovered by technological requirement.
1) extract the direction line of end face and side.With boss end face central point (in Fig. 4 a shown in MP) and casing axis, make planar I P, intersect IP and boss end face and side, obtain end face direction line and side surface direction line, as shown in TL, SL in Fig. 4 a, end face and side surface direction line represent the direction of boss end face and the relative casing in side.
2) with dichotomy with certain precision e(e=0.05-0.10mm) boss end face outer annular edge is carried out discrete, obtain the unique point of boss end face outer annular edge.Process flow diagram as shown in Figure 5, obtain all limits of end face outer shroud, deposit limit list EdgeList in, deposit the end points on all limits in discrete point list PointList, every limit in opposite side list EdgeList, if end-point distances is greater than discrete precision e, extract the mid point on limit, deposit in PointList, then this edge is punished into two sections of Edge1, Edge2 from mid point and deposit EdgeList list in, to work as front and delete from EdgeList, next limit in EdgeList is made as and works as front; If when the distance of front two-end-point is less than discrete precision e, directly forward next limit to, so circulation, until all limits end-point distances is all less than discrete precision e in EdgeList, point in PointList is the unique point of boss end face outer annular edge, as shown in FP in Fig. 4 a.Discrete precision e is less, and the number that obtains discrete point is more, discrete meticulousr, and the value of e can be set by technologist by interactive interface.
3) boss end face outer annular edge unique point is rotated to planar I P, as shown in Figure 4 b, find the point of end face direction line TL vertical range maximum as boss end face profile reference mark, as shown in TCP in Fig. 4 b; Find end face central point MP along end face direction line TL apart from maximum point, as boss side surfaces profile reference mark, as shown in SCP1, SCP2 in Fig. 4 b, SCP1, the SCP2 distance to end face central point along end face direction line is respectively Ds1, Ds2.
4) take end face profile reference mark TCP is starting point, and the end face direction line TL of take is direction, and it is end face largest contours line as straight line that Ds1, Ds2 extend to both sides for distance, as shown in TML in Fig. 4 a; The two-end-point of TML of take is starting point, and side surface direction line SL is direction, makes two straight lines crossing with casing ring groove bottom surface, obtains side largest contours line, as shown in SML in Fig. 4 a.The combination of boss end face and side largest contours line is boss gyroscope wheel profile.
5) end face largest contours line and side largest contours line are rotated to sketch plane, obtain boss contour line of sketch drawing, as shown in SPL in Fig. 4 c.
6) by boss contour line of sketch drawing SPL, by the required margin value of milling of interactive interface user input, equidistantly setover, obtain boss biasing outline line, as shown in BPL in Fig. 4 c, the boss outline line of setovering is deposited in list LayerEdge.
4, remove the boss outline line overlapping in sketch plane, by the too small outline line merging of distance between layers, obtain Generalized Convex chaptrel profile.
Owing to often containing the identical boss of a plurality of geometric configuratioies in one deck boss, the biasing outline line that has many coincidences in sketch plane, this step is removed the line of repetition by the end points coordinate of comparative silhouette line, simultaneously by the too small outline line merging of distance between layers, obtain Generalized Convex chaptrel profile, process flow diagram as shown in Figure 6.The intersection (as shown in CSL in Fig. 7) of casing ring groove side and sketch plane is added in LayerEdge, in order to judge the distance of boss biasing profile and casing ring groove side.Limit in LayerEdge is compared between two, if two limit end points overlap between two, latter one of two limits is deleted from LayerEdge; If two limit end points does not overlap, and end-point distances is less than the requirement of the turning cutting tool width of interactive interface user input, makes straight line CLine two end points are connected, and as shown in Cline in Fig. 7, Cline stores in LayerEdge.The combination on the limit in the LayerEdge finally obtaining is Generalized Convex chaptrel profile, as shown in EBL in Fig. 7 (part outside casing internal and external contour line CIL, COL).
5, Generalized Convex chaptrel profile and casing outer contour are decomposed with profile take-off point, obtain decomposing outline line.
Casing outer contour COL deposits in LayerEdge, and the limit in LayerEdge is decomposed, and process flow diagram as shown in Figure 8.Friendship is asked in other limits in every limit in LayerEdge and LayerEdge, if handing over element is that point is stored in CutPoint list, if friendship element is line segment, get the end points of handing over element, store in CutPoint list, point in CutPoint is profile take-off point, as shown in CPT in Figure 10 a; When front and every other limit, ask after friendship, if element number is not 0 in CutPoint, with the point in CutPoint, cuts apart and work as front, the multistage limit obtaining is stored in CutEdge; After in LayerEdge, has decomposed on all limits, the limit in CutEdge is decomposition outline line, as shown in DPL in Figure 10 a.
6, along searching for counterclockwise casing blank outline, between the casing blank outline limit of recessed connection, by turning process requirement, round-corner transition is set, obtains casing blank outline simultaneously; In casing blank outline and casing, profile merges, and obtains casing blank sketch profile.
Along the process flow diagram of counterclockwise search casing blank outline as shown in Figure 9:
1) take the upper extreme point (as shown in UEP in Figure 10 a) of casing outline is search starting point, traversal CutEdge list, finds the limit being connected with starting point to be set to, as front Pedge, Pedge be deleted from CutEdge list, traversal CutEdge list, finds the limit being connected with Pedge.
2) by minimum clamp horn cupping, select multiple-limb path.The system of selection in minimum clamp horn cupping multiple-limb path is as shown in Figure 10 c, MO is the current contour path of determining, along MO direction (advancing counterclockwise), at O point, run into 3 individual paths, path 1, path 2, path 3, select the contour path that wherein a paths is searched for as a new round; Three paths replace with tangent line 3 ' with the direction that the counterclockwise angle of working as front profile MO is respectively ∠ AOB, ∠ AOC, ∠ AOD(circular arc path 3); ∠ AOB is minimum, and selecting respective path 1 is that new contour path continues search.Casing outline in the routing of take-off point as shown in direction SD in Figure 10 a.By described routing resource, from the limit being connected with Pedge, find out the limit Medge with the counterclockwise angle minimum of Pedge, the limit being connected with Pedge is removed from CutEdge list.
3) if the counterclockwise angle of Pedge and Medge is less than 180 degree, it between Pedge and Medge, is recessed connection, requirement by the turning cutting tool fillet of interactive interface user input generates round-corner transition line Corner between both sides, as shown in CRL in Figure 10 b, deposit Corner and Pedge in Profile list; If Pedge and Medge are counterclockwise, angle is greater than 180 degree, directly Pedge is deposited in to Profile list.
4) Medge is made as to new as front profile Pedge, judge whether Pedge is connected with terminating point (lower extreme point of casing outline), if be connected, deposits Pedge in Profile list, search for end; If be not connected, return to step 2) continue search, until search finishes.The combination on the limit in the Profile list obtaining is casing blank outline, as shown in CBO in Figure 10 b.
5) profile in casing blank outline and casing is merged, obtain closed outline, be casing blank sketch profile, as shown in CSP in Figure 11.
7, with casing sketch profile, generate solid of revolution, obtain casing milling blank.
The casing axis CA(of take is shown in Fig. 3) be turning axle, with casing blank sketch profile (Figure 11), generate solid of revolution, obtain aero-engine casing part milling blank, final effect is as shown in figure 12.
The part that the present invention does not relate to all prior art that maybe can adopt same as the prior art is realized.
Claims (5)
1. the method that aero-engine casing part milling blank generates automatically, is characterized in that it comprises the following steps:
Step 1, identifies or reads casing feature, obtains the face geological information of casing;
Step 2, creates casing axis of rotation and sketch plane, extracts casing outline line;
Step 3, extracts boss gyroscope wheel profile, is rotated to sketch plane, and setovers by the required surplus of milling;
Step 4, according to turning cutting tool width, the distance between merging adjacent lands profile is less than the boss profile of cutter width, obtains Generalized Convex chaptrel wide;
Step 5, according to casing outline line and Generalized Convex chaptrel profile, search casing blank outline, and press turning cutting tool fillet information, and in the turning point of the recessed connection of profile, round-corner transition is set, obtain casing blank sketch profile;
Step 6, generates solid of revolution with casing blank sketch profile, obtains casing milling blank.
2. method according to claim 1, it is characterized in that described establishment casing axis of rotation and sketch plane, extracting casing outline line refers to: the axis of rotation that extracts a casing ring groove bottom surface, as casing axis, a bit to create plane on casing axis and this ring groove bottom surface, as the sketch plane of casing blank, sketch plane and casing face are asked to hand over and are obtained casing outline line.
3. method according to claim 1, is characterized in that the method for described extraction boss gyroscope wheel profile comprises the following steps:
1) extract the direction line of end face and side; With boss end face central point and casing axis, make plane, as boss, hand over plane, boss hands over plane and boss end face and side to intersect, and intersection is respectively end face direction line and side surface direction line;
2) extract boss end face and side profile reference mark; With dichotomy, to boss end face outer annular edge, carry out discrete, obtain the unique point of boss end face outer annular edge, boss end face outer annular edge unique point is rotated to boss and hand over plane, find the point of end face direction line vertical range maximum as end face profile reference mark, find end face central point along the point of end face direction linear distance maximum, as boss side surfaces profile reference mark;
3) take end face profile reference mark is starting point, and the end face direction line of take is direction, and the distance of side profile reference mark to end face central point along end face direction line is that length extends to both sides is end face largest contours line as straight line; The two-end-point of end face largest contours line of take is starting point, and side surface direction line is direction, makes two straight lines crossing with casing ring groove bottom surface, and two straight lines are side largest contours line, and the combination of end face and side largest contours line is boss gyroscope wheel profile.
4. method according to claim 1, the definite method that it is characterized in that described Generalized Convex chaptrel exterior feature is to adopt between two the relatively end points coordinate of sketch plane convex platform profile top line and side line, if two line endpoints overlap between two, deletes a coincidence line; If two line endpoints does not overlap, and certain two end-point distances is less than the technological requirement of turning cutting tool width, as straight line, join two endpoints, the straight line of doing as the part of profile, add in boss outline line; Remove coincidence line, add the boss outline line combination connecting after straight line, be Generalized Convex chaptrel wide.
5. method according to claim 1, is characterized in that the searching method of described casing blank outline comprises the following steps:
1) Generalized Convex chaptrel profile and casing outline line are decomposed with profile take-off point, obtain decomposing outline line;
2) to decomposing outline line, search in the counterclockwise direction, the silhouette edge being connected with casing outline upper extreme point of take is an initial line, be made as current silhouette edge, find the limit being connected with the counterclockwise working direction end points of current silhouette edge, obtain the counterclockwise angle of itself and current silhouette edge, the limit of angle minimum is outline limit, is made as the front of working as of next round search; If minimum angle is less than 180 degree,, between two outline limits, be recessed connection, between both sides, by turning cutting tool fillet information, round-corner transition is set, fillet line is as the part storage of outline, so circulation, until when front is connected with casing outline lower extreme point, search finishes, and obtains casing blank outline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410381573.3A CN104199383B (en) | 2014-08-05 | 2014-08-05 | Aviation engine case part milling blank automatic generation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410381573.3A CN104199383B (en) | 2014-08-05 | 2014-08-05 | Aviation engine case part milling blank automatic generation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104199383A true CN104199383A (en) | 2014-12-10 |
| CN104199383B CN104199383B (en) | 2017-01-11 |
Family
ID=52084684
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410381573.3A Active CN104199383B (en) | 2014-08-05 | 2014-08-05 | Aviation engine case part milling blank automatic generation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104199383B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110253060A (en) * | 2019-07-23 | 2019-09-20 | 湖南南方通用航空发动机有限公司 | A kind of processing method of inclined-plane boss |
| CN111443660A (en) * | 2020-04-23 | 2020-07-24 | 智腾机械设备（上海）有限公司 | Impeller turning model generation method and computer program |
| CN112355580A (en) * | 2020-10-29 | 2021-02-12 | 中国航发南方工业有限公司 | Burr removing process for high-temperature alloy case |
| CN112817271A (en) * | 2020-12-29 | 2021-05-18 | 苏州千机智能技术有限公司 | Method for optimizing machining allowance of casting case blank based on-machine measurement |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3213740A1 (en) * | 1982-04-14 | 1983-12-15 | Oerlikon-Boehringer GmbH, 7320 Göppingen | Whirl device |
| CN101767218B (en) * | 2008-12-30 | 2012-05-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Five-axis plunge milling method of aeroengine crankcase |
| CN102794610A (en) * | 2012-08-24 | 2012-11-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing thin wall welder cases of revolving body structures |
| CN102999011A (en) * | 2012-10-16 | 2013-03-27 | 沈阳黎明航空发动机(集团)有限责任公司 | High-temperature alloy thin-wall case numerical-control lathing method |
-
2014
- 2014-08-05 CN CN201410381573.3A patent/CN104199383B/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110253060A (en) * | 2019-07-23 | 2019-09-20 | 湖南南方通用航空发动机有限公司 | A kind of processing method of inclined-plane boss |
| CN111443660A (en) * | 2020-04-23 | 2020-07-24 | 智腾机械设备（上海）有限公司 | Impeller turning model generation method and computer program |
| CN112355580A (en) * | 2020-10-29 | 2021-02-12 | 中国航发南方工业有限公司 | Burr removing process for high-temperature alloy case |
| CN112355580B (en) * | 2020-10-29 | 2021-11-02 | 中国航发南方工业有限公司 | Burr removing process for high-temperature alloy case |
| CN112817271A (en) * | 2020-12-29 | 2021-05-18 | 苏州千机智能技术有限公司 | Method for optimizing machining allowance of casting case blank based on-machine measurement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104199383B (en) | 2017-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104375464B (en) | Aircraft skin milling efficient machining path automatic generating method | |
| CN101763069B (en) | Identification method of machining characteristics of complex parts of airplane | |
| Dwijayanti et al. | Basic study on process planning for turning-milling center based on machining feature recognition | |
| CN104199383B (en) | Aviation engine case part milling blank automatic generation method | |
| CN103336485B (en) | Rapid generating method of milling path of web of airplane structural member | |
| CN105354353A (en) | MBD model based processing feature identification and modeling method | |
| CN104360634A (en) | Skin mirror image milling numerical control program fast generating method based on features | |
| CN103365243B (en) | Method for rapidly generating corner side milling process path | |
| CN102289537A (en) | Method for identifying characteristics of complex structure in multi-body mode | |
| CN103926879B (en) | Aero-engine casing characteristic recognition method | |
| CN102436217B (en) | Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure | |
| CN104090528A (en) | Method suitable for cycloid high-speed milling machining path | |
| CN105880953A (en) | Method for processing aviation blade | |
| WO2022179097A1 (en) | Method and system for automatically constructing editable model of isogeometric topology optimization result | |
| CN104570948A (en) | Hole feature machining method for spaceflight sheet part | |
| Liu et al. | Extracting the turning volume and features for a mill/turn part with multiple extreme faces | |
| CN104462656B (en) | Aircraft skin part feature recognition methods | |
| CN104267669B (en) | The casing cannelure milling roughing track automatic generation method of feature based | |
| CN103577631A (en) | Three-dimensional process model establishment method for numerical control machining of circular-arc chamfered part | |
| CN103984289A (en) | Method for determining self-adaptive outline surrounding milling tool path according to peak characteristics of complex structural member | |
| CN109318051A (en) | A kind of curved surface part numerical control processing localization method | |
| CN108723725A (en) | A kind of processing method of aerial blade | |
| CN105894021B (en) | A kind of matching process of the identical machining feature based on process knowledge | |
| CN102930108B (en) | Plane structural part rib characteristic identification method | |
| CN103927426A (en) | Aero-engine blisk feature recognition method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |