CN106514129A - Numerical control programming nonuniform margin configuration method based on machining characteristic intermediate state rigidity - Google Patents

Numerical control programming nonuniform margin configuration method based on machining characteristic intermediate state rigidity Download PDF

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CN106514129A
CN106514129A CN201710000516.XA CN201710000516A CN106514129A CN 106514129 A CN106514129 A CN 106514129A CN 201710000516 A CN201710000516 A CN 201710000516A CN 106514129 A CN106514129 A CN 106514129A
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rigidity
surplus
machined surface
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CN106514129B (en
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刘长青
李迎光
郝小忠
李仲宇
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Nanjing University of Aeronautics and Astronautics
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Abstract

The invention discloses a nonuniform margin configuration method based on machining characteristic intermediate state rigidity. The method combines part geometric information with process information extracted from a process tree; based on the machining sequence of machining characteristics, an intermediate state of the machining characteristics is built, and a rigidity measurement index is proposed; the rigidity corresponding to a machined surface is measured by a ratio of a wall thickness corresponding to the machined surface to an area; and the rigidity measurement index is used as standard to distribute nonuniform margin values for finish machining to automatically generate machining drive geometry. The method realizes optimization of finishing margins of considering the machining characteristic intermediate state rigidity; and a nonuniform margin programming method is used for effectively improving overall part rigidity and guaranteeing the part machining quality.

Description

Based on the non-homogeneous surplus collocation method of the rigid numerical control programming of machining feature intermediateness
Technical field
The present invention relates to the surplus optimization method of a kind of method for fine finishing, especially a kind of polish, specifically one Plant based on the rigid non-homogeneous surplus implementation method of machining feature intermediateness.
Background technology
The size of aircraft structure is big, complex structure, and requirement on machining accuracy is high, and thin-wall part is a lot, to make machining deformation not Can be excessive, to often ensure that integral rigidity is required in process, traditional uniform surplus programming is not due to accounting for processing Sequentially, all of machined surface polish all distributes same surplus, but actually due to processing sequence problem, causes different adding The middle machining state of its adjacent machining feature of work face is different, therefore the wall thickness corresponding to machined surface is different, and evenly distributed Surplus then causes to make the allowance distribution of some machined surfaces unreasonable in process, so that part integral rigidity is reduced, Finally deform excessive, make part overall processing inefficiency.
Brought problem on deformation is configured for the uniform surplus of thin-wall part, it is considered to intermediateness based on machining feature and Its rigid non-homogeneous surplus configuration obtains the processing sequence based on machining feature by processing technique and machining feature, so as to root The intermediateness model based on machining feature is built according to processing sequence, and according to each machining feature intermediateness, is added with different The corresponding rigidity in work face, as weighing, is that different machined surfaces distribute different allowance for finish values so that remaining in process Amount grayscales uneven distribution, and the processing driving geometry of non-homogeneous surplus is automatically generated, so that the course of processing ensure that entirety just Property require, improve crudy.
The content of the invention
The purpose of the present invention is for conventional uniform surplus programmed method it cannot be guaranteed that one-piece parts rigid requirements, cause to add The excessive problem of work part deformation, invention is a kind of to be based on the rigid non-homogeneous surplus collocation method of machining feature intermediateness, leads to The processing sequence for crossing machining feature builds middle machining state model, it is considered to which machining feature intermediateness and its rigidity, are finishing The non-homogeneous surplus of work reasonable distribution, makes the course of processing ensure that integral rigidity is required, improves crudy.
The technical scheme is that：
It is a kind of to be based on the rigid non-homogeneous surplus collocation method of machining feature intermediateness, it is characterized in that according to machining feature Processing sequence, intermediateness model is built based on machining feature, it is considered to which the machining feature intermediateness of part and its rigidity are asked Topic, it is different from traditional uniform surplus configuration, it is the non-homogeneous surplus of polish reasonable distribution, and it is several to automatically generate processing driving What, realizes, based on the rigid non-homogeneous surplus configuration of machining feature intermediateness, making the course of processing ensure that integral rigidity will Ask, improve crudy.
Processing sequence refers to the processing sequence based on machining feature, by the technique information that extracts from processing technique tree The machining feature identifier of each process operation corresponds to the machining feature of part geometry, is then obtained by the order of process operation To the processing sequence of machining feature.
Based on the construction method of machining feature structure intermediateness model it is：Extract first from part end-state model Geological information, by the architectural feature and processing characteristic of analyzing part, is processed tagsort to part, secondly from processing work Extraction process information in skill tree, and according to corresponding to the machining feature identifier in process operation and geometric properties, finally according to Feature machining order is sequentially built to the intermediateness geometry of machining feature each time, and different processing sequence correspondences is different Middle machining state.
Machining feature intermediateness geometric representation is the machining cell that the model after roughing cuts machined feature：
In formula, PG represents current machining feature intermediateness geometry, and RG represents the geometry after roughing, FGiFor the of part The geometry of the corresponding finishing unit of i machining feature, k represent current machined number of features.
The rigidity of described machining feature intermediateness, it is contemplated that optimization is allowance for finish, for complex thin-wall is tied Component, due to the larger rigidity of wall thickness preferably, the less rigidity of wall thickness is poor, and the larger rigidity of machined surface area is poor, face The less rigidity of product preferably, therefore proposes rigid measurement index ε, corresponding with the machined surface under current machining feature intermediateness Wall thickness weighs the rigidity of a certain machined surface with the ratio of area.The method and step for wherein calculating wall thickness corresponding to machined surface is as follows：
Step one：On current machining feature intermediateness model, geometric center P of the machined surface is calculated1, cross the point edge Normal direction makees straight line L1。
Step 2：Write down L1From P1Start along first intersecting face F of normal direction opposite direction1And L1With F1Intersecting point P2。
Step 3：Calculate point P1With point P2Air line distance, be machined surface correspondence wall thickness value.
After obtaining wall thickness value δ of the machined surface, machined surface area A is calculated, using its ratio as inflexible target, is referred to Mark
Described is according to the optimization face correspondence essence i.e. with machined surface wall thickness value for the non-homogeneous surplus of polish reasonable distribution Allowance, surplus optimized calculation method step are as follows：
Step one：According to part overall dimensions and final geometric model, allowance span, i.e. allowance are set Maximum Zmax=4.0mm and minima Zmin=0.5mm.
Step 2：For all faces in a machining feature calculate its wall thickness respectively, each face is then obtained corresponding Inflexible target εi, and calculate the meansigma methodss of all machined surface inflexible targets in a machining feature：
ε in formulaavgIt is the mean rigidity index of all machined surfaces of machining feature, n is all processing of machining feature The number in face.
Step 3：The inflexible target of each machined surface is contrasted, the corresponding reduction surplus bigger than mean rigidity index, than average The little corresponding increase surplus of inflexible target：
Z in formulaiRepresent the margin value after optimization, ZpiRepresent the margin value before optimization, εiRepresent the corresponding rigidity in each face Measurement index value, εmaxThe maximum of all machined surface inflexible targets of one machining feature of expression, εminRepresent a machining feature The minima of all machined surface inflexible targets.
Step 4：If the surplus after optimization is more than presetting maximum margin value Zi＞ Zmax, then margin value take maximum surplus Value, i.e. Zi=Zmax；If the surplus after optimization is less than presetting minimum margin value Zi＞ Zmin, then margin value take minimum margin value, That is Zi=Zmin。
Described automatically generates the surplus that processing drives geometry, i.e. each machined surface to obtain according to its rigid measurement index Processing is driven geometry accordingly to bias by value, is automatically generated new processing and is driven geometry.
For the rigidity of machining feature intermediateness, it is contemplated that optimization is allowance for finish, for complex thin-wall structure Part, due to the larger rigidity of wall thickness preferably, the less rigidity of wall thickness is poor, and the larger rigidity of machined surface area is poor, area Less rigidity preferably, therefore proposes rigid measurement index, with the corresponding wall of the machined surface under current machining feature intermediateness The thick rigidity that a certain machined surface is weighed with the ratio of area.
For the non-homogeneous surplus of polish reasonable distribution i.e. with the inflexible target of machined surface place feature be according to optimize the face Correspondence allowance for finish, each time optimization of surplus should be carried out in a machining feature, first be calculated in a machining feature The meansigma methodss of all machined surface correspondence inflexible targets, contrast the rigid measurement index of each machined surface in a machining feature, than The big machined surface of mean rigidity index accordingly reduces surplus, and the machined surface less than mean rigidity index accordingly increases surplus, arranges The feasible value scope of surplus, i.e. surplus maximum and minima threshold value, if the surplus after optimization is more than presetting maximum surplus Value, then margin value takes maximum margin value；If the surplus after optimization is less than presetting minimum margin value, margin value is taken more than minimum Value.After obtaining the margin value of each machined surface, geometry biasing is driven for processing using the value, automatically generate new processing and drive Geometry.
Beneficial effects of the present invention：
Present invention achieves consider the optimization of the rigid allowance for finish of machining feature intermediateness, using non-homogeneous surplus Distribution can effectively improve part integral rigidity, it is ensured that the crudy and precision of part.
Description of the drawings
Fig. 1 is based on the rigid non-homogeneous surplus collocation method flow chart of machining feature intermediateness for the present invention.
Fig. 2 is the example components schematic diagram of the present invention.
Processing sequence schematic diagrams of the Fig. 3 for example components machining feature.
Fig. 4 is example components calculated wall thickness value schematic diagram.
Fig. 5 is the machining feature schematic diagram that example components distribute non-homogeneous surplus.
Fig. 6 automatically generates processing for example components and drives geometric representation.
Specific embodiment
The present invention is further illustrated with reference to the accompanying drawings and examples.
Using the cavity feature of the aircraft structure shown in Fig. 2 as example, technical scheme is carried out in detail with reference to accompanying drawing Describe in detail bright.
Fig. 1 is of the invention based on the rigid non-homogeneous surplus programmed method flow chart of machining feature intermediateness, and it leads To be distributed rationally two parts and be constituted by the establishment of machining feature intermediateness geometric model and the non-homogeneous surplus of polish.It is concrete to wrap Include following steps：
1st, feature identification is processed to part body, by the architectural feature and processing characteristic of analyzing part, part is entered Row machining feature is classified.
2nd, processing technique tree is selected, the process operation related to machining feature is obtained from tree, and according in process operation Machining feature identifier carry out corresponding with machining feature, obtain the corresponding process operation of different machining features, and according to processing Order of the operation on processing technique tree, obtains the processing sequence of machining feature, as shown in Figure 3.
3rd, the processing sequence according to machining feature, builds the middle machining state based on machining feature.Will be current undressed The all machined surfaces of feature build the corresponding middle machining state geometry of current machining feature plus allowance for finish, the like To the corresponding middle machining state geometry of each machining feature.
4th, for the middle machining state geometry of each machining feature, calculate the wall in each face in current machining feature Thick value.Computational methods are as follows：
Step one：On current machining feature intermediateness model, geometric center P of the machined surface is calculated1, cross the point edge Normal direction makees straight line L1。
Step 2：Write down L1From P1Start along first intersecting face F of normal direction opposite direction1And L1With F1Intersecting point P2。
Step 3：Calculate point P1With point P2Air line distance, be machined surface correspondence wall thickness value.As shown in figure 4, passing through Can be calculated P1P2Air line distance, i.e., the wall thickness value corresponding to the machined surface be 4mm.
For complex thin-wall structural member, due to the larger rigidity of wall thickness preferably, the less rigidity of wall thickness is poor, and machined surface The larger rigidity of area is poor, and the less rigidity of area is preferable, therefore should be with reference to 2 points, it is considered to process the rigidity of certain one side with this The corresponding wall thickness of machined surface is benchmark with the ratio of area.The area A of the machined surface is 5401.5mm2, can by calculating Obtain rigid measurement index ε=7.41 of the machined surface.
5th, for each machining feature, it is rigidly to distribute non-homogeneous surplus based on machining feature intermediateness, one need to be calculated The meansigma methodss of the rigid measurement index of all machined surfaces in individual machining feature, contrast the firm of interior each machined surface of a machining feature Property measurement index, the machined surface bigger than mean rigidity measurement index accordingly reduce surplus, it is less than mean rigidity measurement index plus Work face accordingly increases surplus.The feasible value scope of surplus, i.e. surplus maximum and minima threshold value are set, if the surplus after optimization More than presetting maximum margin value, then margin value takes maximum margin value；If the surplus after optimization is remaining less than presetting minimum Value, then margin value take minimum margin value.Surplus optimization calculation procedure is as follows：
Step one：According to part overall dimensions and final geometric model, allowance span, i.e. allowance are set Maximum Zmax=2.5mm and minima Zmin=0.3mm.
Step 2：For all faces in a machining feature calculate its wall thickness respectively, each face is then obtained corresponding Rigid measurement index εi, groove as shown in Figure 5 can be calculated under current machining feature intermediateness each by previous step and faces the wall and meditates Thick to be respectively 4mm, 3mm+1.2mm (face is undressed, add allowance for finish), 4mm, 3mm, the corresponding rigidity in each face weighs Figureofmerit is 7.41,8.53,7.41,9.95, and calculates the meansigma methodss of all machined surface rigidity measurement indexs in the machining feature：
Step 3：Contrast the rigid measurement index of each machined surface, more than the corresponding reduction bigger than mean rigidity measurement index Amount, the corresponding increase surplus less than mean rigidity measurement index, current margin value Z obtained from artistic treepi=1.2mm, because This is according to equation below：
The margin value calculated after the cavity feature each machined surface optimization is 1.63mm, 1.11mm, 1.63mm, 0.43mm.
6th, after obtaining the non-homogeneous margin value of each machined surface distribution, geometry biasing is driven for processing using the value, automatically Generate new processing and drive geometry, as shown in Figure 6.
Part that the present invention does not relate to is same as the prior art or can be realized using prior art.

Claims (5)

1. it is a kind of to be based on the rigid non-homogeneous surplus collocation method of machining feature intermediateness, it is characterized in that according to machining feature Processing sequence, builds intermediateness model based on machining feature, it is considered to the machining feature intermediateness of part and its stiff problem, It is different from traditional uniform surplus configuration, it is the non-homogeneous surplus of polish reasonable distribution, and automatically generates processing to drive geometry, it is real Now based on the rigid non-homogeneous surplus configuration of machining feature intermediateness, make the course of processing ensure that integral rigidity is required, carry High crudy.
2. method according to claim 1, it is characterised in that processing sequence refers to the processing sequence based on machining feature, leads to The machining feature identifier for crossing from processing technique tree each process operation in the technique information for extracting corresponds to part geometry Machining feature, then obtains the processing sequence of machining feature by the order of process operation.
3. method according to claim 1, it is characterised in that the structure side of intermediateness model is built based on machining feature Method is：Geological information is extracted from part end-state model first, it is by the architectural feature and processing characteristic of analyzing part, right Part is processed tagsort, secondly from extraction process information in processing technique tree and special according to the processing in process operation Levy corresponding to identifier and geometric properties, finally according to feature machining order to the intermediateness geometry of machining feature each time according to Sequence is built, the different middle machining state of different processing sequence correspondences.
4. method according to claim 1, it is characterised in that for the rigidity of machining feature intermediateness, it is contemplated that optimization Be allowance for finish, for complex thin-wall structural member, due to the larger rigidity of wall thickness preferably, the less rigidity of wall thickness is poor, And the larger rigidity of machined surface area is poor, the less rigidity of area preferably, therefore proposes rigid measurement index, currently to process Under feature intermediateness, the ratio of the corresponding wall thickness of the machined surface and area weighs the rigidity of a certain machined surface.
5. method according to claim 1, it is characterised in that be the non-homogeneous surplus of polish reasonable distribution i.e. with machined surface The inflexible target of place feature is that the optimization of surplus each time should be special in a processing according to the optimization face correspondence allowance for finish Carry out in levying, first calculate the meansigma methodss of all machined surface correspondence inflexible targets in a machining feature, contrast a processing special The rigid measurement index of each machined surface in levying, the machined surface bigger than mean rigidity index accordingly reduce surplus, compare mean rigidity The little machined surface of index accordingly increases surplus, arranges the feasible value scope of surplus, i.e. surplus maximum and minima threshold value, if excellent Surplus after change is more than presetting maximum margin value, then margin value takes maximum margin value；If the surplus after optimization is less than default Fixed minimum margin value, then margin value take minimum margin value；After obtaining the margin value of each machined surface, driven for processing using the value Dynamic geometry biasing, automatically generates new processing and drives geometry.
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CN109976261A (en) * 2019-04-24 2019-07-05 西北工业大学 The method for solving of surplus Optimized model towards processing positioning
CN110732681A (en) * 2019-11-19 2020-01-31 中国航发贵州黎阳航空动力有限公司 turning method for thin-wall weak-rigidity plate-welded part with ceramic coating
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CN109976261A (en) * 2019-04-24 2019-07-05 西北工业大学 The method for solving of surplus Optimized model towards processing positioning
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CN110732681B (en) * 2019-11-19 2021-06-29 中国航发贵州黎阳航空动力有限公司 Turning method for thin-wall weak-rigidity plate-welded part with ceramic coating
CN117092962A (en) * 2023-10-19 2023-11-21 常州市百宏智能科技有限公司 Numerical control machine tool machining control system

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