CN103699055A - Intelligent numerical control machining programming system and intelligent numerical control machining programming method for aircraft structural parts - Google Patents
Intelligent numerical control machining programming system and intelligent numerical control machining programming method for aircraft structural parts Download PDFInfo
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Abstract
The invention relates to an intelligent numerical control machining programming system and an intelligent numerical control machining programming method for aircraft structural parts. According to the system, an existing CAD/CAM (Computer-Aided Design/Computer-Aided Manufacturing) system is taken as a platform; the system comprises a model detection module, a process scheme automatic generation module, a process resource and knowledge base management model, an automatic programming subsystem module and a numerical control program intelligent optimization module. The system is established on the basis of a three-dimensional model, the numerical control machining programming specialization process of the aircraft structural parts is relatively systematically and accurately reflected and supported, the man-machine interaction operation required in the technological preparation and programming process can be greatly reduced, the problems of unstable program, long programming period and the like caused by interactive programming based on universal platform and artificial experience are effectively solved, the numerical control machining preparation and programming efficiency and quality can be obviously improved, and the specialization level and the intelligence level of the CAD/CAM system are promoted.
Description
Technical field
The present invention relates to a kind of aircraft structure intelligent numerical control machining prgraming system and method, be applied to the nc program establishment of aircraft large-scale integral structural member, improve robotization and the intelligent level of numerical control program establishment, to shorten Flight Structures NC Machining programming cycle and to improve the working (machining) efficiency of structural member.This technological invention belongs to airplane digital manufacturing technology field.
Background technology
The development of Technology of NC Programming has the history of five more than ten years, it is to come out and be born and develop rapidly with the first in the world platform three coordinate numerical control milling machine, has experienced by manual programming and has been developed to the process that numerical control language automated programming rises to the CNC automatic programming based on 3-D geometric model again.Make a general survey of its development, what promote these transition is the lively production practices requirements to NC Machining Program technology.At present, through the extensive research of domestic and international experts and scholars, NC Machining Program technology has obtained significant development, obtained great achievement, for further improving the automatization level of programming, at present, Technology of NC Programming has progressively entered the developing stage of intelligent numerical control programming, will form intelligent numerical control programming.
The fast development of the correlation techniques such as computing machine, programming and high-speed cutting processing and the development that widespread use has promoted aircraft structure manufacturing technology, in present generation aircraft structure, adopt more and more the one-piece parts forming via digital control processing to replace assembled subassembly, alleviated aircraft deadweight, shorten processing and the installation time of aircraft structure, and effectively improved the overall performance of aircaft configuration.But, integral structure component has complex structure, manufacturing accuracy and requires the features such as high and difficulty of processing is large, current in general CAM platform the technological preparation based on 3-D geometric model and mutual numerical control programming mode become one of the bottleneck of aircraft structure manufacturing cycle and the quality factor that affects.Trace sth. to its source, mainly contain following two aspects: the one, the intelligent degree of technological preparation and programming technique is low, is too dependent on the experimental knowledge that journey is compiled personnel's long-term accumulation under specific production environment, programmes lack of standardization and program quality is unstable; The 2nd, programming process automaticity is low, need to a large amount of process operation parameters be set by man-machine interaction mode, and repeated workload is large, and programming cycle is long.
The experience that this simple dependence journey is compiled personnel adopt interactive mode specify machining area and arrange machined parameters can not meet far away production practices to nc program establishment fast, demand easily.Therefore the intelligent numerical control programming technique that is intended to improve robotization and intelligent degree causes extensive concern and the great attention of academia and industry member.Method is that the intellectual technologies such as artificial intelligence, neural network and expert system are incorporated in the existing NC APT based on 3-D geometric model, make it have certain identification, analysis, judgement and decision-making capability, can automatically identify feature model according to the geometric model of part and blank, and formulate accordingly rational processing process, determine and work option is set, at utmost simplifying the operation course.Target is that people is freed from heavy repetitive operation, by system synthesis, considered the various factorss such as blank, part, cutter and lathe, automatically complete the nc program establishment of whole process from blank to product, thereby greatly improve efficiency and the quality of program composition.
Yet robotization and Intelligent CNC programming, still in research and exploratory stage, need the problem of solution also a lot, await further further investigation.Academia's study hotspot mainly comprises the aspects such as machining features recognition, characteristic optimization sequence, cutter are chosen, machined parameters optimization is chosen, cutting tool path calculates, 5 axle processing cutter axis orientation control and simulation checkings.Numerous researchists have obtained certain achievement, R.B.Karadkar etc. have studied and have developed the 2.5 axle part process planning and design systems that comprise based on feature in 1996, realize the automatic planning of 2.5 axle part processes, for follow-up CAM automatic programming provides basis.Huikang K.Miao etc. carries out secondary development at IDEAS platform and has realized the process planning based on machining feature, effectively realized the integrated of CAD/CAPP/CAM, but this system is also only applicable to 2.5 axle parts.For improving the automaticity of programing system, Millan k.Yeung is incorporated into artificial intelligence in programing system, by the automatic identification of machining feature and the optimization of cutter, choose, develop Intelligent art planning system, and the flexibility of system, simplified the expansion be convenient to new knowledge, new technology.In addition, for the progressively increase solving due to modern mechanical product complexity causes the problems such as process programming process is loaded down with trivial details, complicated, the fundamental element using the machining feature based on knowledge as technological process such as UlrichBerger, take that to reduce the process time be target, the mode of employing figure is described and optimizing process, and realizes on CATIA.GeCAM company also introduces intellectual technology following closely successively in NC Programming System separately, release has the CAM system of part intelligence, as FeatureCAM system and ESPRIT system, these two systems are the global function software based on feature and knowledge, use automatic Feature Recognition all, the use of feature and Knowledge Base Techniques, make part machining prgraming more convenient, simpler, greatly shortened the machining prgraming time.But this type systematic also needs more man-machine interactively operation at present, and inapplicable complex parts, from practical application, still has a segment distance.
Summary of the invention
In order to solve the technical matters of above-mentioned existence, the invention provides a kind of aircraft structure intelligent numerical control machining prgraming system (being called for short INCPro), according to process program, drive the intelligence programming of aircraft structure, intellectuality, standardization and the self-optimizing of programming have been realized, the program height of establishment meets technological requirement, and can embody programmer's thought.
The object of the invention is to be achieved through the following technical solutions: a kind of aircraft structure intelligent numerical control machining prgraming system, this system be take CAD/CAM system as platform, comprise process resource and knowledge base management module and automated programming subsystem, it is characterized in that: system also comprises model detection module, process program automatically-generating module and numerical control program intelligent optimization module;
Described CAD/CAM system platform, supports for INCPro provides platform, and first system sets up 3 d part model and the blank model of aircraft structure on this platform, for system provides basis input data; In addition, the machining cell constructed according to automated programming module, applies " digital control processing " Module Generation process operation of this platform and sets and carry out the calculating of cutter rail, machining simulation and rearmounted processing, realizes the automatic generation of digital control processing file;
Described process resource and knowledge base management module, for system provides shoring of foundation data, supports the interface that data and other modules are carried out exchanges data, and the management function of supporting database; Wherein, supporting database comprises process knowledge storehouse, lathe parameter storehouse, workpiece material storehouse, cutter parameters and material depot, Numerical Control Cutting storehouse, process program template base and other resources banks; Secondly, by setting up the data-interface of other modules and supporting database, realize data transmission between disparate modules, call and manage, complete being connected of supporting database and whole INCPro, realize the sharing and management of data resource; In addition, the management of supporting database comprises inquiry, deletion, insertion, modification, preservation and the reasoning of various support data, facilitates checking and upgrading of various support data;
Described model detection module, is responsible for part model to carry out robotization detection, specifically comprises: (1) part model design mistake: in the part model of design, comprised the non-existent structure of actual product, comprised residual body, narrow slit; (2) markup information is imperfect: according to MBD model definition standard, whether geometry and the non-geological information automatically identified in part model be complete; (3) processability of product structure is not enough: according to existing process resource (comprising cutter, frock, lathe etc.) and process, automatically detect the bad even completely not machinable structure of the manufacturability existing in part model; Realization is to part model correctness, technological automatic examination; According to examination result, the method for type, position and the modification of prompting problem, and automatically revise for some frequent faults, with the method, guarantee the correctness of part model;
Described process program automatically-generating module, for realizing the numerical control program of technological process driving, automatically generate macroscopical process program is provided, wherein process program adopts multiway tree to represent, comprise part, lathe, station, operation, work step, program, cutter, eight grades of nodes of feature, can describe macroscopical machining process; By process program automatically-generating module, set up process program template base, existing aircraft structure is classified and summed up the general technology flow process of structural member, for every quasi-representative structural member, set up processing scheme template, comprised lathe, station, operation, work step; Then, the manufacture resource choosing method selecting machine tool based on machining feature, cutter, frock resource, and merge mutually with processing scheme template, automatically generate the numerical control processing technology scheme of aircraft structure;
Described automated programming subsystem, it is the nucleus module of aircraft structure intelligence programming, mainly comprise: (1) automatic feature recognition: according to the 3-D geometric model of aircraft structure and blank model, adopt layered characteristic recognition methods to carry out the feature identification of part, obtain all machining feature of part, and with tree structure form storage feature recognition result; (2) process program intelligent inference: according to conditions such as part type, process side number, blank type and feature recognition results, support data in combined process resource and base module, carry out intelligent knowledge reasoning and from process program template base, automatically recommend the processing scheme template of part; (3) cutter is chosen automatically: geometric parameter and process segment based on feature are chosen process tool, and for example the roughing tool based on ablation volume ratio is chosen; (4) machining cell intelligence structure and sequence: cutter is fused to and in processing scheme template, forms complete process program, the technological process of being described by process program again drives machining cell automatically to construct, according to cutter can working ability, residual region based in process extracts often to be chosen the machinable region of cutter, intelligent inference optimum process operation and calculates the required geometric parameter of process operation, form often the machining cell sequence of cutter, by process program and machining cell, merged mutually the digital control processing unit sequence of complete; (5) process operation generates automatically: digital control processing unit sequence automatic mapping is set to the process operation in " digital control processing " module of CAD/CAM system, and the geometric parameter of each process operation of Lookup protocol, policing parameter, cutter parameters, speed parameter and the connection of advance and retreat cutter, and carry out the calculating of cutter rail and machining simulation;
Described numerical control program intelligent optimization module is responsible for the processing sequence of the resource of choosing in intelligence programming process, arrangement etc. to be optimized, be specially: (1) cutter is chosen optimization: adopt the method for selecting roughing tool based on ablation volume ratio, according to given tool magazine list, from tool magazine, according to diameter, calculate in aircraft structure every the machinable all machining area volumes of cutter successively, when there being a region to be processed volume that the machinable volume of cutter is greater than to 80%, think that this cutter is suitable roughing tool; In addition, take the shortest process time as optimization aim, corner processing and sidewall finishing tool are optimized, sharp processing in qualified corner machining feature and sidewall is chosen to multiple cutter scheme processes, by calculating the cutter of determining profile machining feature in corner feature and sidewall process time of different schemes bottom tool, realize the optimization of corner feature and sidewall finishing tool and choose; (2) roughing hierarchy optimization: for the structures of sinking in aircraft structure more, take that to realize the layering roughing time minimum be prerequisite, the bottom web that guarantees each vallecular cavity feature after roughing can adopt finishing web cutter one cutter to complete under accurately machined prerequisite, adopt genetic algorithm to carry out intelligent optimization to minute aspect, realize the minimum of roughing minute aspect, to improve roughing efficiency; (3) machining cell path optimization: minute Macro and two aspect of cutter layer are optimized; At Macro, the technological process of describing according to process program, carries out auto-sequencing by all digital control processing unit according to macroscopical technological process (comprising lathe, station, operation, work step and cutter); At cutter layer, to every, the machining cell of cutter association is carried out to level Four grouping, first the machining cell of cutter association is divided into a plurality of secondary unit groups according to the difference of work step type and (comprises two types: add work order tuple and target work sheet tuple, wherein add work order tuple and under current work step work step before added to work order metaset, target machining cell is that current work step is specified the unit collection that will process), and will add work order tuple and process prior to target work sheet tuple; Secondly, by adding work order tuple, according to the type of machining cell place work step, it is divided into groups again, form three grades of unit groups, and according to technological process order, these three grades of unit groups are sorted successively; Have again, three grades of unit groups are carried out to top-down whole layer sorting, form level Four unit group; Finally, the machining path of take is the shortest is optimization aim, to the machining cell in level Four unit group, adopts simulated annealing to carry out path optimization's sequence, realizes the optimization of machining path in level Four unit group.Adopt and can realize in this way the machining cell Optimal scheduling that process program drives, considered the sequence of geometry level and process level, can significantly improve sequence efficiency and quality.
An implementation method for aforementioned aircraft structure intelligent numerical control machining prgraming system, concrete steps are as follows:
Step 1): enter " digital control processing " module of CAD/CAM platform, and enter " aircraft structure intelligent numerical control machining prgraming system ", be written into aircraft structure three-dimensional model and blank model;
Step 2): carry out the setting of part essential information, specifically have: the type of (1) part: wallboard, frame, beam, rib, joint etc.; (2) process side number: comprise one side, two-sided and multiaspect; (3) blank type: comprise sheet material, section bar, forging and foundry goods;
Step 3): enter model detection module, in conjunction with part model manufacturability, part model is carried out to quality testing, and revise accordingly not meeting the local error structure of actual process requirement, make part model meet processing technology requirement, to guarantee to input the correctness of part model;
Step 4): enter automated programming module, first need according to step 2) in the part type set for each process side, set corresponding machining coordinate with process side information and be, then under each machining coordinate system, all manifold of part are carried out to face type identification, identify based on this pore structures such as countersunk, counter sink, vertebral foramen, cylinder straight hole, and delete transverse holes and oblique hole, be convenient to the smooth realization of feature identification; Under each machining coordinate system, the slot descriptor characteristic recognition method of employing based on layering processing thought carries out machining features recognition to part, creating layering aspect and material object parts asks and hands over and obtain out intersection ring and the inner and outer ring relation thereof of every layer, by this relation, determined the machining area of every layer, then extract the part manifold that in intersection ring, sideline relies on, again the face that in intersection ring, all sidelines rely on is combined, and then form slot descriptor feature, then construct aircraft structure slot descriptor feature structure tree according to the incidence relation between longitudinal surface;
Step 5): after the feature identification in step 4), man-machine interactively selects whether to be written into existing similar part process program, if select "Yes", the process program of intelligent search similar part from processing scheme storehouse, then by manually choosing by mutual mode optimization; Otherwise enter process program automatically-generating module, according to technique experimental knowledge and part type, carry out knowledge reasoning, determine the process program template of current part, comprise lathe, station, operation, work step etc., based on machining feature, automatically choose cutter again, determine and in each process segment process, process the needed cutter parameters of different characteristic and cutting parameter, and processing scheme template and cutter are chosen to result merge, generate complete process program; Build by the way after process program, form the tree structure that comprises seven grades of nodes, wherein seven grades of nodes are specially: part node, lathe node, process side node, procedure-node, work step node, program node and cutter node; Manually can interactive modifying and carry out validity check, finally confirm to preserve; If part is processing first, its process program is added to automatic powder adding in processing scheme storehouse, for calling of next similar part, and the unitarity of assured plan and standardization;
Step 6): again enter automated programming module, first the process program generating from step 5), extract the cutter that each work step is used, and the cutter choosing method based on how much, cutter and machining feature are set up to matching relationship, guarantee that machining feature has suitable cutter to process in the different process segments; Then, macroscopical technological process of describing according to process program and cutter can working ability, and on the basis of calculating in real time in residual region, solve cutter can machining area, process operation is chosen in optimization and calculating processing operates the required information such as geometric parameter automatically to build machining cell, completes the structure of Flight Structures NC Machining machining cell sequence;
Step 7): in step 6) digital control processing cell formation process, need to enter digital control processing intelligent optimization module, carry out the Optimization Works such as roughing hierarchy optimization, machining path optimization, realize the optimization of numerical control program;
Step 8): last, in CAM system, automatically generate the process operation tree corresponding with Flight Structures NC Machining machining cell sequence, wherein process operation is to use one cutter, one group of machined parameters and a job sequence that parametrization cutter rail generates, by the policing parameter of each machining cell, machined parameters, geometric parameter, cutter parameters and processing macro parameter are set to respectively in corresponding process operation, can complete the automatic generation of process operation, and then all process operations are carried out to the calculating of cutter rail and machining simulation, complete the intelligence establishment of Flight Structures NC Machining program, finally, by front and rear handling procedure, numerical control machining knife rail is converted to the NC code of corresponding digital control system.
Beneficial effect of the present invention: for current interactive numerical control programming and fast programming, the present invention has developed emphatically model detection module, process program automatically-generating module and numerical control program intelligent optimization module, first further guarantee to be input to part model correctness in programing system and good manufacturability, can effectively reduce the problems such as the calculating causing due to model quality existing problems producing in automated programming process is unstable, result is inaccurate; Secondly, employing Multiway Tree Structure is unitized, abstract represents process program, the process program of different aircraft structures is made to template, can realize templating, the standardization of technique, in addition with all kinds of manufacture Resource Fusions based on Feature Selection after, can automatically generate the process program of part, the process program rationality that this mode generates is strong, be identical with actual process process, and the efficiency that process program generates is automatically high; Have again, the exploitation of intelligent optimization module, is optimized a plurality of critical stages in numerical control programming process, can realize that cutter optimization is chosen, machining path optimization etc., can significantly improve the quality of nc program, significantly improve the working (machining) efficiency of batch production aircraft structure.
Accompanying drawing explanation
Fig. 1 is the mode chart of aircraft structure intelligent numerical control machining prgraming system of the present invention.
Fig. 2 is the general function framework of aircraft structure intelligent numerical control machining prgraming system of the present invention.
Fig. 3 is the realization flow figure of aircraft structure intelligent numerical control machining prgraming system of the present invention.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail; the present embodiment is under prerequisite, to implement take technical solution of the present invention; provided detailed embodiment and concrete implementation procedure, but protection scope of the present invention is not limited to following embodiment.
Fig. 1 is the aircraft structure intelligent numerical control machining prgraming system mode chart of (being called for short INCPro), by process program, driven the intelligence programming of aircraft structure, realized intellectuality, standardization and the self-optimizing of programming, the program height of establishment meets technological requirement, and can embody programmer's thought.Its main thought is: according to layering rough machining method thought, adopt the machining feature of layered characteristic recognition methods identification detail of construction, and the machining feature type comprising based on part and feature intelligent inference are chosen the process program template (aircraft structure of each type all has process program template separately) of part; Then, the Feature Selection cutter of the geometric parameter based on machining feature to the processing of each operation in process program template/work step, and cutter and process program template are merged mutually, construct macroscopical process program, comprise station, operation, work step and all kinds of operation resource; Adopting process scheme drives digital control processing unit automatically to construct again, according to cutter on the basis of calculating in real time at relic model, can working ability automatically build digital control processing unit, then macroscopical technological process of describing with process program drives machining cell to carry out intelligent optimization sequence to meet technique and shortest path requirement, and the machining cell after serializing and process program are merged mutually and generate digital control processing unit sequence; Finally, digital control processing unit sequence is mapped to existing CAD/CAM digital control processing module, a machining cell example changes into a process operation, by all process operations, can complete processing cutter rail calculates, and process and be converted to NC code by postposition, finally complete the automatic generation of part by numerical control program; This system be take CAD/CAM system as shown in Figure 2 as platform, comprise process resource and knowledge base management 1., 2. model detect, 3. process program generates automatically, automated programming subsystem 4., the numerical control program intelligent optimization 5 modules such as 5..
Wherein, described CAD/CAM system platform, supports for INCPro provides platform, and first system sets up 3 d part model and the blank model of aircraft structure on this platform, for system provides basis input data; In addition, the machining cell constructed according to automated programming module, applies " digital control processing " Module Generation process operation of this platform and sets and carry out the calculating of cutter rail, machining simulation and rearmounted processing, realizes the automatic generation of digital control processing file;
Described process resource and knowledge base management module 1., for system provides shoring of foundation data, supports the interface that data and other modules are carried out exchanges data, and the management function of supporting database; Wherein, supporting database comprises process knowledge storehouse, lathe parameter storehouse, workpiece material storehouse, cutter parameters and material depot, Numerical Control Cutting storehouse, process program template base and other resources banks; Secondly, by setting up the data-interface of other modules and supporting database, realize data transmission between disparate modules, call and manage, complete being connected of supporting database and whole INCPro, realize the sharing and management of data resource; In addition, the management of supporting database comprises inquiry, deletion, insertion, modification, preservation and the reasoning of various support data, facilitates checking and upgrading of various support data;
2. described model detection module is mainly responsible for part model to carry out robotization detection, specifically comprises: (1) part model design mistake: in the part model of design, comprised the non-existent structure of actual product, comprised residual body, narrow slit; (2) markup information is imperfect: according to MBD model definition standard, whether geometry and the non-geological information automatically identified in part model be complete; (3) processability of product structure is not enough: according to existing process resource (comprising cutter, frock, lathe etc.) and process, automatically detect the bad even completely not machinable structure of the manufacturability existing in part model; Realization is to part model correctness, technological automatic examination; According to examination result, the method for type, position and the modification of prompting problem, and automatically revise for some frequent faults, with the method, guarantee the correctness of part model;
Described process program automatically-generating module 3., for realizing the numerical control program of technological process driving, automatically generate macroscopical process program is provided, wherein process program adopts multiway tree to represent, comprise part, lathe, station, operation, work step, program, cutter, eight grades of nodes of feature, can describe macroscopical machining process; This module comprises following functions: (1) has set up process program template base: existing aircraft component is classified and summed up the general technology flow process of these structural members, and set up processing scheme template for every quasi-representative structural member, comprise lathe, station, operation, work step; (2) process program generates automatically: the resources such as the manufacture resource choosing method selecting machine tool based on feature, cutter, frock, and merge mutually with processing scheme template, automatically generate the numerical control processing technology scheme of aircraft structure;
Described automated programming subsystem 4., it is the nucleus module of aircraft structure intelligence programming, mainly comprise: (1) automatic feature recognition: according to the 3-D geometric model of aircraft structure and blank model, adopt layered characteristic recognition methods to carry out the feature identification of part, obtain all machining feature of part, and with tree structure form storage feature recognition result; (2) process program intelligent inference: according to conditions such as part type, process side number, blank type and feature recognition results, support data in combined process resource and base module, carry out intelligent knowledge reasoning and from process program template base, automatically recommend the processing scheme template of part; (3) cutter is chosen automatically: geometric parameter and process segment based on feature are chosen process tool, and for example the roughing tool based on ablation volume ratio is chosen; (4) machining cell intelligence structure and sequence: cutter is fused to and in processing scheme template, forms complete process program, the technological process of being described by process program again drives machining cell automatically to construct, according to cutter can working ability, residual region based in process extracts often to be chosen the machinable region of cutter, intelligent inference optimum process operation and calculates the required geometric parameter of process operation, form often the machining cell sequence of cutter, by process program and machining cell, merged mutually the digital control processing unit sequence of complete; (5) process operation generates automatically: digital control processing unit sequence automatic mapping is set to the process operation in " digital control processing " module of CAD/CAM system, and the geometric parameter of each process operation of Lookup protocol, policing parameter, cutter parameters, speed parameter and the connection of advance and retreat cutter, and carry out the calculating of cutter rail and machining simulation;
5. described numerical control program intelligent optimization module is mainly responsible for the processing sequence of the resource of choosing in intelligence programming process, arrangement etc. to be optimized, be specially: (1) cutter is chosen optimization: adopt the method for selecting roughing tool based on ablation volume ratio, according to given tool magazine list, from tool magazine, according to diameter, calculate every the machinable all machining area volumes of cutter successively, when there being a region to be processed volume that the machinable volume of cutter is greater than to 80%, think that this cutter is suitable roughing tool; In addition, take the shortest process time as optimization aim, corner processing and sidewall finishing tool are optimized, sharp processing in qualified corner machining feature and sidewall is chosen to multiple cutter scheme processes, by calculating the cutter of determining profile machining feature in corner feature and sidewall process time of different schemes bottom tool, realize the optimization of corner feature and sidewall finishing tool and choose; (2) roughing hierarchy optimization: for the how sagging structure in aircraft structure, take that to realize the layering roughing time minimum be prerequisite, the bottom web that guarantees each vallecular cavity feature after roughing can adopt finishing web cutter one cutter to complete under accurately machined prerequisite, adopt genetic algorithm to carry out intelligent optimization to minute aspect, realize the minimum of roughing minute aspect, to improve roughing efficiency; (3) machining cell path optimization: minute Macro and two aspect of cutter layer are optimized; At Macro, the technological process of describing according to process program, carries out auto-sequencing by all digital control processing unit according to macroscopical technological process (comprising lathe, station, operation, work step and cutter); At cutter layer, to every, the machining cell of cutter association is carried out to level Four grouping, first the machining cell of cutter association is divided into a plurality of secondary unit groups according to the difference of work step type and (comprises two types: add work order tuple and target work sheet tuple, wherein add work order tuple and under current work step work step before added to work order metaset, target machining cell is that current work step is specified the unit collection that will process), and will add work order tuple and process prior to target work sheet tuple; Secondly, by adding work order tuple, according to the type of machining cell place work step, it is divided into groups again, form three grades of unit groups, and according to technological process order, these three grades of unit groups are sorted successively; Have again, three grades of unit groups are carried out to top-down whole layer sorting, form level Four unit group; Finally, the machining path of take is the shortest is optimization aim, to the machining cell in level Four unit group, adopts simulated annealing to carry out path optimization's sequence, realizes the optimization of machining path in level Four unit group.Adopt and can realize in this way the machining cell Optimal scheduling that process program drives, considered the sequence of geometry level and process level, can significantly improve sequence efficiency and quality.
Fig. 3 is the main-process stream of realizing for aircraft structure intelligent numerical control machining prgraming system of the present invention, and the concrete steps of realization are as follows:
Step 1): enter " digital control processing " module (S1) of CAD/CAM platform, and enter INCPro system (S2), be written into aircraft structure three-dimensional model and blank model;
Step 2): carry out the setting of part essential information, specifically have: the type (S3) of (1) part: wallboard, frame, beam, rib, joint etc.; (2) process side number (S4): comprise one side, two-sided and multiaspect; (3) blank type (S5): comprise sheet material, section bar, forging and foundry goods;
Step 3): enter model detection module 2., in conjunction with part model manufacturability, part model is carried out to quality testing (S6), and revise accordingly (S7) to not meeting the local error structure of actual process requirement, make part model meet processing technology requirement, to guarantee to input the correctness of part model;
Step 4): enter automated programming module 4., first need according to step 2) in the part type set for each process side, to set corresponding machining coordinate with process side information be (S8), then under each machining coordinate system, all manifold of part are carried out to face type identification (S9), identify based on this pore structures such as countersunk, counter sink, vertebral foramen, cylinder straight hole, and delete transverse holes and oblique hole, be convenient to the smooth realization of feature identification; Under each machining coordinate system, the slot descriptor characteristic recognition method of employing based on layering processing thought carries out machining features recognition (S10) to part, creating layering aspect and material object parts asks and hands over and obtain out intersection ring and the inner and outer ring relation thereof of every layer, by this relation, determined the machining area of every layer, then extract the part manifold that in intersection ring, sideline relies on, again the face that in intersection ring, all sidelines rely on is combined, and then form slot descriptor feature, then construct aircraft structure slot descriptor feature structure tree (S11) according to the incidence relation between longitudinal surface;
Step 5): after the feature identification in step 4), man-machine interactively selects whether to be written into existing similar part process program (S12), if select "Yes", the process program of intelligent search similar part from processing scheme storehouse, then by manually choosing by mutual mode optimization; Otherwise enter process program automatically-generating module 3., according to technique experimental knowledge and part type, carry out knowledge reasoning (S13), determine the process program template (S14) of current part, comprise lathe, station, operation, work step etc., based on machining feature, automatically choose cutter (S15) again, determine and in each process segment process, process the needed cutter parameters of different characteristic and cutting parameter (S16), and processing scheme template and cutter are chosen to result merge, generate complete process program (S17); Build by the way after process program, the tree structure that formation comprises seven grades of nodes (part node, lathe node, process side node, procedure-node, work step node, program node and cutter node), manually can interactive modifying (S19) and carry out validity check (S20), finally confirm to preserve (S21); If part is processing first, its process program is added to automatic powder adding in processing scheme storehouse, for calling of next similar part, and the unitarity of assured plan and standardization;
Step 6): again enter automated programming module 4., first the process program generating from step 5), extract the cutter that each work step is used, and the cutter choosing method based on how much, cutter and machining feature are set up to matching relationship (S22), guarantee that machining feature has suitable cutter to process in the different process segments; Then, macroscopical technological process of describing according to process program and cutter can working ability, and on the basis of calculating in real time in residual region, solve cutter can machining area (S23), process operation is chosen in optimization and calculating processing operates the required information such as geometric parameter automatically to build machining cell (S24), completes the structure (S25) of Flight Structures NC Machining machining cell;
Step 7): in step 6) digital control processing cell formation process, need to enter digital control processing intelligent optimization module 5., carry out the Optimization Works such as roughing hierarchy optimization (S26), machining path optimization (S27), realize the optimization of numerical control program, finally improve efficiency of numerical control (NC) machining;
Step 8): last, in CAM system, automatically generate the process operation tree (S29) corresponding with Flight Structures NC Machining machining cell sequence, wherein process operation is to use one cutter, one group of machined parameters and a job sequence that parametrization cutter rail generates, by the policing parameter of each machining cell in digital control processing unit sequence, machined parameters, geometric parameter, cutter parameters and processing macro parameter are set to respectively in corresponding process operation, can complete the automatic generation of process operation, and then all process operations are carried out to cutter rail calculating (S30) and machining simulation (S31), complete the intelligence establishment of Flight Structures NC Machining program, finally, by front and rear handling procedure (S32), numerical control machining knife rail is converted to the NC code (S33) of corresponding digital control system.
Claims (3)
1. aircraft structure intelligent numerical control machining prgraming system, this system be take CAD/CAM system as platform, comprise process resource and knowledge base management module and automated programming subsystem, it is characterized in that: system also comprises model detection module, process program automatically-generating module and numerical control program intelligent optimization module;
Described model detection module, is responsible for part model to carry out robotization detection, specifically comprises: (1) part model design mistake; (2) markup information is imperfect; (3) processability of product structure is not enough; Realization is to part model correctness, technological automatic examination; According to examination result, the method for type, position and the modification of prompting problem, and automatically revise for some frequent faults;
Described process program automatically-generating module, for realizing the numerical control program of technological process driving, automatically generate macroscopical process program is provided, wherein process program adopts multiway tree to represent, comprise part, lathe, station, operation, work step, program, cutter, eight grades of nodes of feature, can describe macroscopical machining process; By process program automatically-generating module, set up process program template base, existing aircraft structure is classified and summed up the general technology flow process of structural member, for every quasi-representative structural member, set up processing scheme template, comprised lathe, station, operation, work step; Then, the manufacture resource choosing method selecting machine tool based on machining feature, cutter, frock resource, and merge mutually with processing scheme template, automatically generate the numerical control processing technology scheme of aircraft structure;
Described numerical control program intelligent optimization module is responsible for the processing sequence of the resource of choosing in intelligence programming process, arrangement etc. to be optimized, be specially: (1) cutter is chosen optimization: adopt the method for selecting roughing tool based on ablation volume ratio, according to given tool magazine list, from tool magazine successively according to every the machinable vallecular cavity machining area of cutter volume in diameter computation structure part, when there being a region to be processed volume that the machinable volume of cutter is greater than to 80%, think that this cutter is suitable roughing tool; In addition, take the shortest process time as optimization aim, corner processing and sidewall finishing tool are optimized, sharp processing in qualified corner machining feature and sidewall is chosen to multiple cutter scheme processes, by calculating the cutter of determining profile machining feature in corner feature and sidewall process time of different schemes bottom tool, realize the optimization of corner feature and sidewall finishing tool and choose; (2) roughing hierarchy optimization: for the how sagging structure in aircraft structure, take that to realize the layering roughing time minimum be prerequisite, the bottom web that guarantees each vallecular cavity feature after roughing can adopt finishing web cutter one cutter to complete under the prerequisite of processing, adopt genetic algorithm to carry out intelligent optimization to minute aspect, realize the minimum of roughing minute aspect; (3) machining cell path optimization: minute Macro and two aspect of cutter layer are optimized; At Macro, the technological process of describing according to process program, according to macroscopical technological process, comprises lathe, station, operation, work step and cutter by all digital control processing unit, carries out auto-sequencing; At cutter layer, to every, the machining cell of cutter association is carried out to level Four grouping, first the machining cell of cutter association is divided into a plurality of secondary unit groups according to the difference of work step type and (comprises two types: add work order tuple and target work sheet tuple, wherein add work order tuple and under current work step work step before added to work order metaset, target machining cell is that current work step is specified the unit collection that will process), and will add work order tuple and process prior to target work sheet tuple; Secondly, by adding work order tuple, according to the type of machining cell place work step, it is divided into groups again, form three grades of unit groups, and according to technological process order, these three grades of unit groups are sorted successively; Have again, three grades of unit groups are carried out to top-down whole layer sorting, form level Four unit group; Finally, the machining path of take is the shortest is optimization aim, to the machining cell in level Four unit group, adopts simulated annealing to carry out path optimization's sequence, realizes the optimization of machining path in level Four unit group.
2. aircraft structure intelligent numerical control machining prgraming system according to claim 1, it is characterized in that: described automated programming subsystem, mainly comprise: (1) automatic feature recognition: according to the 3-D geometric model of aircraft structure and blank model, adopt layered characteristic recognition methods to carry out the feature identification of part, obtain all machining feature of part, and with tree structure form storage feature recognition result; (2) process program intelligent inference: according to conditions such as part type, process side number, blank type and feature recognition results, support data in combined process resource and base module, carry out intelligent knowledge reasoning and from process program template base, automatically recommend the processing scheme template of part; (3) cutter is chosen automatically: geometric parameter and process segment based on feature are chosen process tool, and for example the roughing tool based on ablation volume ratio is chosen; (4) machining cell intelligence structure and sequence: cutter is fused to and in processing scheme template, forms complete process program, the technological process of being described by process program again drives machining cell automatically to construct, according to cutter can working ability, residual region based in process extracts often to be chosen the machinable region of cutter, intelligent inference optimum process operation and calculates the required geometric parameter of process operation, form often the machining cell sequence of cutter, by process program and machining cell, merged mutually the digital control processing unit sequence of complete; (5) process operation generates automatically: digital control processing unit sequence automatic mapping is set to the process operation in " digital control processing " module of CAD/CAM system, and the geometric parameter of each process operation of Lookup protocol, policing parameter, cutter parameters, speed parameter and the connection of advance and retreat cutter, and carry out the calculating of cutter rail and machining simulation.
3. an implementation method for aircraft structure intelligent numerical control machining prgraming system as claimed in claim 1, is characterized in that: concrete steps are as follows:
Step 1): enter " digital control processing " module of CAD/CAM platform, and enter " aircraft structure intelligent numerical control machining prgraming system ", be written into aircraft structure three-dimensional model and blank model;
Step 2): carry out the setting of part essential information, specifically have: the type of (1) part: wallboard, frame, beam, rib, joint etc.; (2) process side number: comprise one side, two-sided and multiaspect; (3) blank type: comprise sheet material, section bar, forging and foundry goods;
Step 3): enter model detection module, in conjunction with part model manufacturability, part model is carried out to quality testing, and revise accordingly not meeting the local error structure of actual process requirement, make part model meet processing technology requirement, to guarantee to input the correctness of part model;
Step 4): enter automated programming module, first need according to step 2) in the part type set for each process side, set corresponding machining coordinate with process side information and be, then under each machining coordinate system, all manifold of part are carried out to face type identification, identify based on this pore structures such as countersunk, counter sink, vertebral foramen, cylinder straight hole, and delete transverse holes and oblique hole, be convenient to the smooth realization of feature identification; Under each machining coordinate system, the slot descriptor characteristic recognition method of employing based on layering processing thought carries out machining features recognition to part, creating layering aspect and material object parts asks and hands over and obtain out intersection ring and the inner and outer ring relation thereof of every layer, by this relation, determined the machining area of every layer, then extract the part manifold that in intersection ring, sideline relies on, again the face that in intersection ring, all sidelines rely on is combined, and then form slot descriptor feature, then construct aircraft structure slot descriptor feature structure tree according to the incidence relation between longitudinal surface;
Step 5): after the feature identification in step 4), man-machine interactively selects whether to be written into existing similar part process program, if select "Yes", the process program of intelligent search similar part from processing scheme storehouse, then by manually choosing by mutual mode optimization; Otherwise enter process program automatically-generating module, according to technique experimental knowledge and part type, carry out knowledge reasoning, determine the process program template of current part, comprise lathe, station, operation, work step etc., based on machining feature, automatically choose cutter again, determine and in each process segment process, process the needed cutter parameters of different characteristic and cutting parameter, and processing scheme template and cutter are chosen to result merge, generate complete process program; Build by the way after process program, form the tree structure that comprises eight grades of nodes, wherein seven grades of nodes are specially: part node, lathe node, process side node, procedure-node, work step node, program node, cutter node and characteristic node; Manually can interactive modifying and carry out validity check, finally confirm to preserve; If part is processing first, its process program is added to automatic powder adding in processing scheme storehouse;
Step 6): again enter automated programming module, first the process program generating from step 5), extract the cutter that each work step is used, and the cutter choosing method based on how much, cutter and machining feature are set up to matching relationship, guarantee that machining feature has suitable cutter to process in the different process segments; Then, macroscopical technological process of describing according to process program and cutter can working ability, and on the basis of calculating in real time in residual region, solve cutter can machining area, process operation is chosen in optimization and calculating processing operates the required information such as geometric parameter automatically to build machining cell, completes the structure of Flight Structures NC Machining machining cell sequence;
Step 7): in step 6) digital control processing cell formation process, need to enter digital control processing intelligent optimization module, carry out the Optimization Works such as roughing hierarchy optimization, machining path optimization, realize the optimization of numerical control program;
Step 8): last, in CAM system, automatically generate the process operation tree corresponding with Flight Structures NC Machining machining cell sequence, wherein process operation is to use one cutter, one group of machined parameters and a job sequence that parametrization cutter rail generates, by the policing parameter of each machining cell, machined parameters, geometric parameter, cutter parameters and processing macro parameter are set to respectively in corresponding process operation, can complete the automatic generation of process operation, and then all process operations are carried out to the calculating of cutter rail and machining simulation, complete the intelligence establishment of Flight Structures NC Machining program, finally, by front and rear handling procedure, numerical control machining knife rail is converted to the NC code of corresponding digital control system.
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