CN101763068A - Preparation system of quick numerical control machining of complex parts of airplane and method - Google Patents

Abstract

The invention discloses a preparation system of quick numerical control machining of complex parts of an airplane and a method. The system takes the existing CAD/CAM system as a platform, and comprises a technology resource and knowledge base management module, a quick blank generation module, a part classification and technical scheme analysis module, an automatic programming module, a quick tool generation module, a strain analysis and deformation control module, a front and rear process module and a technology data generation module. The system is built on the basis of a three-dimensional numeric part model, systematically and exactly embodies a specialized flow path for supporting the numerical control machining technology preparing and the programming of the complex parts of the airplane, can greatly reduce man-machine interaction operation required by preparing technology and programming, effectively solves the problems of the unstable programmed procedure and the unreasonable scheme design of the machining technology caused by the lack of the experience of process operators, and the like, can effectively control the deformation quantity during and after machining the parts, can obviously improve the efficiency and the quality of the numerical control machining preparing and the programming, and improves the professional level and the intelligence level of the CAD/CAM system.

Description

Preparation system of quick numerical control machining of complex parts of airplane and method

Technical field

The present invention relates to a kind of preparation system of quick numerical control machining of complex parts of airplane and method, the quick numerical control processing technology that is applied to aircraft complex component is prepared and programming, and then the efficient high-quality digital control processing of realization aircraft complex component, belong to aircraft structure digital intelligent processing technique field.

Background technology

A large amount of integral structure components that adopt improve aeroplane performance to shorten processing and assembly period and weight reduction in the present generation aircraft structure.But aircraft complex component has complex structure, characteristics such as manufacturing accuracy requires high, and difficulty of processing is big, and the today's numerical control processing technology is prepared and there are a lot of problems in numerical control programming: (1) processing experimental knowledge is not carried out regularization, unitized, do not bring into play inheritance; (2) adopt existing CAD/CAM system, the blank systematic function is simple, can't satisfy actual processing needs, and the mutual amount of programming is huge, and the cycle is long; (3) technology person's personal experience and know-how is depended in processing technology planning to a great extent, and randomness is bigger, causes the program quality instability; (4) structural member is yielding in the digital control processing process, influences part processing quality and machining precision; (5) the frock design also is to rely on the personal experience, and the design cycle is long, the quality instability; (6) post processing program can't be finished the code conversion between the different NC system; (7) especially lack a whole set of the specialized flow process that on digitizing three-dimensional model basis, realizes numerical control processing technology preparation and numerical control programming, causing links such as process program planning, digital control processing programming, machining deformation analysis, the design of clamping configuration, clamping scheme, blank generation to lack each other coordinates with related, and then have influence on the working (machining) efficiency and the quality of aircraft structure, prolonged the aircraft manufacturing cycle.

Summary of the invention

In order to solve the problem of above-mentioned existence, the invention provides a kind of preparation system of quick numerical control machining of complex parts of airplane and method;

The objective of the invention is to be achieved through the following technical solutions:

A kind of preparation system of quick numerical control machining of complex parts of airplane and method, this system is based upon on the existing CAD/CAM system platform, form by process resource and knowledge base management module, quick blank generation module, part classification and process program analysis module, automated programming module, quick frock generation module, stress analysis and Deformation control module, front and rear processing module and process data generation module eight parts, wherein:

Described existing CAD/CAM system platform, for providing platform, " preparation system of quick numerical control machining of complex parts of airplane " support, system at first sets up aircraft complex component 3 d part model on this platform, and carry out exchanges data with eight big modules of system, auxiliary location, clamping and the generation that realizes the frock model, the auxiliary blank model that generates part; Utilize in " deformation analysis " module implementation structure spare process of CAD/CAM system platform then and the deformation analysis after processing; Last " digital control processing " module according to the constructed machining cell application CAD/CAM system platform of automated programming module is auxiliary to be generated the process operation tree and carries out calculating of cutter rail and machining simulation;

Described process resource and knowledge base management module, for providing shoring of foundation data, support data and other modules, system carries out the interface of exchanges data, and the management of supporting database, wherein supporting database comprises process knowledge storehouse, lathe parameter storehouse, workpiece material storehouse, cutter parameters and material depot, digital control processing cutting parameter storehouse, tool standard part storehouse, tool typical parts storehouse, frock inspection template model bank, frock design knowledge base; In addition by setting up the data-interface of other modules and supporting database, realize between disparate modules data transmission, call and manage, finish being connected of supporting database and whole " preparation system of quick numerical control machining of complex parts of airplane ", supporting database and total system are associated together, realize sharing and management of data resource; The management of supporting database comprises inquiry, deletion, insertion, modification, preservation and the reasoning of various support data, the checking and upgrade of convenient various support data;

Described quick blank generation module is determined the process redundancy at each position of part to generate the blank model according to part model, blank type and other process constraint condition automatically;

Described part classification and process program analysis module are at first classified to existing aircraft complex component and are defined characteristic features different in these parts and structure; The combined process resource is determined the processing scheme that various parts are corresponding with the process knowledge storehouse in the knowledge base management module then, comprises that job operation, clamping method, the cutter of determining various features, structure are recommended, cutting parameter is recommended and lathe is recommended;

Described automated programming module is at first carried out the machining feature identification of one-piece parts according to the digitizing three-dimensional model of aircraft complex component, obtain all machining feature of part; Secondly according to part model, part type, process side number, blank type, blank model and feature identification result, support data in combined process resource and the knowledge base management module again, carry out the processing scheme of knowledge reasoning generation part, wherein processing scheme adopts multiway tree to represent, corresponding with the machining process of reality, promptly generate the processing scheme structure tree; Automatically choose the cutter that each process segment different characteristic adopts according to different processing stages and machining feature geometric parameter then, and carry out the processing sequence that knowledge reasoning is determined different characteristic in the structural member automatically according to the processing technology knowledge of different parts; Choose result and processing scheme structure tree according to feature identification result, cutter again, automatically in " digital control processing " module of CAD/CAM system, generate the process operation tree, and each process operation is provided with processing geometric parameter, Processing Strategies parameter, cutter parameters, cutting parameter and processing transition automatically connects, and then realize the automatic generation of processed file; Carry out the cutter rail at last and calculate and machining simulation, and in process, carry out the cutting parameter analysis, realize that the optimization of cutting parameter is chosen;

Described quick frock generation module, determine clamping and the position location that current operation needs at first fast, determine the clamping scheme of part fast, secondly by stress analysis and Deformation control module this clamping scheme is carried out the frock scheme that optimization is obtained in deformation analysis, determine fast to clamp and the steady arm type in conjunction with man-machine interaction again, from the tool typical parts storehouse of process resource and knowledge base management module, tool standard part storehouse, call corresponding location and clamp device model at last, and locate accordingly and install;

Described stress analysis and Deformation control module, be used to optimize frock and cutting parameter, supplementary module as system, after the frock clamping is finished, surface of the work stress distribution in the sunykatuib analysis process, and analyze the material deformation that machines each clamping point position on back surface of the work residual stress distribution and the workpiece, calculate the deflection of part workpiece after processing then; According to analyzing and result of calculation, adjust the organization plan and the cutting parameter of frock, with the distortion of control workpiece;

Described front and rear processing module, be used to realize the conversion between the different numerical control programs, wherein pre-process is used for converting the CAD/CAM system processed file to intermediate code APT file, the rearmounted machining code that is used for APT is converted to different NC system of handling, and, realize its freely changing each other at the numerical control program of different NC system;

Described process data generation module extracts the every content in the parts machining process rules, adds to then in the technology form, generates flow process chart, manufacturing procedure card, NC cutting tool card, clamping figure and part and sets card.

The concrete steps of preparation system of quick numerical control machining of complex parts of airplane implementation method are as follows:

Step 1): enter " digital control processing " module of CAD/CAM system platform, and enter preparation system of quick numerical control machining of complex parts of airplane, be written into existing aircraft complex component part model;

Step 2): carry out the setting of part essential information, specifically have: the type of (1) part: wallboard, frame, beam, rib, long purlin, joint and edge strip; (2) process side number: comprise single face, two-sided and multiaspect; (3) blank type: comprise sheet material, section bar, forging and foundry goods;

Step 3): the process characteristic in conjunction with part model carries out quality testing to part model, and revise accordingly not satisfying the local error structure that actual process requires, make part model satisfy the processing technology requirement, to guarantee to be input to the correctness of the part model in system's eight big modules;

Step 4): enter quick blank generation module, by step 2) in the part type set determine the blank type of this part, at first part model is carried out the analysis of blank process redundancy, then in conjunction with blank type and blank process redundancy, be aided with suitable man-machine interaction again, on the basis of part model, generate the blank model fast, form processing model by part model and blank model at last;

Step 5): enter the automated programming module, at first need according to step 2) in the part type set with process side information be for the corresponding machining coordinate of each process side setting, under each machining coordinate system, all manifold of part are carried out the identification of Noodles type then, and organize hole operation according to Noodles type recognition result, the identification and the structure that comprise countersunk, counter sink, taper hole, cylinder straight hole, deletion action is carried out in transverse holes and the oblique hole formed, with convenient follow-up feature identification; Under current machining coordinate is, employing is carried out machining feature identification based on the slot descriptor characteristic recognition method of layering thought to part, promptly creating layering aspect and part entity asks friendship and obtains out every layer intersection ring, extract the face that the sideline relies in the intersection ring then, by the annexation between the different sidelines in the intersection ring face that these sidelines rely on is made up again, and then form the slot descriptor feature, construct aircraft structure slot descriptor feature structure tree according to the incidence relation between the longitudinal surface again;

Step 6): after the feature identification in the step 5), man-machine interactively sets whether be written into existing similar part processing scheme, if selected "Yes" from the processing scheme storehouse processing scheme of coupling similar part automatically, show on system interface with tabular form, be optimized by man-machine interactively once more and choose; Otherwise enter part classification and process program analysis module, carry out knowledge reasoning according to technology experimental knowledge and part type, determine the basic processing scheme of current part, comprise that lathe information, process side information, overall process segment divide etc., divide according to part feature information and process segment again, automatically choose cutter, determine processing needed cutter parameters of different characteristic and cutting parameter in each process segment process, basic processing scheme and cutter are chosen the result merge, promptly generate the part processing scheme of recommending; After above-mentioned dual mode generation part processing scheme, enter processing scheme interactive modifying interface, the whole machining process of multiway tree structure representation part is adopted at this interface, this tree comprises part node, lathe node, process side node, operation node, work step node, program node, cutter node, manually processing scheme is carried out interactive modifying and inspection then, confirm at last to preserve; If be the part of first processing, its processing scheme adds in the processing scheme storehouse automatically, for calling of next similar part, guarantees the unitarity and the standardization of scheme;

Step 7): enter the automated programming module once more, at first from the processing scheme that step 6) generates, extract the tool-information that uses in each operation work step, and with the machining feature information of extracting in these cutters coupling step 5), it is related that machining feature and cutter are carried out, and guarantees that machining feature has suitable cutter to process in the different process segments; Then in conjunction with processing scheme, and the corresponding informance of feature and cutter, make up the machining cell of part, mainly contain:＜1 the roughing unit structure: adopt layering roughing thought, at first machining feature is optimized layering, obtains how much guidings of processing wire loop of each aspect then, and revise accordingly, connect in conjunction with bottom surface, end face, cutter parameters, cutting parameter, Processing Strategies parameter and processing transition more in addition, promptly finish the structure of roughing unit;＜2〉the sidewall finishing unit makes up: with reference to the roughing unit building mode, obtain how much guide wires of the accurately machined processing of machining feature, connect in conjunction with bottom surface, end face, cutter parameters, cutting parameter, Processing Strategies parameter and processing transition again, make up finishing unit; Set according to processing scheme at last, automatically in the CAM system, generate the process operation tree, wherein process operation is the set of a concrete machining cell information, comprising Processing Strategies parameter, machined parameters, geometric parameter, cutter parameters and the processing macro transition of processing current feature connects, again all process operations in the process operation tree are carried out the cutter rail and calculate and machining simulation, and in-problem cutter rail is revised;

Step 8) enters quick frock generation module, calculates clamping and the position location that current operation needs at first automatically, secondly extracts discrete cutting point from the cutter rail information that the automated programming module generates, and carries out the calculating of clamping force, anchorage force and cutting force; Enter into stress analysis and Deformation control module then, in this module according to clamped position, the position location, and act on these locational power, set up part processing process stress strain analysis model, carry out stress-strain analysis by Automatic Program, if deformation result does not meet the demands, then continue adjustment clamping point and anchor point and carry out the analysis of next scheme, up to the frock scheme that gets access to an optimization, then from the tool typical parts storehouse of process resource and knowledge base management module, call corresponding location and clamp device model in the tool standard part storehouse, and locate accordingly and install;

After step 9) frock three-dimensional model had generated, need judge whether needed to revise the cutter rail, if then need the tool setting rail to revise, prevented to produce interference with the frock model; If do not need, then enter step 10);

Step 10) enters the front and rear processing module, at first convert the processed file of CAM system to the APT intermediate code by the pre-process program, and then in conjunction with specific numerically-controlled machine code format, it is carried out semantic analysis and parsing, generate corresponding numerically-controlled machine code through post processing program, be saved in file; The lathe code that generates is carried out machining simulation, check whether to exist and cut or residual region, if it is then revise the cutter rail once more, entirely true up to the code that generates;

Step 11) enters the process data generation module at last, at first the Middleware Model that generates according to the automated programming module realizes generating the operation sketch by the middleware three-dimensional model automatically, and wherein the operation sketch comprises middleware projection sketch, machining coordinate system, local detail explanation and local size mark; Then according to content in the actual process list and form, and the processing scheme of automated programming module generation, extract the process data information in the processing scheme, process data information comprises that lathe, process side are to, operation, work step, program, cutter and frock, and its content and operation sketch added in the corresponding technology list automatically, and then the relevant card in the generating structure spare processing technology rules, comprise flow process chart, manufacturing procedure card, NC cutting tool card and clamping figure and part setting card.

Beneficial effect of the present invention: the present invention is based upon on the three-dimensional digitalization model basis of part, than system with embody exactly and support the aircraft complex component numerical control processing technology to prepare and the specialized flow process of programming, use this system, can directly on the components three-dimensional model, carry out and realize planning from process program, the digital control processing programming, machining deformation is analyzed, the design of clamping configuration, blank and semi-finished articles three-dimensional modeling are to the clamping scheme, complete digital control processing set-up procedures such as process optimization and anchor clamps intelligentized design, can reduce man-machine interactive operation required in technological preparation and the programming process in a large number, can effectively solve because technology person lacks experience and cause the program instability worked out, problems such as the processing technology conceptual design is unreasonable, can significantly improve efficient and quality that digital control processing is prepared and programmed, and then the specialization and the intelligent level of lifting CAD/CAM system, will play an important role to satisfy pressing for of China's national defense construction to the development of accelerating current and following aviation model.

Description of drawings

Fig. 1 preparation system of quick numerical control machining of complex parts of airplane functional structure chart;

Fig. 2 preparation system of quick numerical control machining of complex parts of airplane realization flow figure.

Embodiment

Below in conjunction with accompanying drawing embodiments of the invention are described in detail; present embodiment is to be to implement under the prerequisite with the 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 preparation system of quick numerical control machining of complex parts of airplane functional structure chart, this system is based on " digital control processing " module of existing CAD/CAM system, collection process resource and knowledge base and corresponding intelligence interface thereof, be used for directly on the aircraft complex component three-dimensional model, carrying out and realizing planning from process program, the digital control processing programming, machining deformation is analyzed, the design of clamping configuration, blank and semi-finished articles three-dimensional modeling are to the clamping scheme, complete digital control processing set-up procedures such as process optimization and anchor clamps intelligentized design, it comprises eight big modules, be specially: process resource and knowledge base management module are 1., the blank generation module 2. fast, part classification and process program analysis module are 3., the automated programming module 4., the frock generation module 5. fast, stress analysis and Deformation control module are 6., the front and rear processing module 7. and the process data generation module 8., wherein:

Described existing CAD/CAM system platform, for providing platform, " preparation system of quick numerical control machining of complex parts of airplane " support, system at first sets up aircraft complex component 3 d part model on this platform, and carry out exchanges data with eight big modules of system, auxiliary location, clamping and the generation that realizes the frock model, the auxiliary blank model that generates part; Utilize in " deformation analysis " module implementation structure spare process of CAD/CAM system platform then and the deformation analysis after processing; Last " digital control processing " module according to the 4. constructed machining cell application CAD/CAM system platform of automated programming module is auxiliary to be generated the process operation tree and carries out calculating of cutter rail and machining simulation;

Described process resource and knowledge base management module are 1., for providing shoring of foundation data, support data and other modules, system carries out the interface of exchanges data, and the management of supporting database, wherein supporting database comprises process knowledge storehouse, lathe parameter storehouse, workpiece material storehouse, cutter parameters and material depot, digital control processing cutting parameter storehouse, tool standard part storehouse, tool typical parts storehouse, frock inspection template model bank, frock design knowledge base; In addition by setting up the data-interface of other modules and supporting database, realize between disparate modules data transmission, call and manage, finish being connected of supporting database and whole " preparation system of quick numerical control machining of complex parts of airplane ", supporting database and total system are associated together, realize sharing and management of data resource; The management of supporting database comprises inquiry, deletion, insertion, modification, preservation and the reasoning of various support data, the checking and upgrade of convenient various support data;

Described quick blank generation module 2., promptly determine the process redundancy at each position of part automatically according to part model, blank type and other process constraint condition, generate the blank model then, this module comprises the quick generation of three kinds of blanks:＜1〉sheet material, the automatic generation of section bar blank;＜2〉forging blank generates fast;＜3〉spray generates fast;

3. described part classification and process program analysis module are at first classified to existing aircraft complex component and are defined characteristic features different in these parts and structure; The combined process resource is determined the processing scheme that various parts are corresponding with the process knowledge storehouse in the knowledge base management module then, comprises that job operation, clamping method, the cutter of determining various features, structure are recommended, cutting parameter is recommended and lathe is recommended;

4. described automated programming module at first carries out the machining feature identification of one-piece parts according to the digitizing three-dimensional model of aircraft complex component, obtain all machining feature of part; Secondly according to part model, part type, process side number, blank type, blank model and feature identification result, support data in combined process resource and the knowledge base management module again, carry out the processing scheme of knowledge reasoning generation part, wherein processing scheme adopts multiway tree to represent, corresponding with the machining process of reality, promptly generate the processing scheme structure tree; Automatically choose the cutter that each process segment different characteristic adopts according to different processing stages and machining feature geometric parameter then, and carry out the processing sequence that knowledge reasoning is determined different characteristic in the structural member automatically according to the processing technology knowledge of different parts; Choose result and processing scheme structure tree according to feature identification result, cutter again, automatically in " digital control processing " module of CAD/CAM system, generate the process operation tree, and each process operation is provided with processing geometric parameter, Processing Strategies parameter, cutter parameters, cutting parameter and processing transition automatically connects, and then realize the automatic generation of processed file; Carry out the cutter rail at last and calculate and machining simulation, and in process, carry out the cutting parameter analysis, realize that the optimization of cutting parameter is chosen;

Described quick frock generation module 5., determine clamping and the position location that current operation needs at first fast, determine the clamping scheme of part fast, secondly 6. this clamping scheme is carried out the frock scheme that optimization is obtained in deformation analysis by stress analysis and Deformation control module, determine fast to clamp and the concrete installation way of locating in conjunction with man-machine interaction again, from 1. tool typical parts storehouse of process resource and knowledge base management module, tool standard part storehouse, call corresponding location and clamp device model at last, and locate accordingly and install;

Described stress analysis and Deformation control module are 6., be used to optimize frock and cutting parameter, supplementary module as system, after the frock clamping is finished, surface of the work stress distribution in the sunykatuib analysis process, and analyze the material deformation that machines each clamping point position on back surface of the work residual stress distribution and the workpiece, calculate the deflection of part workpiece after processing then; According to analyzing and result of calculation, adjust the organization plan and the cutting parameter of frock, with the distortion of control workpiece;

Described front and rear processing module 7., be used to realize the conversion between the different numerical control programs, wherein pre-process is used for the CAD/CAM system processed file and converts intermediate code APT file to, the rearmounted machining code that is used for APT is converted to different NC system of handling, and, realize its freely changing each other at the numerical control program of different NC system;

8. described process data generation module extracts the every content in the parts machining process rules, adds to then in the technology form, generates flow process chart, manufacturing procedure card, NC cutting tool card, clamping figure and part and sets card;

Fig. 2 is the main-process stream that preparation system of quick numerical control machining of complex parts of airplane is realized, is not proper series process between each module, but an interlaced process that relies on each other, the step of its specific implementation is:

Step 1): enter " digital control processing " module of CAD/CAM system platform, and enter into preparation system of quick numerical control machining of complex parts of airplane (S1), be written into aircraft complex component part model (S2) then;

Step 2): the type of interactive setup part (S3), aircraft complex component comprises following type: wallboard, frame, beam, rib, long purlin, joint and edge strip;

Step 3): at first the programmer carries out quality testing (S4) in conjunction with the process characteristic of part model to part model, and carry out corresponding model correction (S5) to not satisfying the local error structure that actual process requires, make part model satisfy the processing technology requirement, to guarantee to be input to the correctness of the part model in system's eight big modules; Carry out the setting (S6) of parts information then, comprise (1) process side number: comprise single face, two-sided and multiaspect; (2) blank type: comprise sheet material, section bar, forging and foundry goods;

Step 4): enter quick blank generation module 2., at first by step 2) in the part type set determine the blank type of this part, next carries out the setting (S7) of blank information, then part model is carried out the blank allowance analysis, at last in conjunction with blank type and blank allowance, be aided with suitable man-machine interaction again, on the basis of part model, generate blank model (S8) fast, it is last that affirmation generates final blank model (S9) through local correction again, and be written into the blank model (S10) of generation, form processing model by part model and blank model, the lathe resource (S11) of acquiescence is set in addition again;

Step 5): enter the automated programming module 4., at first need according to step 2) in the part type set be (S12) with the processing side information for the corresponding machining coordinate of each process side setting, under each machining coordinate system, all manifold of part are carried out Noodles type identification (S13) then, and organize hole operation according to Noodles type recognition result, the identification and the structure that comprise countersunk, counter sink, taper hole, cylinder straight hole, deletion action (S14) is carried out in transverse holes and the oblique hole formed, with convenient follow-up feature identification; Under current machining coordinate is, employing is carried out machining feature identification based on the slot descriptor characteristic recognition method of layering thought to part, promptly creating layering aspect and part entity asks friendship and obtains out every layer intersection ring (S15), extract the face (S16) that the sideline relies in the intersection ring then, by the annexation between the different sidelines in the intersection ring face that these sidelines rely on is carried out knowledge reasoning and rule match (S17) again, and then form slot descriptor feature (S18), construct aircraft structure slot descriptor feature structure tree according to the incidence relation between the longitudinal surface again;

Step 6): after the feature identification in the step 5), man-machine interactively sets whether be written into existing similar part processing scheme (S19), if selected "Yes" from the processing scheme storehouse processing scheme of coupling similar part automatically, show on system interface with tabular form, be optimized by man-machine interactively once more and choose, directly be written into similar processing scheme (S241) then; Otherwise enter part classification and process program analysis module 3., carry out knowledge reasoning according to technology experimental knowledge and part type, determine the basic processing scheme (S20) of current part, comprise lathe information, process side information, the overall process segment divides, divide according to part feature information and process segment again, automatically choose cutter (S21), determine processing needed cutter parameters of different characteristic and cutting parameter (S22) in each process segment process, basic processing scheme and cutter are chosen the result merge (S23), promptly generate the part processing scheme (S242) of recommending; After above-mentioned dual mode generation part processing scheme, eject processing scheme interactive editor interface, the whole machining process of multiway tree structure representation part is adopted at this interface, comprise part node, lathe node, process side node, operation node, work step node, program node and cutter node, manually can carry out interactive modifying and inspection (S25), confirm at last to preserve and output (S26) this scheme; If be the part of first processing, its processing scheme adds in the processing scheme storehouse automatically, for calling of next similar part, guarantees the unitarity and the standardization of scheme;

Step 7): enter the automated programming module once more 4., at first from the processing scheme that step 6) generates, extract the tool-information that uses in each operation work step, and with the machining feature information of extracting in these cutters coupling step 5), make machining feature and cutter carry out related (S27), guarantee that feature has suitable cutter to process in the different process segments; Then in conjunction with processing scheme, and the corresponding informance of feature and cutter, make up the machining cell (S28) of structural member processing, it mainly comprises:＜1〉the roughing unit structure: adopt layering roughing thought, at first machining feature is optimized layering, obtain how much guidings of processing wire loop (S29) of each aspect then, and revise (S30) accordingly, connect in conjunction with bottom surface, end face, cutter parameters, cutting parameter, Processing Strategies parameter and processing transition more in addition, promptly finish the structure of roughing unit;＜2〉the sidewall finishing unit makes up: with reference to the roughing unit building mode, obtain how much guide wires (S29) of the accurately machined processing of machining feature, and revise (S30) accordingly, connect in conjunction with bottom surface, end face, cutter parameters, cutting parameter, Processing Strategies parameter and processing transition again, make up finishing unit; Set according to processing scheme at last, automatically in the CAM system, generate process operation tree (S31), wherein process operation is the set of a concrete machining cell information, comprise geometric parameter (S32), Processing Strategies parameter (S33), machined parameters (S33), cutter parameters (S33) and the processing macro transition of processing current feature and connect (S33), again all process operations in the process operation tree are carried out the cutter rail and calculate (S34) and machining simulation (S35), and in-problem cutter rail is revised (S35);

5. step 8) enters quick frock generation module, at first system calculates clamping and position location (S37) that current operation needs automatically, and from the cutter rail information that 4. the automated programming module generates, extract discrete cutting point, and the calculating (S38) of carrying out clamping force, anchorage force and cutting force; Enter into stress analysis and Deformation control module then, in this module according to clamped position, the position location, and act on these locational power, set up part processing process stress strain analysis model (S39), carry out stress-strain analysis (S40) by Automatic Program, extract deformation result (S41), and judge and be out of shape whether meet the requirements (S42), if deformation result does not meet the demands, then continue adjustment clamping and position location (S37) and carry out the analysis of next scheme, up to the frock scheme (S43) that gets access to an optimization, otherwise directly obtain current frock scheme is prioritization scheme (S43), the frock scheme (S44) of output two dimension then, and interactive setup location binding clasp type (S45), again from the tool typical parts storehouse of process resource and knowledge base management module, call corresponding location and clamp device model (S46) in the tool standard part storehouse, and locate and install (S47) accordingly, generate frock three-dimensional model (S48) at last;

After step 9) frock three-dimensional model had generated, need judge whether needed to revise the cutter rail, promptly regenerates process operation (S49), if then reenter (S31) of step 7), need set frock information this moment in process operation, prevents to produce to interfere; Otherwise directly carry out the cutter rail and analyze and revise cutter rail (S50);

Step 10) front and rear processing module 7., at first convert the processed file in the CAM system to APT intermediate code (S52) by pre-process program (S51), and then in conjunction with specific numerically-controlled machine code format, it is carried out semantic analysis and parsing, generate corresponding numerically-controlled machine code (S54) through post processing program (S53), be saved in file; At last the lathe code that generates is carried out machining simulation (S55), check whether to exist and cut or residual region (S56), entirely true if then revise the cutter rail once more up to the code that generates, otherwise directly carry out the output (S57) of code;

8. step 11) enters the process data generation module at last, at first the Middleware Model that 4. generates according to the automated programming module realizes generating the operation sketch by the middleware three-dimensional model automatically, and wherein the operation sketch comprises middleware projection sketch, machining coordinate system, local detail explanation and local size mark; Then according to content in the actual process list and form, and the processing scheme that 4. generates of automated programming module, extract the process data information in the processing scheme, process data information comprises that lathe, process side are to, operation, work step, program, cutter and frock, and its content and operation sketch added in the corresponding technology list automatically, and then the relevant card in the generating structure spare processing technology rules, comprise flow process chart (S58), manufacturing procedure card (S59), NC cutting tool card (S60), clamping figure and part setting card (S61).

Claims (2)

1. preparation system of quick numerical control machining of complex parts of airplane, this system is based upon on the existing CAD/CAM system platform, it is characterized in that: form by process resource and knowledge base management module, quick blank generation module, part classification and process program analysis module, automated programming module, quick frock generation module, stress analysis and Deformation control module, front and rear processing module and process data generation module eight parts, wherein:

Described existing CAD/CAM system platform, for providing platform, " preparation system of quick numerical control machining of complex parts of airplane " support, system at first sets up aircraft complex component 3 d part model on this platform, and carry out exchanges data with eight big modules of system, auxiliary location, clamping and the generation that realizes the frock model, the auxiliary blank model that generates part; Utilize in " deformation analysis " module implementation structure spare process of CAD/CAM system platform then and the deformation analysis after processing; Last " digital control processing " module according to the constructed machining cell application CAD/CAM system platform of automated programming module is auxiliary to be generated the process operation tree and carries out calculating of cutter rail and machining simulation;

Described process resource and knowledge base management module, for providing shoring of foundation data, support data and other modules, system carries out the interface of exchanges data, and the management of supporting database, wherein supporting database comprises process knowledge storehouse, lathe parameter storehouse, workpiece material storehouse, cutter parameters and material depot, digital control processing cutting parameter storehouse, tool standard part storehouse, tool typical parts storehouse, frock inspection template model bank, frock design knowledge base; In addition by setting up the data-interface of other modules and supporting database, realize between disparate modules data transmission, call and manage, finish being connected of supporting database and whole " preparation system of quick numerical control machining of complex parts of airplane ", supporting database and total system are associated together, realize sharing and management of data resource; The management of supporting database comprises inquiry, deletion, insertion, modification, preservation and the reasoning of various support data, the checking and upgrade of convenient various support data;

Described quick blank generation module is determined the process redundancy at each position of part to generate the blank model according to part model, blank type and other process constraint condition automatically;

Described part classification and process program analysis module are at first classified to existing aircraft complex component and are defined characteristic features different in these parts and structure; The combined process resource is determined the processing scheme that various parts are corresponding with the process knowledge storehouse in the knowledge base management module then, comprises that job operation, clamping method, the cutter of determining various features, structure are recommended, cutting parameter is recommended and lathe is recommended;

Described automated programming module is at first carried out the machining feature identification of one-piece parts according to the digitizing three-dimensional model of aircraft complex component, obtain all machining feature of part; Secondly according to part model, part type, process side number, blank type, blank model and feature identification result, support data in combined process resource and the knowledge base management module again, carry out the processing scheme of knowledge reasoning generation part, wherein processing scheme adopts multiway tree to represent, corresponding with the machining process of reality, promptly generate the processing scheme structure tree; Automatically choose the cutter that each process segment different characteristic adopts according to different processing stages and machining feature geometric parameter then, and carry out the processing sequence that knowledge reasoning is determined different characteristic in the structural member automatically according to the processing technology knowledge of different parts; Choose result and processing scheme structure tree according to feature identification result, cutter again, automatically in " digital control processing " module of CAD/CAM system, generate the process operation tree, and each process operation is provided with processing geometric parameter, Processing Strategies parameter, cutter parameters, cutting parameter and processing transition automatically connects, and then realize the automatic generation of processed file; Carry out the cutter rail at last and calculate and machining simulation, and in process, carry out the cutting parameter analysis, realize that the optimization of cutting parameter is chosen;

Described quick frock generation module, determine clamping and the position location that current operation needs at first fast, determine the clamping scheme of part fast, secondly by stress analysis and Deformation control module this clamping scheme is carried out the frock scheme that optimization is obtained in deformation analysis, determine fast to clamp and the steady arm type in conjunction with man-machine interaction again, from the tool typical parts storehouse of process resource and knowledge base management module, tool standard part storehouse, call corresponding location and clamp device model at last, and locate accordingly and install;

Described stress analysis and Deformation control module, be used to optimize frock and cutting parameter, supplementary module as system, after the frock clamping is finished, surface of the work stress distribution in the sunykatuib analysis process, and analyze the material deformation that machines each clamping point position on back surface of the work residual stress distribution and the workpiece, calculate the deflection of part workpiece after processing then; According to analyzing and result of calculation, adjust the organization plan and the cutting parameter of frock, with the distortion of control workpiece;

Described front and rear processing module, be used to realize the conversion between the different numerical control programs, wherein pre-process is used for the CAD/CAM system processed file and converts intermediate code APT file to, the rearmounted machining code that is used for APT is converted to different NC system of handling, and, realize its freely changing each other at the numerical control program of different NC system;

Described process data generation module extracts the every content in the parts machining process rules, adds to then in the technology form, generates flow process chart, manufacturing procedure card, NC cutting tool card, clamping figure and part and sets card.

2. preparation system of quick numerical control machining of complex parts of airplane implementation method according to claim 1, it is characterized in that: concrete steps are as follows:

Step 1): enter " digital control processing " module of CAD/CAM system platform, and enter preparation system of quick numerical control machining of complex parts of airplane, be written into existing aircraft complex component part model;

Step 2): carry out the setting of part essential information, specifically have: the type of (1) part: comprise wallboard, frame, beam, rib, long purlin, joint and edge strip; (2) process side number: comprise single face, two-sided and multiaspect; (3) blank type: comprise sheet material, section bar, forging and foundry goods;

Step 3): the process characteristic in conjunction with part model carries out quality testing to part model, and revise accordingly not satisfying the local error structure that actual process requires, make part model satisfy the processing technology requirement, to guarantee to be input to the correctness of the part model in system's eight big modules;

Step 4): enter quick blank generation module, by step 2) in the part type set determine the blank type of this part, at first part model is carried out the analysis of blank process redundancy, then in conjunction with blank type and blank process redundancy, be aided with suitable man-machine interaction again, on the basis of part model, generate the blank model fast, form processing model by part model and blank model at last;

Step 5): enter the automated programming module, at first need according to step 2) in the part type set with process side information be for the corresponding machining coordinate of each process side setting, under each machining coordinate system, all manifold of part are carried out the identification of Noodles type then, and organize hole operation according to Noodles type recognition result, the identification and the structure that comprise countersunk, counter sink, taper hole, cylinder straight hole, deletion action is carried out in transverse holes and the oblique hole formed, with convenient follow-up feature identification; Under current machining coordinate is, employing is carried out machining feature identification based on the slot descriptor characteristic recognition method of layering thought to part, promptly creating layering aspect and part entity asks friendship and obtains out every layer intersection ring, extract the face that the sideline relies in the intersection ring then, by the annexation between the different sidelines in the intersection ring face that these sidelines rely on is made up again, and then form the slot descriptor feature, construct aircraft structure slot descriptor feature structure tree according to the incidence relation between the longitudinal surface again;

Step 6): after the feature identification in the step 5), man-machine interactively sets whether be written into existing similar part processing scheme, if selected "Yes" from the processing scheme storehouse processing scheme of coupling similar part automatically, show on system interface with tabular form, be optimized by man-machine interactively once more and choose; Otherwise enter part classification and process program analysis module, carry out knowledge reasoning according to technology experimental knowledge and part type, determine the basic processing scheme of current part, comprise that lathe information, process side information, overall process segment divide etc., divide according to part feature information and process segment again, automatically choose cutter, determine processing needed cutter parameters of different characteristic and cutting parameter in each process segment process, basic processing scheme and cutter are chosen the result merge, promptly generate the part processing scheme of recommending; After above-mentioned dual mode generation part processing scheme, enter processing scheme interactive modifying interface, the whole machining process of multiway tree structure representation part is adopted at this interface, this tree comprises part node, lathe node, process side node, operation node, work step node, program node, cutter node, manually processing scheme is carried out interactive modifying and inspection then, confirm at last to preserve; If be the part of first processing, its processing scheme adds in the processing scheme storehouse automatically, for calling of next similar part, guarantees the unitarity and the standardization of scheme;

Step 7): enter the automated programming module once more, at first from the processing scheme that step 6) generates, extract the tool-information that uses in each operation work step, and with the machining feature information of extracting in these cutters coupling step 5), it is related that machining feature and cutter are carried out, and guarantees that machining feature has suitable cutter to process in the different process segments; Then in conjunction with processing scheme, and the corresponding informance of feature and cutter, make up the machining cell of part, mainly contain:＜1 the roughing unit structure: adopt layering roughing thought, at first machining feature is optimized layering, obtains how much guidings of processing wire loop of each aspect then, and revise accordingly, connect in conjunction with bottom surface, end face, cutter parameters, cutting parameter, Processing Strategies parameter and processing transition more in addition, promptly finish the structure of roughing unit;＜2〉the sidewall finishing unit makes up: with reference to the roughing unit building mode, obtain how much guide wires of the accurately machined processing of machining feature, connect in conjunction with bottom surface, end face, cutter parameters, cutting parameter, Processing Strategies parameter and processing transition again, make up finishing unit; Set according to processing scheme at last, automatically in the CAM system, generate the process operation tree, wherein process operation is the set of a concrete machining cell information, comprising Processing Strategies parameter, machined parameters, geometric parameter, cutter parameters and the processing macro transition of processing current feature connects, again all process operations in the process operation tree are carried out the cutter rail and calculate and machining simulation, and in-problem cutter rail is revised;

Step 8) enters quick frock generation module, calculates clamping and the position location that current operation needs at first automatically, secondly extracts discrete cutting point from the cutter rail information that the automated programming module generates, and carries out the calculating of clamping force, anchorage force and cutting force; Enter into stress analysis and Deformation control module then, in this module according to clamped position, the position location, and act on these locational power, set up part processing process stress strain analysis model, carry out stress-strain analysis by Automatic Program, if deformation result does not meet the demands, then continue adjustment clamping point and anchor point and carry out the analysis of next scheme, up to the frock scheme that gets access to an optimization, then from the tool typical parts storehouse of process resource and knowledge base management module, call corresponding location and clamp device model in the tool standard part storehouse, and locate accordingly and install;

After step 9) frock three-dimensional model had generated, need judge whether needed to revise the cutter rail, if then need the tool setting rail to revise, prevented to produce interference with the frock model; If do not need, then enter step 10);

Step 10) enters the front and rear processing module, at first convert the processed file of CAM system to the APT intermediate code by the pre-process program, and then in conjunction with specific numerically-controlled machine code format, it is carried out semantic analysis and parsing, generate corresponding numerically-controlled machine code through post processing program, be saved in file; The lathe code that generates is carried out machining simulation, check whether to exist and cut or residual region, if it is then revise the cutter rail once more, entirely true up to the code that generates;

Step 11) enters the process data generation module at last, at first the Middleware Model that generates according to the automated programming module realizes generating the operation sketch by the middleware three-dimensional model automatically, and wherein the operation sketch comprises middleware projection sketch, machining coordinate system, local detail explanation and local size mark; Then according to content in the actual process list and form, and the processing scheme of automated programming module generation, extract the process data information in the processing scheme, process data information comprises that lathe, process side are to, operation, work step, program, cutter and frock, and its content and operation sketch added in the corresponding technology list automatically, and then the relevant card in the generating structure spare processing technology rules, comprise flow process chart, manufacturing procedure card, NC cutting tool card and clamping figure and part setting card.

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