CN110909417A - Multi-BOM construction and conversion method for testing and refitting stages in civil aircraft test flight - Google Patents
Multi-BOM construction and conversion method for testing and refitting stages in civil aircraft test flight Download PDFInfo
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Abstract
The invention belongs to the technical field of aviation flight tests and discloses a multi-BOM construction and conversion method for testing and refitting stages in civil aircraft test flight. The method is characterized in that a BOM view construction method is defined, and test flight elements in a test modification stage are defined and managed in a BOM structure mode; defining a test flight element object model by adopting an object-based idea; and the conversion from design BOM and process BOM to manufacture BOM and implementation BOM is realized by defining the relevant mapping relation. The method can be applied to building and converting the military and civil model test flight full life cycle BOM, and solves the difficult problems of multi-BOM building and view conversion in the test modification process.
Description
Technical Field
The invention belongs to the technical field of aviation flight test digitization, and particularly relates to a method for constructing and converting multiple BOMs (bill of material) in a test modification stage in civil aircraft test flight.
Background
The test flight test modification is an important part in the flight test process, and the improvement of the digitization level in the process can obviously improve the quality and the efficiency of the flight test. The test modification covers a series of links such as product design, process design, production and manufacture, implementation test and the like, is similar to the design and manufacture process of airplane development, has uniqueness of flight test, and comprises the steps that the product design takes test equipment and modification as a core; the process design mainly comprises an assembly process; the machine is erected instead of batches, and the state of each machine is different; shorter cycle requirements, etc.
Under the condition of the test and modification design of the current testing machine, the work of product design, process design, production preparation and the like is carried out dispersedly and serially, and the work is often redesigned when the problems are found in the on-machine implementation or ground test, so that the time consumption is long. Therefore, a full life cycle management (PLM) system needs to be modified through digital means and construction testing, so that the working quality and efficiency are improved. In the construction of a PLM system, according to the service characteristics of flight test modification, the following problems exist in the multi-BOM construction and conversion process:
1. the test modified equipment has the characteristics of both standard parts and designed parts, equipment is selected from an equipment library during each design, equipment with the same specification can be associated with different sub-part equipment at different periods, for example, a board card is associated with different collectors at different periods, and the coupling relation between the temporary equipment cannot be simply expressed by BOM.
2. Can be relevant material object information simultaneously (like principle drawing area equipment serial number) when current test repacking design, the design drawing has contained design information and material object information simultaneously promptly, has caused the information to obscure, and the work load is big during the design change, need design and material object information isolation to improve the flexibility that design and equipment chooseed for use.
Meanwhile, with the increasingly strict airworthiness examination and the objective requirement of product research and development refinement on real data, the number and complexity of test flight test modification tasks are greatly increased, so that how to accurately define the BOM structure and test flight elements of multiple links of test modification, how to realize the conversion from BOM design and process BOM to BOM manufacturing and BOM implementation, so that a large number of test flight test modification tasks can be safely and efficiently completed within a limited time period and personnel cost investment by using a digital means, and the problem which needs to be solved at present becomes urgent.
Disclosure of Invention
The purpose of the invention is as follows: a BOM structure and a test flight element definition method are provided, BOM view construction of multiple links in a test flight test modification stage is achieved, and conversion from design BOM and process BOM to manufacture BOM and implementation BOM is achieved through defining relevant mapping relations. The method has the advantages of meeting the requirements of test modification full life cycle digital management, improving the test modification working efficiency and quality, enhancing the test modification working reliability and maintainability, providing the work expression and output capacity with strong exhibitiveness, and meeting the relevant requirements of airworthiness approval on the test modification work.
The technical scheme of the invention is as follows:
the English abbreviations referred to in the present invention are defined as follows:
BOM is bill of materials;
EBOM is a design bill of materials;
MBOM is a manufacturing bill of materials;
PLM is full lifecycle management;
CI is a configuration item;
DS is a design module;
the ATA100 specification is a specification commonly specified by the american air transportation association and aviation manufacturers for unifying civil aircraft product numbers.
The technical scheme of the invention mainly comprises two aspects of a test modified BOM structure construction method and test modified design BOM to physical BOM conversion content.
First, as shown in fig. 1, the modified BOM structure construction was tested. The test flight test refitting management is designed based on a CI-DS mode, namely, test refitting system design, process design and implementation are carried out corresponding to one airplane model, and different airplanes are distinguished and filtered according to DS effectiveness. And (3) building a test modification system design and process according to ATA chapters/sections, implementing a top-level structure of BOM, and further developing a specific test modification system design. The device can be divided into a mechanical part and an electrical part according to the profession. The mechanical design is performed on three-dimensional design software (e.g., CATIA). The electrical design can be divided into a circuit design, a two-dimensional harness design and a three-dimensional harness design, the former two being executed on electrical design software (such as Capital), the latter being executed in three-dimensional design software (such as CATIA). And storing the mechanical design and three-dimensional wiring harness design results in a PLM system for management by constructing a BOM structure.
The test retrofit design mainly contains the following pages:
1) designing an input label: managing the total retrofit specifications for the entered project.
2) Modifying a design label: and the system automatically collects all the configuration item sub-schemes according to the template to generate a total modification scheme.
3) Manufacturing a compliance check label: various manufacturing compliance lists, configuration lists, material lists, etc. of the mechanical and electrical professions required by the airworthiness management department are managed. And generating according to a template or generating by self-defining according to needs.
4) Test design label: managing ground test records, ground test reports, aerial test records and aerial test reports.
Including documentation and parameterized data, including elements of time, place, personnel, test results, and the like.
The following data sheet record design module (DS) information is created:
1) the life cycle state comprises work, audit, issued and abandoned;
2) the type attributes comprise names, codes, machine types, frame machine numbers, electric wire harness numbers, risk levels, topic codes, recommended items, test schemes and modification technical requirement IDs;
3) data set type, three-dimensional digifax, lightweight digifax;
4) the method comprises the following steps of relation type, context environment, associated process, associated work card, associated coordination, associated two-dimensional drawing, associated electrical design file, associated modification technical requirement and associated modification scheme;
5) the authority defines the read, write, delete and change authority;
6) and (5) carrying out related processes.
Second, as shown in FIG. 2, the conversion of the modified design BOM to a physical BOM is tested.
For the same test equipment, the attention points of the test design and the modified mechanical design are different, the test design is more focused on the weight, the size, the current power consumption and other attributes of the equipment, and the modified mechanical design is more focused on the three-dimensional digital-analog and installation requirements and other characteristics of the equipment, so that the part numbers, the attributes and other description information of the test design and the modified mechanical design are different. The part number code of the test design is related to example information of equipment such as a rack machine, an installation position and the like, and the equipment with the same model has different numbers under different use conditions; part number coding of the modified mechanical design is related to the model (three-dimensional digital-analog) of the testing equipment, and is unrelated to equipment instance information such as a frame machine and an installation position, and the equipment with the same model has the same number under different use conditions.
At the time of test design, the device instance object usage is derived from the device model objects in the test device library by the "part (design state) -part (physical state)" schema.
When the machine is refitted, the device model and the device digital-analog object related to the device model are found through the device example, the device digital-analog object is directly used in the refitted design BOM, and the device digital-analog example is set in three-dimensional design software (CATIA) as the ID of the device example. And the device digital-analog object is associated with the model and is uniformly maintained and managed in the test device library.
When the modified machine is implemented, the device example is found through the model attribute of the device digifax, the related physical part object (the device physical object is predefined) is found through the device example, and the physical part object is directly used in the modified and implemented BOM. And the physical part objects are generated and associated from the equipment modules according to the maintenance structure, and are uniformly maintained and managed in the test equipment library.
Designing BOM and material object processing, wherein the basic processing process is as follows:
1. and the specification of the test equipment is isolated from the actually selected equipment. The method comprises the steps of distinguishing by using a 'part (design state) -part (physical state)' mode, selecting the test equipment specification (design state) from an equipment classification library by using the test equipment specification as a keyword ID for the part (design state), automatically converting the part (design state) into the physical state of a test equipment example by a system and associating the test equipment example with the design, and associating different equipment sub-pieces (physical states) by using the test equipment example (physical states), thereby solving the problem that the equipment is associated with different sub-piece equipment at different periods.
2. The test equipment example (physical state) part number is designed in the existing coding mode of the test system, and the part (physical state) is simultaneously related to the related information of the part (design state) so as to be convenient for viewing related design drawings.
3. The retrofit design uses an equipment model of the test equipment, the equipment model being associated with the equipment model.
4. And generating and associating the test equipment real objects by the modified digital analogy, and uniformly maintaining the test equipment real objects through the test equipment library. The serial number and the manufacturer ID of the test equipment real object are recorded in the attribute of the real object, the real object ID is the equipment digital-analog ID, the real serial number and the manufacturer ID, and for a plurality of real test equipment with the same specification and model, a plurality of real objects are associated.
5. Physically related content (e.g., a certificate, contract, etc.) is associated with the physical object; the content related to the equipment model is associated with the part (design state) or recorded according to the attribute of the design state; instance-related content (e.g., device software) is associated with the part (physical state).
The test equipment used:
1. when the test system is manually designed: when the part (object state) examples are derived from the parts (design states) in the library, all equipment objects are displayed in a list form for selection by a user (the test equipment objects are predefined), the system automatically generates the equipment examples after the equipment examples are determined, and the equipment examples are associated with the selected equipment objects for subsequent modification. When the test system is designed by tool software: part (real object state) examples are automatically derived from parts (design states) in a library through system integration, and because real object predefinition is not executed during current tool software design, the real objects need to be manually predefined subsequently, and the real objects are associated with the equipment examples.
2. When the modified real object is synchronously generated and updated through the equipment library data, the system automatically generates physical parts of all the equipment, and the subsequent test design real object is selected when predefined.
3. When the test object is changed (with the same model), related equipment objects can be searched according to the equipment model, a new equipment object is selected, and the change record is recorded
4. When the model of the equipment is changed (different specifications and models), the test system is modified to design the BOM, then the equipment physical part is selected for the part (physical state) of the equipment with the new specification and model, and the test equipment physical part is replaced on the modified BOM.
The specific scheme is as follows: a method for constructing and converting multiple BOMs in test modification stages in civil aircraft test flight comprises the steps of constructing a BOM view, and defining and managing test flight elements in the test modification stages in a BOM structure mode; defining a test flight element object model by adopting an object-based idea; the conversion from the EBOM to the MBOM is realized by defining a correlation mapping relation.
Preferably, the constructing the BOM view includes a step of constructing a test modified BOM, and the specific process includes: the testing and modifying design of different aircraft erection machines of the same model airplane controls the effectiveness of the aircraft erection machines through a CI-DS mode by adopting a mode of single BOM of a single model airplane, an effectiveness object is associated with a root node of the BOM, and the testing and modifying BOM is divided into a top layer structure and a bottom layer structure.
Preferably, the top level structure is divided into EBOM and MBOM, wherein the EBOM is a test-oriented retrofit design, organized as airplane sections and ATA chapter sections specified in the ATA100 specification; meanwhile, the top-level structure also comprises an overall node, which manages various general input, process and output files of the test modification design, modification schemes, weighing records, test records, level measurement records and description documents; and the MBOM is organized according to the regional sections of the airplane and is sent to a system service manager after the MBOM top layer structure is built, and a modified and implemented BOM top layer structure is generated uniformly.
Preferably, the ATA100 specification, wherein chapter ATA85 is a proprietary test system, chapter ATA87 is an onboard test system, and chapter others manage the three-dimensional data model of the aircraft body.
Preferably, the substructure is constructed in a CI-DS model, where CI is a configuration item and DS is a specific retrofit design module.
Preferably, the DS is used as a basic unit for testing the refitting design, the validity of the rack is controlled, various design files are related, the DS can be divided into a mechanical design DS and an electrical design DS according to the profession, and the mechanical assembly design and the electrical three-dimensional wiring harness design are completed under the three-dimensional design software integration environment.
The test retrofit BOM conversion comprises:
a) isolating the test equipment specification from the actually selected equipment;
b) the part number of the test equipment instance real object state is designed in the existing coding mode by the test system, and the real object state of the part is simultaneously related to the related information of the design state of the part so as to be convenient for checking related design patterns;
c) the method comprises the steps that an equipment digital model of the test equipment is used in a modified design, and the equipment digital model is associated with an equipment model;
d) the method comprises the steps that a test device real object is generated and associated through a modified digital model, the test device real object is maintained uniformly through a test device library, the serial number and the manufacturer ID of the test device real object are recorded in the attribute of the real object, the real object ID is the device digital model ID, the real serial number and the manufacturer ID, and for a plurality of real test devices of the same specification and model, a plurality of real objects are associated;
e) the physically related content is associated with the physical object; the content related to the equipment model is associated with the design state of the part or recorded according to the attribute of the design state; instance-related content is associated with the physical state of the part.
Preferably, the process of step a) is distinguished by using a mode of "design state of part-real object state of part", the design state of part takes test equipment specification as a keyword ID, the design state of test equipment specification is selected from an equipment classification library when a test system is designed, the system automatically converts the design state of part into the real object state of test equipment example and associates the design, the real object state of test equipment example associates the real object state of different equipment sub-parts, thereby solving the problem that equipment associates different sub-part equipment at different periods.
The invention has the advantages that:
the invention provides a BOM structure which is easy to realize by a computer and a method for defining test flight elements, which are fit for the actual service situation of the modified stage of the civil aircraft test flight test, realizes the construction of BOM views of a plurality of links in the modified stage of the test flight test and meets the requirement of the management of the civil aircraft test flight configuration. A method for converting a design BOM and a process BOM to a manufacturing BOM and an implementation BOM is defined. The problem of conversion of test equipment from test design BOM to modified design BOM and modified object BOM is solved. The method is based on the concept of the object, is beneficial to the realization of the PLM system, meets the digital management of the whole life cycle of the test modification, improves the working efficiency and quality of the test modification, enhances the working reliability and maintainability of the test modification, and meets the relevant requirements of airworthiness certification on the test modification.
Drawings
Fig. 1 is a schematic diagram of construction of modified BOM for civil aircraft test flight.
FIG. 2 is a schematic diagram of a conversion from a test retrofit design BOM to a physical BOM.
FIG. 3 is a schematic diagram of construction and conversion of modified multi-BOM for civil aircraft test flight.
Detailed Description
As shown in fig. 3, by applying the method, the construction and conversion of multiple BOMs in the modification stage of the test flight test of a certain civil aircraft model are realized.
1. Test retrofit design BOM
The testing and modifying design of different aircraft erection machines of the same model airplane controls the effectiveness of the airplane erection machine through a CI-DS mode by adopting a single BOM mode of a single model airplane. The validity object is associated with a BOM root node. The test retrofit design BOM is divided into a top layer structure and a bottom layer structure.
a) Top layer structure
Can be divided into EBOM and MBOM. The EBOM is mainly designed for test modification, is organized according to airplane sections and ATA section sections, and manages a three-dimensional data model of an airplane body in other sections except that ATA85 is a special test system and ATA87 is an airborne test system. Meanwhile, the top layer also comprises an overall node, which manages various general input, process and output files of the test modification design, modification schemes, weighing records, test records, level measurement records, description documents and the like; the MBOM is mainly oriented to physical management, organized according to airplane region sections, and sent to a system service manager after the MBOM top layer structure is built, so that a modified and implemented BOM top layer structure is generated uniformly.
b) Bottom layer structure
Constructed in CI-DS mode. CI is a configuration item, DS is a specific modification design scheme, and the modification design scheme is used as a basic unit module for testing modification design, controlling the efficiency of the machine frame and associating various design files. The method can be divided into a mechanical design DS and an electrical design DS according to the profession, and the mechanical assembly design and the electrical three-dimensional wiring harness design are completed under the three-dimensional design software integration environment.
2. Testing retrofit context co-design
The design process object is managed in a separate assembly structure and is independent of the design BOM, and the main description is the assembly relation between the test modification design scheme DS and the airplane body and the coordination digital-analog.
3. Retrofit process design
And establishing data models such as a modification process, a modification procedure and a modification step and corresponding attributes such as working content, working hour and remarks of the data models, using the data models as basic objects of the modification process structure, and constructing the modification process data structure in three modes of template automation, manual operation and integrated import. The top layer of the process structure is similar to the test retrofit design, organized in field sections and ATA chapters, and the bottom layer uses the retrofit process of design scheme DS as the basic unit. And a three-dimensional visual work card can be automatically generated on the basis of the refitting process, and a digital prototype of the object in the design scheme is embedded. The process specification is associated with a process template.
4. Modified implementation data structure
And constructing a modified and implemented BOM data structure by taking a physical part data model of the system as a basic object. The top layer structure is generated from an MBOM top layer structure, the top layer structure is only used for realizing BOM organization management, and no physical object exists in reality, so that no physical serial number or manufacturer ID exists in an object; the bottom layer structure is generated from an MBOM (modified design module/DS layer) and installed under the top layer structure when the bottom layer structure is installed for the first time, and the bottom layer structure and the object are updated when the bottom layer structure is subsequently detached/installed/maintained for the first time. And recording information such as a modified real work card, a modified real work state, a historical dismounting record, a use record, a fault maintenance record and the like on the real object.
Claims (8)
1. A multi-BOM construction and conversion method for testing and modifying stages in civil aircraft test flight is characterized in that a BOM view is constructed, and test and modifying stage test flight elements are defined and managed in a BOM structure mode; defining a test flight element object model by adopting an object-based idea; the conversion from the EBOM to the MBOM is realized by defining a correlation mapping relation.
2. The civil aircraft test flight process testing machine test modification multi-BOM construction and conversion method according to claim 1, wherein the construction of the BOM view comprises a test modification BOM construction step, and the specific process is as follows: the testing and modifying design of different aircraft erection machines of the same model airplane controls the effectiveness of the aircraft erection machines through a CI-DS mode by adopting a mode of single BOM of a single model airplane, an effectiveness object is associated with a root node of the BOM, and the testing and modifying BOM is divided into a top layer structure and a bottom layer structure.
3. The civil aircraft test flight procedure testing machine test modification multi-BOM construction and conversion method as claimed in claim 2, wherein the top layer structure is divided into EBOM and MBOM, wherein EBOM is designed for test modification and organized according to aircraft section and ATA section specified in ATA100 specification; meanwhile, the top-level structure also comprises an overall node, which manages various general input, process and output files of the test modification design, modification schemes, weighing records, test records, level measurement records and description documents; and the MBOM is organized according to the regional sections of the airplane and is sent to a system service manager after the MBOM top layer structure is built, and a modified and implemented BOM top layer structure is generated uniformly.
4. The civil aircraft test flight procedure tester test refitting multi-BOM construction and conversion method according to claim 3, wherein the ATA100 specification is a specification commonly specified by the american air transportation association and aviation manufacturers for unifying civil aircraft product numbers, wherein the chapter ATA85 is a dedicated test system, the chapter ATA87 is an onboard test system, and a three-dimensional data model of an aircraft body is managed under other chapters.
5. The civil aircraft test flight procedure testing machine test refitting multi-BOM construction and conversion method as claimed in claim 2, wherein the bottom layer structure is constructed in a CI-DS mode, wherein CI is a configuration item and DS is a specific refitting design module.
6. The test modification multi-BOM construction and conversion method of the civil aircraft test flight process testing machine according to claim 5, wherein DS is used as a basic unit for test modification design, the machine erection effectiveness is controlled, various design files are related, mechanical design DS and electrical design DS can be divided into according to professions, and mechanical assembly design and electrical three-dimensional wiring harness design are completed in a three-dimensional design software integration environment.
7. The civil aircraft test flight procedure testing machine test retrofit multi-BOM construction and conversion method of claim 1, wherein the test retrofit BOM conversion comprises:
a) isolating the test equipment specification from the actually selected equipment;
b) the part number of the test equipment instance real object state is designed in the existing coding mode by the test system, and the real object state of the part is simultaneously related to the related information of the design state of the part so as to be convenient for checking related design patterns;
c) the method comprises the steps that an equipment digital model of the test equipment is used in a modified design, and the equipment digital model is associated with an equipment model;
d) the method comprises the steps that a test device real object is generated and associated through a modified digital model, the test device real object is maintained uniformly through a test device library, the serial number and the manufacturer ID of the test device real object are recorded in the attribute of the real object, the real object ID is the device digital model ID, the real serial number and the manufacturer ID, and for a plurality of real test devices of the same specification and model, a plurality of real objects are associated;
e) the physically related content is associated with the physical object; the content related to the equipment model is associated with the design state of the part or recorded according to the attribute of the design state; instance-related content is associated with the physical state of the part.
8. The civil aircraft test flight process testing machine testing refitting multi-BOM construction and conversion method as claimed in claim 7, wherein the process of the step a) is distinguished by using a mode of 'design state of part-physical state of part', the design state of part takes the test equipment specification as a keyword ID, the design state of test equipment specification is selected from an equipment classification library when a test system is designed, the system automatically converts the design state of part into physical state of test equipment example and associates the design, and the physical state of test equipment example is associated with physical state of different equipment sub-pieces, so that the problem that equipment is associated with different sub-piece equipment at different periods is solved.
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