Aircraft engineering change unit division method and device

Abstract

The invention provides an aircraft engineering change unit division method and device, and belongs to the technical field of aircraft configuration management, and the method comprises the steps: obtaining an aircraft top map, and splitting the large-scale aircraft top map to obtain a plurality of engineering change units; according to the aircraft technical state base line, generating a product structure tree from the components in the aircraft top map needing to be split; all nodes on the product structure tree are counted, the sum of the number of the current node and the number of all components under the current node serves as the count of the current node, and the count value of each node is obtained; traversing the product structure tree by taking a root node of the product structure tree as a starting point, and when a count value of the node is greater than a threshold value, marking the current node with a first identifier; when the count value of the node is smaller than the threshold value, marking the current node as a second identifier; and storing all the nodes with the first identifier and the second identifier as engineering change units, and completing division of the aircraft engineering change units.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft configuration management, and in particular, relates to a method and device for dividing aircraft engineering change units. Background Art

[0002] As one of the core modules of the aircraft collaborative development platform (DCE), the aircraft engineering change management functional module has established an engineering change process system of "change impact analysis - engineering change request (ECP) - engineering change execution (ECN)", and gradually expanded scenarios such as parallel changes, cross-state changes, and cross-model changes, supporting engineering changes of various data such as secondary prototypes, tertiary prototypes, test pieces, iron birds, air platforms, and air tests of a certain model series of aircraft.

[0003] At present, the engineering change management function of the DCE platform cannot fully meet the application requirements of designers, mainly manifested in the low efficiency of change impact analysis. After analysis, the reasons for this problem are: the aircraft technical status managed in the DCE platform has increased rapidly; the DCE platform supports more than 300 detailed engineering change scenarios. During the change impact analysis process, it is necessary to judge whether the change scenario is within the support range, and analyze the impact of the ongoing engineering change process on the change; in addition, the excessive division of the top view of a certain model series of aircraft is also an important reason for the low efficiency of change impact analysis. The statistical results of the larger top view are shown in Table 1. According to the experience of other models, limiting the number of components in the top view to less than 200 during the top view division process is conducive to engineering change and technical status management. The top view with more than 200 components is a larger top view.

[0004] Table 1 Statistical results of the larger top graph

[0005]

[0006]

[0007] Unreasonable top-drawing division is one of the main reasons for the low efficiency of engineering changes in a certain model series of aircraft. Therefore, to improve the efficiency of engineering changes, it is necessary to split the larger top-drawing to form engineering change units of appropriate size (the total number of components in the engineering change unit is controlled within 200). The development process of a certain model series of aircraft mainly involves multiple units. Splitting the top-drawing requires a lot of work such as redefining the product structure, reorganizing historical data, reorganizing the baseline, and reissuing data. At the same time, the contracting unit needs to modify a large number of process documents.

[0008] In order to meet the model application, it is necessary to optimize and improve the engineering change control system, expand the parallel change support scenarios, cross-state change support scenarios, and finally realize modular changes. The evolution of the engineering change control system of a certain model series aircraft has gone through the following stages:

[0009] a. Initial construction of a "parts-centric" engineering change system: using parts and change orders as inputs to conduct component change impact analysis, initially constructing ECP-ECN engineering change process control, EO creation, post-change data review and baseline solidification, and other functions;

[0010] b. Parallel scenario expansion of multiple engineering change processes for the same module: The change process of multiple changes of the same module has been transformed from serial to parallel, and the support of scenarios such as parallel changes of components at different levels, parallel changes of components at different batches, and parallel changes of components at the same level has been realized. The model dynamic reorganization technology has been used to ensure the correctness of the assembly model after the change;

[0011] c. Multi-state changes of the same component: a change process can be initiated for multiple states of the same component at the same time. Engineering changes will generate multiple small versions, and multiple versions will be solidified according to the batch;

[0012] d. Expansion of multi-model change management functions: top-picture borrowing, cancellation of borrowing, simultaneous change of multiple models, cross-model version change, number change (change of structure model and model code), etc.;

[0013] e. Reconstruction of the engineering change system centered on "engineering change units": Introduce the concept of engineering change units, divide the larger top plan into multiple smaller engineering change units, and use the engineering change unit as the smallest unit of engineering change management to improve the efficiency of engineering changes. At the same time, change the bottom-up "change impact analysis" to the top-down "change planning". Summary of the invention

[0014] The purpose of the present application is to provide a method and device for dividing aircraft engineering modification units to solve or alleviate at least one problem in the background technology.

[0015] The technical solution of the present application is: a method for dividing aircraft engineering change units, comprising:

[0016] Acquire an aircraft top view, and when the scale of the aircraft top view reaches a predetermined scale, split the aircraft top view to obtain a plurality of engineering change units;

[0017] Generate a product structure tree for the components in the aircraft top view that need to be split according to the aircraft technical status baseline;

[0018] Count all nodes on the product structure tree, take the sum of the number of the current node and all components under the current node as the count of the current node, and obtain the count value of each node;

[0019] Taking the root node of the product structure tree corresponding to the airplane top image as the starting point, traverse the product structure tree. When the count value of the node is greater than the threshold, mark the current node with the first identifier and continue to traverse to the next level of nodes; when the count value of the node is less than the threshold, mark the current node with the second identifier and stop traversing to the next level.

[0020] All nodes having the first identifier and the second identifier are saved as engineering change units, the top view and technical status information of the engineering change unit are obtained, and the division of the aircraft engineering change unit is completed.

[0021] Preferably, the predetermined scale refers to an aircraft top view with 200 or more components.

[0022] Preferably, when marking the current node, the first identifier and the second identifier are identifiers of different colors or digital identifiers of different states.

[0023] Preferably, the top diagram and technical status information of the engineering change unit obtained include the top diagram number, version, baseline number, baseline name, parent node number, engineering change unit number, type of engineering change unit, and time of generating the engineering change unit.

[0024] In a second aspect, the present application provides an aircraft engineering change unit division device, comprising:

[0025] A top view acquisition module is used to acquire an aircraft top view, and when the scale of the aircraft top view reaches a predetermined scale, the aircraft top view is split to obtain a plurality of engineering change units;

[0026] The product tree module is used to generate a product structure tree for the components in the aircraft top view that need to be split according to the aircraft technical status baseline;

[0027] The node counting module is used to count all nodes on the product structure tree, taking the sum of the number of the current node and all the components under the current node as the count of the current node, and obtaining the count value of each node;

[0028] A marking module is used to traverse the product structure tree starting from the root node of the product structure tree corresponding to the airplane top image. When the count value of the node is greater than the threshold, the current node is marked with the first identifier and the traversal to the next level node is continued; when the count value of the node is less than the threshold, the current node is marked with the second identifier and the traversal to the next level is stopped;

[0029] The storage module is used to save all nodes with the first identifier and the second identifier as engineering change units, obtain the top view and technical status information of the engineering change unit, and complete the division of the aircraft engineering change unit.

[0030] Preferably, the predetermined scale refers to an aircraft top view with 200 or more components.

[0031] Preferably, when marking the current node, the first identifier and the second identifier are identifiers of different colors or digital identifiers of different states.

[0032] Preferably, the top diagram and technical status information of the engineering change unit obtained include the top diagram number, version, baseline number, baseline name, parent node number, engineering change unit number, type of engineering change unit, and time of generating the engineering change unit.

[0033] In a third aspect, the present application provides an electronic device, including:

[0034] one or more processors;

[0035] Memory;

[0036] One or more application programs are stored in the memory and configured to be executed by the one or more processors, and the one or more application programs are configured to implement the aircraft engineering change unit division method as described in any one of the above items.

[0037] In a fourth aspect, the present application provides a computer storage medium, wherein the computer storage medium stores at least one instruction, at least one program, a code set or an instruction set, wherein the at least one instruction, the at least one program, the code set or the instruction set is loaded and executed by a processor to implement the aircraft engineering change unit division method as described in any one of the above items.

[0038] The engineering change unit division method of the present application introduces the concept of engineering change units, divides a larger aircraft top view into multiple smaller engineering change units, and uses the engineering change unit as the smallest unit of engineering change management, thereby changing the existing engineering change impact analysis model, taking into account the improvement of engineering change efficiency while taking into account the existing technical status management system, thereby simplifying technical status management. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0040] Figure 1 This is a schematic diagram of the aircraft engineering modification unit division method of the present application.

[0041] Figure 2 This is a schematic diagram of an airplane top view product tree according to an embodiment of the present application.

[0042] Figure 3 This is a schematic diagram of the aircraft engineering modification unit division device of the present application.

[0043] Figure 4 A schematic diagram of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0045] In order to overcome the problems raised by the background art, the present application proposes a method and device for dividing aircraft engineering modification units.

[0046] like Figure 1 As shown, the aircraft engineering change unit division method provided by the present application includes the following process:

[0047] Step S10, obtain the aircraft top view, determine the scale of the aircraft top view, when the scale of the aircraft top view reaches a predetermined scale, split the aircraft top view of the predetermined scale, maintain the existing top view division and product structure unchanged during the split, and divide the larger top view into multiple logical units, which is the engineering change unit. The engineering change unit is the smallest unit of engineering change management and the only unit for initiating engineering changes. All engineering change plans must be completed with the engineering change unit as the node to improve the efficiency of engineering changes.

[0048] In this application, a larger-scale top drawing refers to a top drawing with 200 or more components.

[0049] Step S20, generating a product structure tree for the components in the aircraft top view that need to be disassembled according to the aircraft technical status baseline.

[0050] Step 30: Count all nodes on the product structure tree, take the sum of the number of the current node and all components under the current node as the count of the current node, and obtain the count value of each node.

[0051] like Figure 2The product structure tree of the component that needs to be divided in the larger-scale top diagram in this embodiment of the present application is shown. There are 19 nodes A to S in the product structure tree. Node A is the root node, and its count is 19. The child nodes of node A are nodes B to E, and their counts are 5, 6, 1, and 6 respectively. Since the count of node B is not 1, it has child nodes. The child nodes of node B are nodes F to G, and their counts are 3 and 1 respectively. The count of node F is still not 1, and it has child nodes. The child nodes of node F are L to M, and their counts are 1 and 1 respectively. The counts of the remaining nodes and their child nodes are not repeated.

[0052] Step S40: Starting from the root node of the product structure tree corresponding to the airplane top image, traverse the product structure tree. When the node count value is greater than the threshold, mark the current node with the first identifier and continue to traverse to the next level of nodes; when the node count is less than the threshold, mark the current node with the second identifier and stop traversing to the next level.

[0053] In the present application, the above threshold is the number of components 200 defined in the larger-scale top diagram definition.

[0054] For the convenience of explanation, the accompanying drawings of this embodiment are described with a threshold value of 4. That is, in the above embodiment, the count of node A is greater than 4, and it is marked as the first mark, the counts of node B, node C, and node E are all greater than 4, and are also marked as the first mark, and the counts of the child nodes and the child nodes of the child nodes of node B, node C, and node E are not greater than 4, so they are marked as the second mark.

[0055] In some embodiments of the present application, the first identifier and the second identifier may be identifiers of different colors, for example, the first identifier is red and the second identifier is green. The first identifier and the second identifier may also be numbers or identifiers of different states, for example, the first identifier is 1 and the second identifier is 0.

[0056] Step S50: All nodes with the first identifier and the second identifier are saved and stored as engineering change units, and information such as the top diagram and technical status are recorded, including: top diagram number, version, baseline number, baseline name, parent node number, engineering change unit number, type of engineering change unit (i.e., the first identifier or the second identifier), time of generating the engineering change unit, etc.

[0057] After the above division process, the engineering change unit with the first identifier indicates that the branch node can be added or deleted, which represents an assembly in practical applications; the engineering change unit with the second identifier indicates that the node and its branch nodes can be changed, which represents a part or assembly in practical applications.

[0058] The engineering change unit division method of the present application introduces the concept of engineering change units, divides a larger aircraft top view into multiple smaller engineering change units, and uses the engineering change unit as the smallest unit of engineering change management, thereby changing the existing engineering change impact analysis model, taking into account the improvement of engineering change efficiency while taking into account the existing technical status management system, thereby simplifying technical status management.

[0059] like Figure 3 As shown, based on the above, the present application also provides an aircraft engineering change unit division device 100, the device 100 comprising:

[0060] A top view acquisition module 101 is used to acquire an aircraft top view, and when the scale of the aircraft top view reaches a predetermined scale, the aircraft top view is split to obtain a plurality of engineering change units;

[0061] The product tree module 102 is used to generate a product structure tree for the components in the aircraft top view that need to be split according to the aircraft technical status baseline;

[0062] The node counting module 103 is used to count all nodes on the product structure tree, taking the sum of the number of the current node and all components under the current node as the count of the current node, and obtaining the count value of each node;

[0063] The marking module 104 is used to traverse the product structure tree starting from the root node of the product structure tree corresponding to the airplane top image. When the count value of the node is greater than the threshold, the current node is marked with the first identifier and the traversal to the next level node is continued; when the count value of the node is less than the threshold, the current node is marked with the second identifier and the traversal to the next level is stopped;

[0064] The storage module 105 is used to save all nodes with the first identifier and the second identifier as engineering change units, obtain the top view and technical status information of the engineering change unit, and complete the division of the aircraft engineering change unit.

[0065] For the specific division steps of the aircraft engineering change unit division device of the present application, reference may be made to the aircraft engineering change unit division method of the present application, which will not be repeated here.

[0066] When initiating an engineering change using the engineering change unit division method of the present application, it is necessary to complete the initialization of the engineering change unit, and the initialization includes initialization of the existing aircraft top map and initialization of the newly added aircraft top map;

[0067] Among them, the initialization of the existing top chart includes: uniformly traversing the numbers of the existing top charts one by one; for a top chart with a certain number, dividing the top chart execution engineering change unit according to different technical states, and logically splitting the aircraft top chart into engineering change units; recording the relevant information of the engineering change unit, including: top chart number, version, baseline number, baseline name, parent node number, engineering change unit number, engineering change unit type (engineering change unit marked in red or green), time of generating the engineering change unit, etc.;

[0068] The initialization of the newly added top view includes: while the newly added top view review process is executing the baseline solidification, the newly added aircraft top view is logically split into engineering change units, and the relevant information corresponding to the engineering change units is recorded.

[0069] After completing the division of engineering change units using the engineering change unit division method of the present application, it is necessary to update the engineering change units, including: engineering changes will cause changes in technical status and product structure, the technical status baseline is split, and the scale of the components under assembly changes, which will cause the engineering change units under the aircraft top view to become invalid. Therefore, after each engineering change is completed, the engineering change unit of the relevant top view is updated once, that is, the top view is logically split again according to the technical status within the scope of the change, and a new mapping relationship between the engineering change unit, top view and technical status baseline is formed and recorded.

[0070] The use of engineering change units is the basis for initiating engineering changes. Its application scenarios mainly include the following aspects:

[0071] 1) The engineering change planning function uses the engineering change unit as the root node to expand the product structure tree and carry out component planning. Specifically:

[0072] The designer enters the top drawing number to be changed, and the Digital Collaboration Environment (DCE) platform displays a list of engineering change units (including the first and second identifiers). The designer further selects the engineering change unit and enters the effective batch information of this change, and adds it to the change plan execution area. The system will display the product structure under different technical conditions in descending order of the change batch;

[0073] 2) The engineering change unit is the smallest unit for parallel change control, that is, different engineering change units are allowed to be changed in parallel, but different technical statuses of the same engineering change unit are not allowed to initiate parallel changes. The DCE platform supports multiple engineering change unit change scenarios, that is, the same change planning process can realize the change planning of multiple engineering change units in a certain flight. The engineering change unit is also suitable for multiple flight change scenarios. A certain engineering change unit has the same technical status within a certain flight range, and the same change planning process can realize the planning of multiple independent technical statuses for multiple flight intervals.

[0074] like Figure 4 As shown, an embodiment of the present application also provides an electronic device 200, which includes a processing device 201, which can perform various appropriate actions and processes according to a program stored in a ROM (read-only memory) 202 or a program loaded from a storage device 208 to a RAM (random access memory) 203. The processing device 201 may include, for example, a general-purpose microprocessor (such as a CPU), an instruction set processor and / or a related chipset and / or a special-purpose microprocessor (for example, an application-specific integrated circuit (ASIC)), etc. The processing device 201 may also include an onboard memory for caching purposes. The processing device 201 may include a single processing unit or multiple processing units for performing different actions of the method flow according to an embodiment of the present disclosure.

[0075] In RAM 203, various programs and data required for the operation of electronic device 200 are stored. Processing device 201, ROM 202 and RAM 203 are connected to each other via bus 204. Processing device 201 performs various operations of the method flow according to the embodiment of the present application by executing the program in ROM 202 and / or RAM 203. It should be noted that the program can also be stored in one or more memories other than ROM 202 and RAM 203. Processing device 201 can also perform various operations of the method or flow according to the embodiment of the application by executing the program stored in the one or more memories.

[0076] According to an embodiment of the present application, the electronic device 200 may further include an I / O interface 205 (input / output interface), which is also connected to the bus 204. The electronic device 200 may further include one or more of the following components connected to the I / O interface 205: an input device 206 including a keyboard, a mouse, etc.; an output device 207 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage device 208 including a hard disk, etc.; and a communication device 209 including a network interface card such as a LAN card, a modem, etc. The communication device 209 performs communication processing via a network such as the Internet. A drive is also connected to the I / O interface 205 as needed. Removable media, such as magnetic disks, optical disks, magneto-optical disks, semiconductor memories, etc., are installed on the drive as needed so that the computer program read therefrom is installed into the storage device 208 as needed.

[0077] The present application also provides a computer-readable storage medium, which may be included in the device / apparatus / system described in the above embodiments; or may exist independently without being assembled into the device / apparatus / system. The above computer-readable storage medium carries one or more programs, and when the above one or more programs are executed, various operations of the above methods or processes according to the embodiments of the present application are implemented.

[0078] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for dividing aircraft engineering change units, characterized in that: include: Acquire an aircraft top view, and when the scale of the aircraft top view reaches a predetermined scale, split the aircraft top view to obtain a plurality of engineering change units; Generate a product structure tree for the components in the aircraft top view that need to be split according to the aircraft technical status baseline; Count all nodes on the product structure tree, take the sum of the number of the current node and all components under the current node as the count of the current node, and obtain the count value of each node; Taking the root node of the product structure tree corresponding to the airplane top image as the starting point, traverse the product structure tree. When the count value of the node is greater than the threshold, mark the current node with the first identifier and continue to traverse to the next level of nodes; when the count value of the node is less than the threshold, mark the current node with the second identifier and stop traversing to the next level. All nodes having the first identifier and the second identifier are saved as engineering change units, the top view and technical status information of the engineering change unit are obtained, and the division of the aircraft engineering change unit is completed.

2. The aircraft engineering change unit division method according to claim 1, characterized in that: The predetermined scale refers to an aircraft top view with 200 or more components.

3. The aircraft engineering change unit division method according to claim 1, characterized in that: When marking the current node, the first identifier and the second identifier are identifiers of different colors or digital identifiers of different states.

4. The aircraft engineering change unit division method according to claim 1, characterized in that: The top diagram and technical status information of the engineering change unit obtained include the top diagram number, version, baseline number, baseline name, parent node number, engineering change unit number, engineering change unit type, and time of generating the engineering change unit.

5. An aircraft engineering change unit division device, characterized in that: include: A top view acquisition module is used to acquire an aircraft top view, and when the scale of the aircraft top view reaches a predetermined scale, the aircraft top view is split to obtain a plurality of engineering change units; The product tree module is used to generate a product structure tree for the components in the aircraft top view that need to be split according to the aircraft technical status baseline; The node counting module is used to count all nodes on the product structure tree, taking the sum of the number of the current node and all the components under the current node as the count of the current node, and obtaining the count value of each node; A marking module is used to traverse the product structure tree starting from the root node of the product structure tree corresponding to the airplane top image. When the count value of the node is greater than the threshold, the current node is marked with the first identifier and the traversal to the next level node is continued; when the count value of the node is less than the threshold, the current node is marked with the second identifier and the traversal to the next level is stopped; The storage module is used to save all nodes with the first identifier and the second identifier as engineering change units, obtain the top view and technical status information of the engineering change unit, and complete the division of the aircraft engineering change unit.

6. The aircraft engineering change unit division device according to claim 5, characterized in that: The predetermined scale refers to an aircraft top view with 200 or more components.

7. The aircraft engineering change unit division device according to claim 5, characterized in that: When marking the current node, the first identifier and the second identifier are identifiers of different colors or digital identifiers of different states.

8. The aircraft engineering change unit division device according to claim 5, characterized in that: The top diagram and technical status information of the engineering change unit obtained include the top diagram number, version, baseline number, baseline name, parent node number, engineering change unit number, engineering change unit type, and time of generating the engineering change unit.

9. An electronic device, characterized in that: include: one or more processors; Memory; One or more application programs are stored in the memory and configured to be executed by the one or more processors, and the one or more application programs are configured to implement the aircraft engineering change unit division method according to any one of claims 1 to 4.

10. A computer storage medium, characterized in that: The computer storage medium stores at least one instruction, at least one program, a code set or an instruction set, and the at least one instruction, the at least one program, the code set or the instruction set is loaded and executed by the processor to implement the aircraft engineering change unit division method according to any one of claims 1 to 4.

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