Aircraft electrical system integrated design method based on correlation model

Abstract

The invention belongs to the technical field of aircraft electrical system design, and particularly relates to an aircraft electrical system integrated design method based on a correlation model. The method comprises the following steps: S1, multiplexing an electrical physical architecture model of an aircraft, performing electrical signal and connector type selection, and establishing a two-dimensional electrical principle model; s2, constructing a three-dimensional electrical system arrangement model according to the two-dimensional electrical principle model; s3, performing three-dimensional electrical laying and electrical interconnection comprehensive design in the three-dimensional electrical system arrangement model, and setting a virtual separation surface connector; s4, according to the three-dimensional electrical system arrangement model, reversely generating a two-dimensional wiring model which is partitioned through a virtual separation surface connector; s5, carrying out the design of a virtual separation surface connector and the design of wire harness pre-grouping in the two-dimensional wiring model; and S6, generating a three-dimensional wiring harness model of the electrical system based on the two-dimensional wiring model, and optimizing the pre-grouped wiring harnesses.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft electrical system design, and in particular, relates to an integrated design method for aircraft electrical systems based on an association model. Background Art

[0002] The design of aircraft electrical interconnection system includes 2D design and 3D design, and currently digital design methods are widely used to carry out electrical interconnection system design. However, in the existing design methods, electrical 2D design and 3D design are carried out in different design software, 2D design models and 3D design models lack information association, and there is complex data model conversion in the 2D design and 3D design process, resulting in low iteration efficiency of 2D design and 3D design of electrical interconnection system, and it is difficult to ensure the consistency of digital models in each link. Summary of the invention

[0003] In order to solve the above problems, the present application provides an integrated design method for an aircraft electrical system based on an association model, which mainly includes: Step S1, reuse the electrical physical architecture model of the aircraft, select electrical signals and connectors, and establish a two-dimensional electrical principle model; Step S2, constructing a three-dimensional electrical system layout model based on the two-dimensional electrical principle model; Step S3, in the three-dimensional electrical system layout model, perform three-dimensional electrical laying and electrical interconnection comprehensive design, and set up virtual separation surface connectors; Step S4, reversely generating a two-dimensional wiring model separated by a virtual separation surface connector according to the three-dimensional electrical system layout model; Step S5, designing a virtual separation surface connector and a wiring harness pre-grouping in the two-dimensional wiring model; Step S6: Generate a three-dimensional wiring harness model of the electrical system based on the two-dimensional wiring model, and optimize the pre-grouped wiring harness.

[0004] Preferably, step S1 further comprises: Step S11, multiplexing the electrical physical architecture model, and creating a corresponding number of virtual signal terminals in the electrical physical architecture model according to the total number of signal connections in the electrical physical architecture model; Step S12: selecting device connectors for each device in the electrical physical architecture model, determining the number and model of connectors on the device, and establishing a mapping relationship between the terminals of the device connectors and the virtual signal terminals; Step S13: for each physical interface in the electrical physical architecture model, determine the specific electrical signal transmitted by it, connect each electrical signal to the virtual signal terminals at the ends of the two devices, and establish an electrical interconnection interface model; Step S14: generating the two-dimensional electrical principle model according to the electrical interconnection interface model.

[0005] Preferably, step S2 further comprises: Step S21, carrying out electrical three-dimensional layout design according to the two-dimensional electrical principle model, and establishing an electrical main channel model; Step S22: Based on the electrical main channel model, an initial three-dimensional electrical system layout model is generated according to the mapping rules between the two-dimensional electrical principle model and the related objects in the three-dimensional electrical system layout model, including three-dimensional equipment and three-dimensional wires.

[0006] Preferably, in step S21, electrical three-dimensional layout design is carried out under the constraints of the three-dimensional digital prototype appearance and structural layout.

[0007] Preferably, the mapping rules of the related objects in the two-dimensional electrical principle model and the three-dimensional electrical system layout model include: The equipment in the 2D electrical principle model and the 3D electrical system layout model are associated according to the naming rules; The connectors in the 2D electrical schematic model and the 3D electrical system layout model are associated according to the naming rules; The electrical signals in the 2D electrical schematic model are associated with the channels in the 3D electrical system layout model according to a reference relationship.

[0008] Preferably, step S3 further comprises: Step S31, establishing a secondary electrical channel and a related virtual separation surface model according to the aircraft structure, and separating the entire three-dimensional wires through the virtual separation surface model; Step S32: Carry out three-dimensional electrical grounding comprehensive design, equipotential comprehensive design and separation surface comprehensive design in accordance with electromagnetic compatibility, structural weight reduction and error-proofing design rules.

[0009] Preferably, in step S32, carrying out a three-dimensional electrical grounding comprehensive design includes setting up an integrated virtual grounding bracket and grounding pile, or a virtual grounding module; carrying out an equipotential comprehensive design includes generating a hinge point at the bifurcation of the wiring path, and setting up a wiring module at the hinge point; carrying out a separation surface comprehensive design includes setting up a virtual separation surface connector, and determining the wires passing through the virtual separation surface connector.

[0010] Preferably, step S5 further comprises: Step S51, selecting and designing each virtual separation surface connector, and making detailed matching definitions between the wires passing through the virtual separation surface connector and the pins of the virtual separation surface connector; Step S52: according to the selection and design result of the virtual separation surface connector, improve the electrical wiring model and perform electrical connectivity simulation; Step S53: pre-group the wire harnesses in the electrical wiring model according to the logical wire harness grouping rule to form a plurality of wire harness sets.

[0011] Preferably, step S6 further comprises: Step S61: judging whether the pre-grouped wiring harness has reached a state where it can be installed by the topological form in the three-dimensional state; if a branch wire or a loop path that cannot be installed appears in the topological form, indicating that the pre-grouped wiring harness cannot be installed, a separation surface is added at the branch wire, or a part of the branch wire or the loop path is extracted twice to obtain multiple wiring harnesses; Step S62: Carry out installation design of the three-dimensional wire harness assembly and generate a final three-dimensional wire harness installation model.

[0012] Preferably, step S62, carrying out installation design of the three-dimensional wiring harness assembly includes: Determine the installation location and selection of brackets and clamps, and check the bending radius, load and weight of the wire harness.

[0013] This application realizes the continuous transmission, two-way drive and agile iteration of digital models in the entire process from electrical physical architecture design, electrical principle design, electrical integrated design, electrical wiring design and three-dimensional wire harness design, eliminates the frequent interface conversion between electrical two-dimensional design and three-dimensional design models, and ensures data consistency in all aspects of electrical interconnection system design. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a flowchart of a preferred embodiment of the aircraft electrical system integrated design method based on the association model of the present application.

[0015] Figure 2 This application Figure 1 A flowchart of constructing a two-dimensional electrical schematic model of the illustrated embodiment.

[0016] Figure 3 This application Figure 1 A flowchart of constructing a three-dimensional electrical system layout model according to the illustrated embodiment. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0018] This application provides an integrated design method for aircraft electrical systems based on an association model, such as Figure 1-Figure 3 As shown, it mainly includes: Step S1, reuse the electrical physical architecture model of the aircraft, select electrical signals and connectors, and establish a two-dimensional electrical principle model; Step S2, constructing a three-dimensional electrical system layout model based on the two-dimensional electrical principle model; Step S3, in the three-dimensional electrical system layout model, perform three-dimensional electrical laying and electrical interconnection comprehensive design, and set up virtual separation surface connectors; Step S4, reversely generating a two-dimensional wiring model separated by a virtual separation surface connector according to the three-dimensional electrical system layout model; Step S5, designing a virtual separation surface connector and a wiring harness pre-grouping in the two-dimensional wiring model; Step S6: Generate a three-dimensional wiring harness model of the electrical system based on the two-dimensional wiring model, and optimize the pre-grouped wiring harness.

[0019] In some optional embodiments, such as Figure 2 As shown, step S1 further includes: Step S11, multiplexing the electrical physical architecture model, and creating a corresponding number of virtual signal terminals in the electrical physical architecture model according to the total number of signal connections in the electrical physical architecture model; Step S12: selecting device connectors for each device in the electrical physical architecture model, determining the number and model of connectors on the device, and establishing a mapping relationship between the terminals of the device connectors and the virtual signal terminals; Step S13: for each physical interface in the electrical physical architecture model, determine the specific electrical signal transmitted by it, connect each electrical signal to the virtual signal terminals at the ends of the two devices, and establish an electrical interconnection interface model; Step S14: generating the two-dimensional electrical principle model according to the electrical interconnection interface model.

[0020] In this embodiment, after constructing the electrical interconnection interface model, for each physical device, the electrical signal connectivity of the device is checked through the automation program and the physical architecture connection relationship to ensure that all devices have no isolated electrical signal terminals. Finally, the subsystem electrical schematic root node is created, and the schematic devices, two-dimensional electrical signals, signal terminals and their cross-linking relationships are automatically generated under the schematic root node through the automation program according to the electrical interconnection interface model, and a two-dimensional electrical schematic model is generated through the automatic drawing tool.

[0021] Step S2 and step S3 are used to design a three-dimensional electrical system layout model.

[0022] In some optional implementations, step S2 further includes: Step S21, carrying out electrical three-dimensional layout design according to the two-dimensional electrical principle model, and establishing an electrical main channel model; Step S22: Based on the electrical main channel model, according to the mapping rules of the two-dimensional electrical principle model and the related objects in the three-dimensional electrical system layout model, and based on the aircraft subsystems as the grouping basis, an initial three-dimensional electrical system layout model is generated, including three-dimensional equipment and three-dimensional wires.

[0023] In some optional implementations, in step S21, electrical three-dimensional layout design is carried out under the constraints of the three-dimensional digital prototype appearance and structural layout.

[0024] It should also be noted that before step S22, a mapping rule between the two-dimensional electrical principle model and the related objects in the three-dimensional electrical system layout model is further constructed. In some optional implementations, the mapping rule between the two-dimensional electrical principle model and the related objects in the three-dimensional electrical system layout model includes: The equipment in the 2D electrical principle model and the 3D electrical system layout model are associated according to the naming rules; The connectors in the 2D electrical schematic model and the 3D electrical system layout model are associated according to the naming rules; The electrical signals in the 2D electrical schematic model are associated with the channels in the 3D electrical system layout model according to a reference relationship.

[0025] Then in step S3, electrical laying is carried out according to the three-dimensional electrical system layout model to determine the laying channels at each level and the laying paths of the wires.

[0026] In some optional implementations, step S3 further includes: Step S31: On the wire laying path, detailed design of electrical layout is carried out, and secondary electrical channels and related virtual separation surface models are established according to the aircraft structure, such as the aircraft cabin and the design of the division of each section of the aircraft, and the overall three-dimensional wires are separated by the virtual separation surface model; Step S32: Carry out three-dimensional electrical grounding comprehensive design, equipotential comprehensive design and separation surface comprehensive design in accordance with electromagnetic compatibility, structural weight reduction and error-proofing design rules.

[0027] It should be noted that step S32 is used to optimize the length and weight of the wires in the electrical interconnection system. In some optional embodiments, in step S32, carrying out the three-dimensional electrical grounding integrated design includes setting an integrated virtual grounding bracket and grounding pile, or a virtual grounding module; carrying out the equipotential integrated design includes generating a hinge point at the bifurcation of the wiring path, and setting a wiring module at the hinge point; carrying out the separation surface integrated design includes setting a virtual separation surface connector and determining the wire passing through the virtual separation surface connector.

[0028] In this embodiment, in the grounding integrated design, the classification and arrangement of the original grounding terminals are analyzed according to the electrical laying path and the schematic diagram, and an integrated virtual grounding bracket and grounding pile are set, or a virtual grounding module is used for grounding design. In the equipotential integrated design, according to the electrical laying path analysis, all equipotential signals generate hinge points that meet the wire gauge requirements at the bifurcation of the wiring path by default, and wiring modules are set at these hinge points. In the separation surface integrated design, the arrangement of the separation surface connector is analyzed according to the electrical laying path and the position of the virtual separation surface, a virtual separation surface connector is set, and the wires passing through the separation surface connector are determined.

[0029] Steps S4 and S5 design the reverse generated two-dimensional wiring model. In step S4, based on the three-dimensional electrical system layout model, the partitioned two-dimensional wiring model and the virtual separation surface connector are automatically generated under the initial node of the two-dimensional electrical wiring model. In step S5, the two-dimensional wiring model is designed.

[0030] In some optional implementations, step S5 further includes: Step S51, selecting and designing each virtual separation surface connector, referring to the design wire gauge, current, electromagnetic compatibility and other specifications, and making a detailed matching definition of the wire passing through the virtual separation surface connector and the pin of the virtual separation surface connector through the connector type spectrum; Step S52: According to the selection and design result of the virtual separation surface connector, a two-dimensional electrical wiring model is automatically constructed through an automated program, the electrical wiring model is improved, and an electrical connectivity simulation is performed by checking the association relationship between the wire and the connector; Step S53: pre-group the wire harnesses in the electrical wiring model according to the logical wire harness grouping rule to form a plurality of wire harness sets.

[0031] Finally, in step S6, a feasibility analysis is further performed on the pre-grouped wire harnesses in the three-dimensional wire harness model.

[0032] In some optional implementations, step S6 further includes: Step S61, judging whether the pre-grouped harness has reached a state where it can be installed through the topological morphology in the three-dimensional state; if branch wires (such as harness cross-connections) or loop paths that cannot be installed appear in the topological morphology, indicating that the pre-grouped harness cannot be installed, a separation surface is added at the branch wire, or a part of the branch wire or loop path is extracted twice to obtain multiple harnesses; if the three-dimensional harness design in the topological morphology does not have branches that are difficult to install and meets other specifications such as redundancy design, the pre-grouped harness design is mature, and the program automatically generates a three-dimensional harness assembly.

[0033] Step S62: Carry out installation design of the three-dimensional wire harness assembly and generate a final three-dimensional wire harness installation model.

[0034] In this embodiment, when the bending radius of the wire harness is less than a preset threshold (3 times the wire diameter) or there is a loop path, the reconstruction algorithm is triggered. The basis for determining the reconstruction of the loop path is expressed as: ; Where: the conductor is divided into n segments, ri is the bending radius of the i-th segment conductor, di is the diameter of the i-th segment conductor, To adjust the parameters, cloop is the loop path complexity coefficient, TH is the reconstruction threshold, and 0.8 is recommended.

[0035] In some optional implementations, step S62, carrying out installation design of the three-dimensional wiring harness assembly includes: Determine the installation location and selection of brackets and clamps, and check the bending radius, load and weight of the wire harness.

[0036] 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. An integrated design method for aircraft electrical systems based on an association model, characterized in that: include: Step S1, reuse the electrical physical architecture model of the aircraft, select electrical signals and connectors, and establish a two-dimensional electrical principle model; Step S2, constructing a three-dimensional electrical system layout model based on the two-dimensional electrical principle model; Step S3, in the three-dimensional electrical system layout model, perform three-dimensional electrical laying and electrical interconnection comprehensive design, and set up virtual separation surface connectors; Step S4, reversely generating a two-dimensional wiring model separated by a virtual separation surface connector according to the three-dimensional electrical system layout model; Step S5, designing a virtual separation surface connector and a wiring harness pre-grouping in the two-dimensional wiring model; Step S6: Generate a three-dimensional wiring harness model of the electrical system based on the two-dimensional wiring model, and optimize the pre-grouped wiring harness.

2. The aircraft electrical system integrated design method based on the association model according to claim 1, characterized in that: Step S1 further comprises: Step S11, multiplexing the electrical physical architecture model, and creating a corresponding number of virtual signal terminals in the electrical physical architecture model according to the total number of signal connections in the electrical physical architecture model; Step S12: selecting device connectors for each device in the electrical physical architecture model, determining the number and model of connectors on the device, and establishing a mapping relationship between the terminals of the device connectors and the virtual signal terminals; Step S13: for each physical interface in the electrical physical architecture model, determine the specific electrical signal transmitted by it, connect each electrical signal to the virtual signal terminals at the ends of the two devices, and establish an electrical interconnection interface model; Step S14: generating the two-dimensional electrical principle model according to the electrical interconnection interface model.

3. The aircraft electrical system integrated design method based on the association model according to claim 1, characterized in that: Step S2 further comprises: Step S21, carrying out electrical three-dimensional layout design according to the two-dimensional electrical principle model, and establishing an electrical main channel model; Step S22: Based on the electrical main channel model, an initial three-dimensional electrical system layout model is generated according to the mapping rules between the two-dimensional electrical principle model and the related objects in the three-dimensional electrical system layout model, including three-dimensional equipment and three-dimensional wires.

4. The aircraft electrical system integrated design method based on the association model as claimed in claim 3, characterized in that: In step S21, electrical three-dimensional layout design is carried out under the constraints of the three-dimensional digital prototype appearance and structural layout.

5. The aircraft electrical system integrated design method based on the association model as claimed in claim 3, characterized in that: The mapping rules of the related objects in the two-dimensional electrical principle model and the three-dimensional electrical system layout model include: The equipment in the 2D electrical principle model and the 3D electrical system layout model are associated according to the naming rules; The connectors in the 2D electrical schematic model and the 3D electrical system layout model are associated according to the naming rules; The electrical signals in the 2D electrical schematic model are associated with the channels in the 3D electrical system layout model according to a reference relationship.

6. The aircraft electrical system integrated design method based on the association model according to claim 1, characterized in that: Step S3 further comprises: Step S31, establishing a secondary electrical channel and a related virtual separation surface model according to the aircraft structure, and separating the entire three-dimensional wires through the virtual separation surface model; Step S32: Carry out three-dimensional electrical grounding comprehensive design, equipotential comprehensive design and separation surface comprehensive design in accordance with electromagnetic compatibility, structural weight reduction and error-proofing design rules.

7. The aircraft electrical system integrated design method based on the association model according to claim 6, characterized in that: In step S32, carrying out the three-dimensional electrical grounding integrated design includes setting an integrated virtual grounding bracket and grounding pile, or a virtual grounding module; carrying out the equipotential integrated design includes generating an articulation point at the bifurcation of the wiring path, and setting a wiring module at the articulation point; Carrying out the integrated design of the separation surface includes setting a virtual separation surface connector and determining the conductor passing through the virtual separation surface connector.

8. The aircraft electrical system integrated design method based on the association model according to claim 1, characterized in that: Step S5 further comprises: Step S51, selecting and designing each virtual separation surface connector, and making detailed matching definitions between the wires passing through the virtual separation surface connector and the pins of the virtual separation surface connector; Step S52: according to the selection and design result of the virtual separation surface connector, improve the electrical wiring model and perform electrical connectivity simulation; Step S53: pre-group the wire harnesses in the electrical wiring model according to the logical wire harness grouping rule to form a plurality of wire harness sets.

9. The aircraft electrical system integrated design method based on the association model according to claim 1, characterized in that: Step S6 further comprises: Step S61: judging whether the pre-grouped wiring harness has reached a state where it can be installed by the topological form in the three-dimensional state; if a branch wire or a loop path that cannot be installed appears in the topological form, indicating that the pre-grouped wiring harness cannot be installed, a separation surface is added at the branch wire, or a part of the branch wire or the loop path is extracted twice to obtain multiple wiring harnesses; Step S62: Carry out installation design of the three-dimensional wire harness assembly and generate a final three-dimensional wire harness installation model.

10. The aircraft electrical system integrated design method based on the association model according to claim 9, characterized in that: Step S62, carrying out installation design of the three-dimensional wiring harness assembly includes: Determine the installation location and selection of brackets and clamps, and check the bending radius, load and weight of the wire harness.

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