An integrated design method for the electrical system of an aircraft based on an association model

Abstract

This application belongs to the technical field of aircraft electrical system design, and particularly relates to an integrated design method for aircraft electrical systems based on an association model. The method includes: Step S1, reusing the electrical physical architecture model of the aircraft, selecting electrical signals and connectors, and establishing a two-dimensional electrical principle model; Step S2, constructing a three-dimensional electrical system layout model according to the two-dimensional electrical principle model; Step S3, in the three-dimensional electrical system layout model, conducting a comprehensive design of three-dimensional electrical wiring and electrical interconnection, and setting virtual separation surface connectors; Step S4, reversely generating a two-dimensional wiring model separated by virtual separation surface connectors according to the three-dimensional electrical system layout model; Step S5, designing the virtual separation surface connectors and pre-grouping the wire harnesses in the two-dimensional wiring model; Step S6, generating a three-dimensional wire harness model of the electrical system based on the two-dimensional wiring model, and optimizing the pre-grouped wire harnesses.

Description

Technical Field

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

[0002] The design of aircraft electrical interconnection systems includes two-dimensional design and three-dimensional design. Currently, digital design methods are generally used to carry out the design of electrical interconnection systems. However, in the existing design methods, the two-dimensional electrical design and three-dimensional design are carried out in different design software, and there is a lack of information association between the two-dimensional design model and the three-dimensional design model. There are complex data model conversions in the two-dimensional design and three-dimensional design processes, resulting in low iteration efficiency of the two-dimensional design and three-dimensional design of electrical interconnection systems, 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, this application provides an integrated design method for aircraft electrical systems based on an association model, which mainly includes:

[0004] Step S1: Reuse the electrical physical architecture model of the aircraft, select electrical signals and connectors, and establish a two-dimensional electrical principle model;

[0005] Step S2: Construct a three-dimensional electrical system layout model according to the two-dimensional electrical principle model;

[0006] Step S3: In the three-dimensional electrical system layout model, conduct comprehensive design of three-dimensional electrical routing and electrical interconnection, and set virtual separation surface connectors;

[0007] Step S4: According to the three-dimensional electrical system layout model, reversely generate a two-dimensional wiring model separated by virtual separation surface connectors;

[0008] Step S5: Design virtual separation surface connectors and pre-group wiring harnesses in the two-dimensional wiring model;

[0009] 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 harnesses.

[0010] Preferably, step S1 further includes:

[0011] Step S11: Reuse the electrical physical architecture model, and according to the total number of signal connections in the electrical physical architecture model, create the corresponding number of virtual signal terminals in the electrical physical architecture model;

[0012] Step S12: Select device connectors for each device in the electrical physical architecture model, determine the number and type of connectors on the device, and establish a mapping relationship between the terminals of the device connectors and the virtual signal terminals;

[0013] 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;

[0014] Step S14: generating the two-dimensional electrical principle model according to the electrical interconnection interface model.

[0015] Preferably, step S2 further comprises:

[0016] Step S21, carrying out electrical three-dimensional layout design according to the two-dimensional electrical principle model, and establishing an electrical main channel model;

[0017] 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.

[0018] 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.

[0019] Preferably, the mapping rules of the related objects in the two-dimensional electrical principle model and the three-dimensional electrical system layout model include:

[0020] The equipment in the 2D electrical principle model and the 3D electrical system layout model are associated according to the naming rules;

[0021] The connectors in the 2D electrical schematic model and the 3D electrical system layout model are associated according to the naming rules;

[0022] 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.

[0023] Preferably, step S3 further comprises:

[0024] 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;

[0025] 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.

[0026] Preferably, in step S32, the implementation of the three-dimensional electrical grounding comprehensive design includes setting an integrated virtual grounding bracket and grounding pile, or a virtual grounding module; the implementation of the equipotential comprehensive design includes generating a hinge point at the bifurcation of the wiring path and setting a wiring module at the hinge point; the implementation of the separation surface comprehensive design includes setting a virtual separation surface connector and determining the wires passing through the virtual separation surface connector.

[0027] Preferably, step S5 further includes:

[0028] Step S51: Conduct a selection and design for each virtual separation surface connector, and make a detailed matching definition for the wires passing through the virtual separation surface connector and the pins of the virtual separation surface connector;

[0029] Step S52: According to the selection and design results of the virtual separation surface connector, improve the electrical wiring model and conduct an electrical connectivity simulation;

[0030] Step S53: Pre-group the wire harnesses in the electrical wiring model according to the logical wire harness grouping rules to form multiple wire harness sets.

[0031] Preferably, step S6 further includes:

[0032] Step S61: Through the topological form in the three-dimensional state, determine whether the pre-grouped wire harnesses reach a state where they can be installed. If there are un-installable branch wires or loop paths in the topological form, it means that the pre-grouped wire harnesses cannot be installed. Then, add a separation surface at the branch wire, or perform a secondary extraction on a part of the branch wire or loop path to obtain multiple wire harnesses;

[0033] Step S62: Conduct the installation design of the three-dimensional wire harness assembly to generate the final three-dimensional wire harness installation model.

[0034] Preferably, step S62: The implementation of the installation design of the three-dimensional wire harness assembly includes:

[0035] Determine the installation positions and selections of brackets and clamps, and conduct a check on the bending radius, load, and weight of the wire harness.

[0036] This application realizes the continuous transfer, two-way drive, and agile iteration of the full-process digital model from electrical physical architecture design, electrical principle design, electrical comprehensive 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 the data consistency of each link in the design of the electrical interconnection system. Description of the Drawings

[0037] Figure 1 It is a flowchart of a preferred embodiment of the integrated design method for an aircraft electrical system based on an associated model in this application.

[0038] Figure 2 is the two-dimensional electrical principle model construction flow chart of the embodiment shown in the present application. Figure 1 shown in the embodiment.

[0039] Figure 3 is the present application Figure 1 shown in the embodiment of the three-dimensional electrical system layout model construction flow chart. Specific embodiments

[0040] To make the purpose, technical solutions and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present application and should not be construed as limiting the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0041] The present application provides an integrated design method for an aircraft electrical system based on an association model, as Figures 1 - 3 shown, mainly including:

[0042] Step S1: Reuse the electrical physical architecture model of the aircraft, select electrical signals and connectors, and establish a two-dimensional electrical principle model;

[0043] Step S2: Construct a three-dimensional electrical system layout model according to the two-dimensional electrical principle model;

[0044] Step S3: In the three-dimensional electrical system layout model, conduct a comprehensive design of three-dimensional electrical routing and electrical interconnection, and set virtual separation surface connectors;

[0045] Step S4: According to the three-dimensional electrical system layout model, reversely generate a two-dimensional wiring model separated by virtual separation surface connectors;

[0046] Step S5: Design the virtual separation surface connectors and the pre-grouping of wire harnesses in the two-dimensional wiring model;

[0047] Step S6: Generate a three-dimensional wire harness model of the electrical system based on the two-dimensional wiring model, and optimize the pre-grouped wire harnesses.

[0048] In some alternative embodiments, as Figure 2 shown, step S1 further includes:

[0049] Step S11: Reuse the electrical physical architecture model. According to the total number of signal connections in the electrical physical architecture model, create a corresponding number of virtual signal terminals in the electrical physical architecture model.

[0050] Step S12: Conduct equipment connector selection for each device in the electrical physical architecture model, determine the number and model of connectors on the device, and establish a mapping relationship between the terminals of the equipment connector and the virtual signal terminals.

[0051] Step S13: For each physical interface in the electrical physical architecture model, determine the specific electrical signals it transmits, connect each electrical signal to the virtual signal terminals at both ends of the two devices, and establish an electrical interconnection interface model.

[0052] Step S14: Generate the two-dimensional electrical principle model according to the electrical interconnection interface model.

[0053] In this embodiment, after constructing the electrical interconnection interface model, for each physical device, check the electrical signal connectivity of the device through an automated program and the physical architecture connection relationship to ensure that there are no isolated electrical signal terminals for all devices. Finally, create the root node of the subsystem electrical schematic diagram. Through the automated program, according to the electrical interconnection interface model, automatically generate schematic diagram devices, two-dimensional electrical signals, signal terminals, and their cross-linking relationships under the schematic diagram root node, and generate the two-dimensional electrical principle model through an automatic drawing tool.

[0054] Steps S2 and S3 are used for the design of the three-dimensional electrical system layout model.

[0055] In some alternative embodiments, step S2 further includes:

[0056] Step S21: Conduct three-dimensional electrical layout design according to the two-dimensional electrical principle model and establish an electrical main channel model.

[0057] Step S22: On the basis of the electrical main channel model, according to the mapping rules of relevant objects in the two-dimensional electrical principle model and the three-dimensional electrical system layout model, and taking the subsystems of the aircraft as the grouping basis, generate an initial three-dimensional electrical system layout model, including three-dimensional devices and three-dimensional wires.

[0058] In some alternative embodiments, in step S21, conduct three-dimensional electrical layout design under the constraints of the shape and structural layout of the three-dimensional digital mock-up.

[0059] It should be further noted that before step S22, the mapping rules for related objects in the two-dimensional electrical principle model and the three-dimensional electrical system layout model are further constructed. In some alternative embodiments, the mapping rules for related objects in the two-dimensional electrical principle model and the three-dimensional electrical system layout model include:

[0060] The devices in the two-dimensional electrical principle model and the three-dimensional electrical system layout model are associated according to the naming rules;

[0061] The connectors in the two-dimensional electrical principle model and the three-dimensional electrical system layout model are associated according to the naming rules;

[0062] The electrical signals in the two-dimensional electrical principle model and the channels in the three-dimensional electrical system layout model are associated according to the reference relationship.

[0063] After that, in step S3, according to the three-dimensional electrical system layout model, electrical laying is carried out to determine the laying paths of each level of laying channels and wires.

[0064] In some alternative embodiments, step S3 further includes:

[0065] Step S31: On the wire laying path, carry out the detailed design of electrical layout, establish secondary electrical channels and related virtual separation surface models according to the aircraft structure such as the aircraft cabin, the division design of each part of the aircraft, etc., and separate the overall three-dimensional wires through the virtual separation surface model;

[0066] Step S32: Carry out the comprehensive three-dimensional electrical grounding design, equipotential comprehensive design and separation surface comprehensive design according to the electromagnetic compatibility, structural weight reduction and anti-error design rules.

[0067] 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 alternative embodiments, in step S32, carrying out the comprehensive three-dimensional electrical grounding design includes setting an integrated virtual grounding bracket and grounding pile, or a virtual grounding module; carrying out the equipotential comprehensive design includes generating a hinged point at the bifurcation of the wiring path and setting a wiring module at the hinged point; carrying out the separation surface comprehensive design includes setting a virtual separation surface connector and determining the wires passing through the virtual separation surface connector.

[0068] In this embodiment, in the comprehensive grounding design, according to the electrical laying path and schematic diagram analysis, the classification and layout of the original grounding terminals are analyzed, and an integrated virtual grounding bracket and grounding pile are set, or a virtual grounding module is used for grounding design. In the equipotential comprehensive design, according to the analysis of the electrical laying path, all equipotential signals are default to generate articulated points that meet the wire gauge requirements at the bifurcation of the wiring path, and wiring modules are set at these articulated points. In the separation surface comprehensive design, according to the analysis of the electrical laying path and the position of the virtual separation surface, the layout of the separation surface connectors is analyzed, virtual separation surface connectors are set, and the wires passing through the separation surface connectors are determined.

[0069] Steps S4 and S5 are used to design the two-dimensional wiring model generated in reverse. In step S4, according to the three-dimensional electrical system layout model, under the initial node of the two-dimensional electrical wiring model, a partitioned two-dimensional wiring model and virtual separation surface connectors are automatically generated. In step S5, the two-dimensional wiring model is designed.

[0070] In some alternative embodiments, step S5 further includes:

[0071] Step S51: Select and design each virtual separation surface connector. Refer to specifications such as design wire gauge, current, and electromagnetic compatibility, and make a detailed matching definition of the wires passing through the virtual separation surface connector and the pins of the virtual separation surface connector through the connector type spectrum diagram;

[0072] Step S52: According to the selection and design results of the virtual separation surface connectors, automatically construct a two-dimensional electrical wiring model through an automated program, improve the electrical wiring model, and conduct electrical connectivity simulation through the association relationship check between wires and connectors;

[0073] Step S53: Pre-group the wire harnesses in the electrical wiring model according to the logical wire harness grouping rules to form multiple wire harness sets.

[0074] Finally, in step S6, a feasibility analysis of the pre-grouped wire harnesses is further performed in the three-dimensional wire harness model.

[0075] In some alternative embodiments, step S6 further includes:

[0076] Step S61: Through the topological form in the three-dimensional state, determine whether the pre-grouped wire harnesses reach a state where they can be installed. If there are un-installable branch wires (such as wire harness intersections) or circular paths in the topological form, it means that the pre-grouped wire harnesses cannot be installed. Then, add a separation surface at the branch wire, or perform a secondary extraction on a part of the branch wire or circular path to obtain multiple wire harnesses; if there are no difficult-to-install branches in the three-dimensional wire harness design scheme in the topological form and it meets other specifications such as redundancy design, the pre-grouped wire harness design scheme is mature, and the program automatically generates a three-dimensional wire harness component.

[0077] Step S62: Conduct the installation design of the three-dimensional wire harness assembly to generate the final three-dimensional wire harness installation model.

[0078] In this embodiment, when the bending radius of the wire harness is less than the preset threshold (3 times the wire diameter) or there is a circular path, the reconstruction algorithm is triggered. Among them, the determination basis for reconstruction when there is a circular path is expressed as:

[0079] ;

[0080] wherein: the wire is divided into n segments, ri is the bending radius of the i-th segment of the wire, and di is the diameter of the i-th segment of the wire. is an adjustment parameter, cloop is the complexity coefficient of the circular path, and TH is the reconstruction threshold, which is recommended to be taken as 0.8.

[0081] In some alternative embodiments, Step S62: Conduct the installation design of the three-dimensional wire harness assembly includes:

[0082] Determine the installation positions and selections of the brackets and clamps, and conduct the verification of the bending radius, load, and weight of the wire harness.

[0083] As mentioned above, the above are only the specific embodiments 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 those skilled in the technical field of the present application within the technical scope disclosed by the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to 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, generating a three-dimensional wiring harness model of the electrical system based on the two-dimensional wiring model, and optimizing the pre-grouped wiring harness; Wherein, 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 a mapping rule between the two-dimensional electrical principle model and related objects in the three-dimensional electrical system layout model, including three-dimensional equipment and three-dimensional wires; In step S21, electrical three-dimensional layout design is carried out under the constraints of the three-dimensional digital prototype appearance and structural layout; 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.

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 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.

4. The aircraft electrical system integrated design method based on the association model as claimed in claim 3, 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.

5. 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.

6. 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.

7. The aircraft electrical system integrated design method based on the association model as claimed in claim 6, 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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