A comprehensive design method for aircraft wiring harness

Abstract

The present application relates to a comprehensive design method for aircraft wiring harnesses, including: bundling cables of various high-importance systems of the aircraft; bundling cables of core equipment in various general-importance systems of the aircraft; merging cables interconnected with its core equipment in various general-importance systems into the wiring harness of the corresponding core equipment; merging cables of various general-importance systems that are adjacently interconnected with core equipment in other general-importance systems into the wiring harness of the corresponding core equipment; bundling adjacent cables of various general-importance systems into each other, or merging them into the wiring harness of adjacent core equipment; splitting and allocating wiring harnesses with redundancy and electromagnetic compatibility requirements to obtain initial wiring harnesses; designing initial laying paths of various wiring harnesses on the aircraft; and adjusting wiring harnesses and / or laying paths when redundancy isolation constraints, electromagnetic compatibility isolation constraints, path impedance constraints or laying path constraints cannot be met between wiring harnesses.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft wiring harness integrated design, and specifically relates to an aircraft wiring harness integrated design method. Background Art

[0002] Aircraft wiring harness integration is to realize the logical layer connection relationship between airborne devices into a design of manufacturable and installable cable bundles at the physical layer.

[0003] The comprehensive cable design on aircraft has three levels:

[0004] The first level is the pre-integration level, which bundles the cables according to the integrity of the functions of each system on the aircraft. For example, all the cables of the navigation system are bundled, and all the cables of the flight control system are bundled. When there is signal interaction between the wiring harness of the navigation system and the wiring harness of the flight control system, a process docking surface is set between the wiring harness of the navigation system and the wiring harness of the flight control system, and the connector is used for docking. This wiring harness integration level focuses on the realization of the functions of each system on the aircraft, and lacks relevant designs for the performance requirements of the wiring harness such as redundancy and electromagnetic compatibility. In addition, the number of wiring harnesses obtained is too large, and the wiring harnesses are unbalanced. Some wiring harnesses are too thick in diameter, and some are too thin in diameter. It is not possible to efficiently use the space on the aircraft and it is difficult to lay them on the aircraft.

[0005] The second level is the initial integration level. First, the cables are bundled according to the integrity of the functions of each system on the aircraft, then the harnesses are integrated locally, and finally the harnesses are integrated at the whole machine level. This harness integration level still bundles the cables based on the functions of each system on the aircraft, but the harnesses are integrated locally and at the whole machine level, which can reduce the number of harnesses, promote the balance between harnesses, improve the efficiency of space utilization on the aircraft, and facilitate laying on the aircraft. However, the performance requirements such as redundancy and electromagnetic compatibility of the harness have not yet been designed.

[0006] The third level is the fine integration level. When bundling the cables of various systems on the aircraft, cables with compatible performance such as redundancy and electromagnetic compatibility are bundled, and cables with incompatible redundancy and electromagnetic compatibility are isolated and designed. This level of wiring harness integration fully considers the performance requirements of wiring harness redundancy, electromagnetic compatibility and other performance requirements, but it is easy to produce a large number of small wiring harnesses, which greatly increases the difficulty of laying on the aircraft, and breaks the relative integrity of the system functions, making it difficult to maintain.

[0007] This application is proposed in view of the above-mentioned technical defects.

[0008] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention

[0009] The purpose of the present application is to provide an integrated design method for aircraft wiring harnesses to overcome or alleviate at least one of the known technical deficiencies.

[0010] The technical solution of this application is:

[0011] An aircraft wiring harness integrated design method, comprising:

[0012] Bundle the cables of each high-importance system of the aircraft;

[0013] Bundle the cables of the core equipment in each aircraft's generally important system;

[0014] Integrate the cables interconnected with the core equipment in each general importance system into the wiring harness of the corresponding core equipment;

[0015] Incorporate cables in each general importance system that are adjacent to and cross-linked with core equipment in other general importance systems into the wiring harness of the corresponding core equipment;

[0016] Bundle the unbundled cables of each system of general importance into adjacent bundles, or merge them into the bundles of adjacent core equipment;

[0017] Split and distribute the wiring harnesses with redundancy and electromagnetic compatibility requirements to obtain the initial wiring harnesses;

[0018] Design the initial routing paths for each harness on the aircraft;

[0019] When the wiring harnesses cannot meet the redundancy isolation constraint, the electromagnetic compatibility isolation constraint, the path impedance constraint or the routing path constraint, adjust the wiring harnesses and / or the routing path.

[0020] According to at least one embodiment of the present application, in the above-mentioned aircraft wiring harness integrated design method, the high-importance system is a system on the aircraft that will affect the safe flight of the aircraft after its function fails;

[0021] The general importance system is a system on the aircraft that will not affect the safe flight of the aircraft after its function failure.

[0022] According to at least one embodiment of the present application, in the above-mentioned aircraft wiring harness integrated design method, the high-importance system includes the flight management system, flight control system, aircraft status perception system, and engine control system on the aircraft;

[0023] The generally important systems are the lighting system, communication system, radio frequency sensing system, infrared sensing system, data management system, and environmental control system on the aircraft.

[0024] According to at least one embodiment of the present application, in the above-mentioned aircraft wiring harness comprehensive design method, the design of the initial laying path of each wiring harness on the aircraft is specifically:

[0025] Use 3D wiring harness and duct design tools to build an aircraft internal channel occupancy model;

[0026] The aircraft internal channel occupancy model is imported into the 3D path planning tool, and the shortest routing path of each wiring harness is calculated as the routing path.

[0027] According to at least one embodiment of the present application, in the above-mentioned aircraft harness integrated design method, the three-dimensional harness pipeline design tool is CATIA

[0028] Software: The three-dimensional path planning tool is SeeTopology software.

[0029] According to at least one embodiment of the present application, in the above-mentioned aircraft wiring harness integrated design method, the redundancy isolation constraint includes that wiring harnesses with redundancy requirements cannot be laid in the same laying path;

[0030] The electromagnetic compatibility isolation constraint includes that the laying path of the wiring harness with electromagnetic compatibility requirements should be greater than the electromagnetic compatibility isolation distance;

[0031] The path impedance constraint includes that the effective length of the wiring harness laying path should not be greater than the length required by the cable impedance;

[0032] The routing path constraint includes that the effective diameter of the wire harness should not be larger than the effective size of the routing path.

[0033] According to at least one embodiment of the present application, the above-mentioned aircraft wiring harness integrated design method further includes:

[0034] Vector coding is performed on each cable, including the system to which the cable belongs, the importance of the system, redundancy, and electromagnetic compatibility information.

[0035] According to at least one embodiment of the present application, the above-mentioned aircraft wiring harness integrated design method further includes:

[0036] Design the initial process separation surface between each harness;

[0037] Adjust the wire harness and / or routing when the initial process separation surface between the wire harnesses cannot match the connector. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of the aircraft wiring harness comprehensive design method provided in an embodiment of the present application.

[0039] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0040] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0041] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0042] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0043] The following is combined with Figure 1 This application is described in further detail.

[0044] An aircraft wiring harness integrated design method, comprising:

[0045] Bundle the cables of each high-importance system of the aircraft;

[0046] Bundle the cables of the core equipment in each aircraft's generally important system;

[0047] Integrate the cables interconnected with the core equipment in each general importance system into the wiring harness of the corresponding core equipment;

[0048] Incorporate cables in each general importance system that are adjacent to and cross-linked with core equipment in other general importance systems into the wiring harness of the corresponding core equipment;

[0049] Bundle the unbundled cables of each system of general importance into adjacent bundles, or merge them into the bundles of adjacent core equipment;

[0050] Split and distribute the wiring harnesses with redundancy and electromagnetic compatibility requirements to obtain the initial wiring harnesses;

[0051] Design the initial routing paths for each harness on the aircraft;

[0052] When the wiring harnesses cannot meet the redundancy isolation constraint, the electromagnetic compatibility isolation constraint, the path impedance constraint or the routing path constraint, adjust the wiring harnesses and / or the routing path.

[0053] As for the aircraft wiring harness integrated design method disclosed in the above-mentioned embodiment, it can be understood by technicians in the field that it divides the aircraft system into a high-importance system and a general-importance system, and bundles the cables of the high-importance system separately to ensure the integrity of the functions of the high-importance system and facilitate maintenance. For the general-importance system, the bundling of the core equipment cables is taken as the center, and the cables cross-linked with it in the system are incorporated, as well as the cables cross-linked with it in other general-importance systems in the vicinity are incorporated, which can ensure the integrity of the core functions of the core equipment of the general-importance system to a certain extent, facilitate maintenance, and only break the relative integrity of the system functions to a certain extent, reduce the number of small wiring harnesses, and reduce the difficulty of laying on the aircraft.

[0054] As for the aircraft harness integration design method disclosed in the above-mentioned embodiment, it can be understood by technicians in the field that its design splits and distributes the harnesses with redundancy and electromagnetic compatibility requirements to obtain the initial harnesses. When splitting and distributing the harnesses of high-importance systems, it should still be ensured that the cables of high-importance systems are not mixed with the cables of other systems. When splitting and distributing the harnesses of general-importance systems, the relative integrity of the core functions of the core equipment should be ensured to avoid mixing with the cables of other core equipment. On this basis, the harnesses with redundancy and electromagnetic compatibility requirements are split and distributed, and the performance requirements of the harnesses for redundancy, electromagnetic compatibility, etc. are fully considered to achieve a balance between the function and performance of the harness integration.

[0055] For the aircraft wiring harness integrated design method disclosed in the above-mentioned embodiment, technical personnel in the field can also understand that its design is based on the initial wiring harness obtained by splitting and allocating the wiring harness with redundancy and electromagnetic compatibility requirements, and designs the initial laying paths of each wiring harness on the aircraft. When the redundancy isolation constraints, electromagnetic compatibility isolation constraints, path impedance constraints or laying path constraints cannot be met between the wiring harnesses, the wiring harness and / or laying path are adjusted. When adjusting the wiring harness, it should still be ensured that the cables of the high-importance system are not mixed with the cables of other systems, the relative integrity of the core functions of the core equipment of the general importance system should be maintained, and the requirements of the function and performance of the balanced bundle should be met.

[0056] In some optional embodiments, in the above-mentioned aircraft wiring harness integrated design method, the high-importance system is a system on the aircraft that will affect the safe flight of the aircraft after its function fails;

[0057] The general importance system is a system on the aircraft that will not affect the safe flight of the aircraft after its function failure.

[0058] In some optional embodiments, in the above-mentioned aircraft wiring harness integrated design method, the high-importance system includes the aircraft flight management system, flight control system, aircraft state perception system, engine control system, etc.;

[0059] The generally important systems include the lighting system, communication system, radio frequency sensing system, infrared sensing system, data management system, environmental control system, etc. on the aircraft.

[0060] In some optional embodiments, in the above-mentioned aircraft wiring harness comprehensive design method, the design of the initial laying path of each wiring harness on the aircraft is specifically:

[0061] Use 3D wiring harness and duct design tools to build an aircraft internal channel occupancy model;

[0062] The aircraft internal channel occupancy model is imported into the 3D path planning tool, and the shortest routing path of each wiring harness is calculated as the routing path.

[0063] In some optional embodiments, in the above-mentioned aircraft wire harness integrated design method, the three-dimensional wire harness pipeline design tool is CATIA software;

[0064] The three-dimensional path planning tool is SeeTopology software.

[0065] In some optional embodiments, in the above-mentioned aircraft harness integrated design method, the redundancy isolation constraint includes that harnesses with redundancy requirements cannot be laid in the same laying path to ensure the physical isolation of the redundancy between harnesses;

[0066] The electromagnetic compatibility isolation constraint includes that the laying path of the wiring harness with electromagnetic compatibility requirements should be greater than the electromagnetic compatibility isolation distance to ensure the physical isolation of the electromagnetic compatibility requirements between the wiring harnesses;

[0067] The path impedance constraint includes that the effective length of the wiring harness laying path should not be greater than the length required by the cable impedance to avoid affecting the performance of the device;

[0068] The routing path constraint includes that the effective diameter of the wire harness should not be larger than the effective size of the routing path, that is, the effective size of each routing path is limited, and the effective diameter of the wire harness laid thereon should not exceed its size limitation.

[0069] In some optional embodiments, the above-mentioned aircraft wiring harness comprehensive design method further includes:

[0070] Vectorized encoding is performed on each cable, including the system to which the cable belongs, the importance, redundancy, and electromagnetic compatibility information of the system. This can conveniently distinguish the system to which the cable belongs, the importance, redundancy, and electromagnetic compatibility of the system, and facilitate the cable bundle design.

[0071] In some optional embodiments, the above-mentioned aircraft wiring harness integrated design method further includes:

[0072] Design the initial process separation surface between each harness;

[0073] Adjust the wire harness and / or routing when the initial process separation surface between the wire harnesses cannot match the connector.

[0074] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0075] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A comprehensive design method for aircraft wiring harness, characterized in that: include: Bundle the cables of each high-importance system of the aircraft; Bundle the cables of the core equipment in each aircraft's generally important system; Integrate the cables interconnected with the core equipment in each general importance system into the wiring harness of the corresponding core equipment; Incorporate cables in each general importance system that are adjacent to and cross-linked with core equipment in other general importance systems into the wiring harness of the corresponding core equipment; Bundle the unbundled cables of each system of general importance into adjacent bundles, or merge them into the bundles of adjacent core equipment; Split and distribute the wiring harnesses with redundancy and electromagnetic compatibility requirements to obtain the initial wiring harnesses; Design the initial routing paths for each harness on the aircraft; When the wiring harnesses cannot meet the redundancy isolation constraint, electromagnetic compatibility isolation constraint, path impedance constraint or routing path constraint, adjust the wiring harnesses and / or routing paths; Design the initial process separation surface between each harness; Adjust the wire harness and / or routing when the initial process separation surface between the wire harnesses cannot match the connector.

2. The aircraft wiring harness integrated design method according to claim 1, characterized in that: The high-importance system is a system on the aircraft that will affect the safe flight of the aircraft if its function fails; The general importance system is a system on the aircraft that will not affect the safe flight of the aircraft after its function failure.

3. The aircraft wiring harness integrated design method according to claim 1, characterized in that: The high-importance systems include the flight management system, flight control system, aircraft status perception system, and engine control system on the aircraft; The generally important systems are the lighting system, communication system, radio frequency sensing system, infrared sensing system, data management system, and environmental control system on the aircraft.

4. The aircraft wiring harness integrated design method according to claim 1, characterized in that: The initial laying paths of each wiring harness on the aircraft are specifically designed as follows: Use 3D wiring harness and duct design tools to build an aircraft internal channel occupancy model; The aircraft internal channel occupancy model is imported into the 3D path planning tool, and the shortest routing path of each wiring harness is calculated as the routing path.

5. The aircraft wiring harness integrated design method according to claim 4, characterized in that: The three-dimensional wiring harness and pipeline design tool is CATIA software; The three-dimensional path planning tool is SeeTopology software.

6. The aircraft wiring harness integrated design method according to claim 1, characterized in that: The redundancy isolation constraint includes that wiring harnesses with redundancy requirements cannot be laid in the same laying path; The electromagnetic compatibility isolation constraint includes that the laying path of the wiring harness with electromagnetic compatibility requirements should be greater than the electromagnetic compatibility isolation distance; The path impedance constraint includes that the effective length of the wiring harness laying path should not be greater than the length required by the cable impedance; The routing path constraint includes that the effective diameter of the wire harness should not be larger than the effective size of the routing path.

7. The aircraft wiring harness integrated design method according to claim 1, characterized in that: Also includes: Vector coding is performed on each cable, including the system to which the cable belongs, the importance of the system, redundancy, and electromagnetic compatibility information.

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