CN108133093B - Automatic wiring method based on aircraft network decomposition structure - Google Patents
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Abstract
The invention belongs to the field of airplane EWIS wiring design. The automatic wiring design method based on the aircraft network decomposition structure comprises the following steps: step 1: designing a system principle, namely performing design data conversion based on a system Interface Control Document (ICD) and automatically generating an electrical principle model; step 2: designing airplane wiring, and automatically defining a physical wiring harness topology model based on the decomposition calculation of an airplane wiring network topology structure; and step 3: wiring installation design, namely establishing an airplane wiring network structure model and a segmented decomposition model of a wiring harness product based on space reservation design of an airplane wiring network structure; and 4, step 4: designing an airplane circuit, and automatically generating an airplane circuit model based on data synthesis of a system electrical principle model and a physical wiring harness topology model; and 5: and (4) designing a wiring harness product, and automatically generating a wiring harness product model based on the extraction of the topological data of the wiring harness three-dimensional physical model and the wiring harness wiring data in the airplane circuit model.
Description
Technical Field
The invention belongs to the field of airplane EWIS wiring design.
Background
The wiring design of the airplane EWIS system covers two main technical fields of airplane mechanical design and electrical design, generally comprises various design contents such as electrical equipment installation design, electrical principle design, wiring topology design, wiring installation design, circuit design, wiring harness product design and the like, and the design flow is very complex.
At present, wiring design of an airplane EWIS system needs to be developed under a three-dimensional mechanical design environment and an electrical design environment respectively, the software environments can provide a relatively perfect design means and a modeling method at a plurality of links in a wiring design process, but under the wiring design process of the current airplane EWIS system, various design data under the mechanical and electrical design software environment lack an effective technical approach for conversion and transmission according to the wiring design requirements of the EWIS, the wiring design process is very complicated, a large amount of manual repeated design work is needed, rapid and automatic wiring design cannot be realized, and the wiring design period and quality are seriously influenced, so that a brand new, effective and automatic airplane wiring design method needs to be established, and the quality and the efficiency of the wiring design of the airplane EWIS are improved.
Disclosure of Invention
Object of the Invention
The invention provides an automatic wiring method based on an aircraft network decomposition structure, which realizes effective conversion and transmission of wiring design data of an EWIS system in each design link and automatically designs aircraft wiring based on the decomposition structure of an aircraft wiring network according to the interface design requirement of a functional system.
Technical scheme
An automatic wiring method based on an aircraft network decomposition structure comprises the following steps:
step 1: designing a system principle, namely performing design data conversion based on a system Interface Control Document (ICD) and automatically generating an electrical principle model;
step 2: designing airplane wiring, and automatically defining a physical wiring harness topology model based on the decomposition calculation of an airplane wiring network topology structure;
and step 3: wiring installation design, namely establishing an airplane wiring network structure model and a segmented decomposition model of a wiring harness product based on space reservation design of an airplane wiring network structure;
and 4, step 4: designing an airplane circuit, and automatically generating an airplane circuit model based on data synthesis of a system electrical principle model and a physical wiring harness topology model;
and 5: and (4) designing a wiring harness product, and automatically generating a wiring harness product model based on the extraction of the topological data of the wiring harness three-dimensional physical model and the wiring harness wiring data in the airplane circuit model.
The step 1 specifically comprises the following steps:
the system ICD design 1 establishes an ICD database by taking an Interface Control Document (ICD) of an aircraft functional system as input; the system principle design 2 processes data in the ICD database, extracts system electrical equipment data and signal connection data among electrical equipment, generates a data exchange file in a standard XML format, imports an electrical design environment and automatically generates an electrical principle model of a functional system; and 3, the system logic interface principle design takes system electrical principle model data generated by the system principle design 2 as design input, defines a logic interface of the electrical equipment according to the logic attribute classification of an interface signal of the electrical equipment, and automatically generates a system logic interface principle model through data exchange.
The step 2 specifically comprises the following steps:
the wiring network topology design 4 defines an aircraft wiring network topology model by extracting electrical equipment data in a functional system in a database established by the ICD design 1 of the system and aircraft wiring network topology model data established by a wiring network space reservation design 8; the logic wiring design 5 carries out wiring design on logic signals in the system logic interface principle model generated by the system logic interface principle design 3, and automatically calculates logic paths of the logic signals in the aircraft wiring network topology; and (3) carrying out structural decomposition on the airplane wiring network according to the separation surface of the airplane body structure and the path and classification of the logic signal in the wiring network by the physical wiring harness topological design 6, and automatically calculating the physical path of the logic signal in the airplane network decomposition structure to form the physical wiring harness topological model definition.
The step 3 specifically comprises the following steps:
a wiring network space reservation design 8 establishes a structural model of the airplane wiring network in a three-dimensional mechanical design environment according to a space reservation design mode; the wiring harness segmented modeling design 9 takes a physical wiring harness topological model defined by the physical wiring harness topological design 6 as design input, and establishes a segmented 3D model of the physical wiring harness for carrying out aircraft wiring network structural decomposition according to the aircraft cabin in a three-dimensional mechanical design environment.
The step 4 specifically comprises the following steps:
the aircraft circuit diagram design 7 defines a physical wiring harness topology model by utilizing a system electrical principle model generated by the system principle design 2 and a physical wiring harness topology design 6, automatically calculates wiring data of electrical signals through data extraction and synthesis, generates a data exchange file in a standard XML format, and imports an electrical design environment to form an aircraft circuit model.
The step 5 specifically comprises the following steps:
the 3D wiring harness product design 10 directly refers to segmented 3D models of the wiring harness product, which are established in the wiring harness segmented modeling design 9, of each cabin of the airplane in a three-dimensional mechanical design environment, and the segmented 3D models are automatically combined to generate a 3D physical model of the wiring harness product; the 2D harness product 11 is designed to extract harness topology data from the harness 3D physical model generated by the 3D harness product design 10, flatten the harness in the electrical design environment, extract harness wiring data from the aircraft circuit model generated by the aircraft circuit diagram design 7, and automatically generate a 2D model of the harness product.
Advantageous effects
According to the interface design requirements of the functional system, the signal wiring design is automatically realized based on the aircraft network decomposition structure, the wire harness product is constructed, the conversion and the transmission of the wiring design data of each link in the wiring design process under different design environments are realized, the wiring design work of the EWIS system can be developed from top to bottom, the design period is shortened, the design quality is improved, and the method is a brand new and effective general technical means for the wiring design of the aircraft EWIS.
Drawings
Fig. 1 is a schematic diagram of the principle of the present invention.
Detailed Description
The invention relates to an automatic wiring method based on an aircraft network decomposition structure, which comprises the following steps of:
step 1: and (4) designing a system principle, and automatically generating an electrical principle model by performing design data conversion based on a system Interface Control Document (ICD).
The system ICD design 1 establishes an ICD database by taking an Interface Control Document (ICD) of an aircraft functional system as input; the system principle design 2 processes data in the ICD database, extracts system electrical equipment data and signal connection data among electrical equipment, generates a data exchange file in a standard XML format, imports an electrical design environment and automatically generates an electrical principle model of a functional system; and 3, the system logic interface principle design takes system electrical principle model data generated by the system principle design 2 as design input, defines a logic interface of the electrical equipment according to the logic attribute classification of an interface signal of the electrical equipment, and automatically generates a system logic interface principle model through data exchange.
Step 2: and (4) designing airplane wiring, and automatically defining a physical wiring harness topological model based on the decomposition calculation of the airplane wiring network topological structure.
The wiring network topology design 4 defines an aircraft wiring network topology model by extracting electrical equipment data in a functional system in a database established by the ICD design 1 of the system and aircraft wiring network topology model data established by a wiring network space reservation design 8; the logic wiring design 5 carries out wiring design on logic signals in the system logic interface principle model generated by the system logic interface principle design 3, and automatically calculates logic paths of the logic signals in the aircraft wiring network topology; and (3) carrying out structural decomposition on the airplane wiring network according to the separation surface of the airplane body structure and the path and classification of the logic signal in the wiring network by the physical wiring harness topological design 6, and automatically calculating the physical path of the logic signal in the airplane network decomposition structure to form the physical wiring harness topological model definition.
And step 3: and (3) wiring installation design, namely establishing an airplane wiring network structure model and a segmented decomposition model of a wire harness product based on the space reservation design of the airplane wiring network structure.
A wiring network space reservation design 8 establishes a structural model of the airplane wiring network in a three-dimensional mechanical design environment according to a space reservation design mode; the wiring harness segmented modeling design 9 takes a physical wiring harness topological model defined by the physical wiring harness topological design 6 as design input, and establishes a segmented 3D model of the physical wiring harness for carrying out aircraft wiring network structural decomposition according to the aircraft cabin in a three-dimensional mechanical design environment.
And 4, step 4: and (3) designing an airplane circuit, and automatically generating an airplane circuit model based on data synthesis of a system electrical principle model and a physical wiring harness topology model.
The aircraft circuit diagram design 7 defines a physical wiring harness topology model by utilizing a system electrical principle model generated by the system principle design 2 and a physical wiring harness topology design 6, automatically calculates wiring data of electrical signals through data extraction and synthesis, generates a data exchange file in a standard XML format, and imports an electrical design environment to form an aircraft circuit model.
And 5: and (4) designing a wiring harness product, and automatically generating a wiring harness product model based on the extraction of the topological data of the wiring harness three-dimensional physical model and the wiring harness wiring data in the airplane circuit model.
The 3D wiring harness product design 10 directly refers to segmented 3D models of the wiring harness product, which are established in the wiring harness segmented modeling design 9, of each cabin of the airplane in a three-dimensional mechanical design environment, and the segmented 3D models are automatically combined to generate a 3D physical model of the wiring harness product; the 2D harness product 11 is designed to extract harness topology data from the harness 3D physical model generated by the 3D harness product design 10, flatten the harness in the electrical design environment, extract harness wiring data from the aircraft circuit model generated by the aircraft circuit diagram design 7, and automatically generate a 2D model of the harness product.
Claims (1)
1. An automatic wiring method based on an aircraft network decomposition structure is characterized by comprising the following steps:
step 1: designing a system principle, namely, performing design data conversion based on a system interface control document ICD, and automatically generating an electrical principle model;
step 2: designing airplane wiring, and automatically defining a physical wiring harness topology model based on the decomposition calculation of an airplane wiring network topology structure;
and step 3: wiring installation design, namely establishing an airplane wiring network structure model and a segmented decomposition model of a wiring harness product based on space reservation design of an airplane wiring network structure;
and 4, step 4: designing an airplane circuit, and automatically generating an airplane circuit model based on data synthesis of a system electrical principle model and a physical wiring harness topology model;
and 5: designing a wire harness product, namely automatically generating a wire harness product model based on the extraction of topological data of a three-dimensional physical model of the wire harness and wire harness wiring data in an airplane circuit model;
the step 1 specifically comprises the following steps:
the system ICD design (1) establishes an ICD database by taking an interface control document of an airplane function system as input; the method comprises the following steps that (2) data in an ICD database are processed, system electrical equipment data and signal connection data among electrical equipment are extracted, a data exchange file in a standard XML format is generated, an electrical design environment is imported, and an electrical principle model of a functional system is automatically generated; the system logic interface principle design (3) takes system electrical principle model data generated by the system principle design (2) as design input, defines the logic interface of the electrical equipment according to the logic attribute classification of the interface signal of the electrical equipment, and automatically generates a system logic interface principle model through data exchange;
the step 2 specifically comprises the following steps:
the wiring network topology design (4) defines an airplane wiring network topology model by extracting system electrical equipment data in a database established by the system ICD design (1) and airplane wiring network topology model data established by the wiring network space reservation design (8); the logic wiring design (5) carries out wiring design on the logic signals in the system logic interface principle model generated by the system logic interface principle design (3), and automatically calculates the logic paths of all the logic signals in the airplane wiring network topology; the physical wiring harness topology design (6) carries out structural decomposition on the airplane wiring network according to the separation surface of the airplane body structure and the path and classification of the logic signal in the wiring network, automatically calculates the physical path of the logic signal in the airplane network decomposition structure, and forms the definition of a physical wiring harness topology model;
the step 3 specifically comprises the following steps:
a wiring network space reservation design (8) establishes a structural model of the airplane wiring network in a three-dimensional mechanical design environment according to a space reservation design mode; the wiring harness segmented modeling design (9) takes a physical wiring harness topological model defined by the physical wiring harness topological design (6) as design input, and establishes a segmented 3D model of the physical wiring harness for decomposing the airplane wiring network structure according to the airplane cabin in a three-dimensional mechanical design environment;
the step 4 specifically comprises the following steps:
the aircraft circuit diagram design (7) defines a physical wiring harness topology model by utilizing a system electrical principle model and a physical wiring harness topology design (6) which are generated by the system principle design (2), automatically calculates the wiring data of interface signals through data extraction and synthesis, generates a data exchange file in a standard XML format, and leads the data exchange file into an electrical design environment to form an aircraft circuit model;
the step 5 specifically comprises the following steps:
the 3D wire harness product design (10) directly refers to segmented 3D models of the wire harness product, which are established in the wire harness segmented modeling design (9) at each cabin of the airplane, in a three-dimensional mechanical design environment, and the segmented 3D models are automatically combined to generate a 3D physical model of the wire harness product; the 2D harness product (11) design extracts harness topological data from a harness 3D physical model generated by the 3D harness product design (10), flattens the harness in an electrical design environment, extracts harness wiring data from an aircraft circuit model generated by the aircraft circuit diagram design (7), and automatically generates a 2D model of the harness product.
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| CN110795830B (en) * | 2019-10-12 | 2023-03-14 | 中航通飞华南飞机工业有限公司 | Automatic design method for aircraft wire harness |
| CN114239142B (en) * | 2021-12-15 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Aircraft complex harness laying method, device, equipment, storage medium and product |
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