CATIA-based aircraft integrated control board automatic generation design method

Abstract

The invention discloses a CATIA (computer-graphics aided three-dimensional interactive application)-based automatic generation and design method for an aircraft integrated control board. The design method is realized based on CATIA software, and specifically comprises the following steps: S1, constructing a general basic model of the CPA: constructing the general basic model of the CPA according to modeling parameters; s2, constructing a super copy of the structural features for switch installation; s3, modifying the key parameters according to the CPA needing to be designed; s4, based on the modified key parameters, updating the CPA general basic model to obtain a CPA model meeting design requirements; and S5, the super copy is used for conducting structural detail modification on the CPA model meeting the design requirement, and then all design of the CPA model can be completed. The method has the beneficial effects that repeated design work is reduced, the design efficiency is improved, and the design error rate is reduced.

Description

Technical Field

[0001] The present invention relates to the field of CPA, and in particular, to an automatic generation design method for an aircraft integrated control panel based on CATIA. Background Art

[0002] An aircraft integrated control panel (CPA, Control Panel Assemblies) is an interactive device for pilots to control an aircraft and is widely used on aircraft. When designing such products, designers often face a wide variety of types with different layouts, resulting in a large and complex design workload, thus prolonging the design cycle. Summary of the Invention

[0003] The object of the present invention is to solve the problem of a relatively large design workload of aircraft CPA in the prior art, and to provide a new automatic generation design method for an aircraft integrated control panel based on CATIA.

[0004] To achieve the above object, a technical solution provided by the present invention is: an automatic generation design method for an aircraft integrated control panel based on CATIA, the design method is implemented based on CATIA software, and the design method includes:

[0005] Step S1, constructing a general basic model of the CPA: constructing a general basic model of the CPA according to modeling parameters; the modeling parameters include: key parameters and general parameters; wherein, the key parameters and the general parameters establish a mapping through a functional relationship;

[0006] Step S2, constructing a super copy of the structural features for switch installation;

[0007] Step S3, modifying the key parameters according to the CPA to be designed;

[0008] Step S4, updating the general basic model of the CPA based on the modified key parameters, that is, obtaining a CPA model that meets the design requirements; and,

[0009] Step S5, using the super copy to perform structural detail modification on the CPA model that meets the design requirements, and the entire design of the CPA model can be completed.

[0010] Compared with the prior art, the beneficial effects of the present invention are at least: by extracting key parameters, establishing a function mapping, and integrating the intermediate steps of modeling into the function equation to achieve the purpose of automatic model generation. At the same time, due to the standardization of general parameters in the function, the deviation that may occur in the artificial operation and artificial definition process is avoided, and the probability of design errors is also greatly reduced. Description of the Drawings

[0011] Figure 1Variables and variable annotations in the present invention.

[0012] Figure 2 Function mapping in the present invention.

[0013] Figure 3 Initial digital model generated by the function mapping in the present invention.

[0014] Figure 4 Target digital model automatically generated after modifying the variables in the present invention.

[0015] Figure 5 Super copy for switch installation features in the present invention. Detailed implementation manners

[0016] The present invention will be further described in detail below through specific implementation manners in conjunction with the accompanying drawings. It should be noted here that the description of these implementation manners is used to help understand the present invention, but does not constitute a limitation to the present invention. In addition, the technical features involved in the various implementation manners of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0017] Please refer to Figure 1 , which shows an automatic generation design method for an aircraft integrated control panel based on CATIA. The design method is implemented based on the CATIA software. The specific steps of the design method include:

[0018] Step S1, constructing a general basic model of CPA: Construct a general basic model of CPA according to the modeling parameters. The modeling parameters include: key parameters and general parameters. Among them, the key parameters and the general parameters are mapped through a functional relationship, that is, the key parameters are independent variables, and the general parameters are dependent variables.

[0019] The list of key variables and general variables is as follows:

[0020] Table 1 Variable comparison table

[0021]

[0022]

[0023] The key parameters include: L, W, δpad, case hight, distance of hole spacing, numberof hole.

[0024] The functional relationship:

[0025] Formula 1:

[0026] if W≤50 offset-W=10;

[0027] else if 50 < W ≤ 100, offset - W = 15

[0028] else if W > 100, offset - W = W / 4.

[0029] Annotation 1: Define the positions of the shell boundary and rib in the width direction within different width ranges.

[0030] Formula 2:

[0031] if L ≤ 50, offset - W = 10;

[0032] else if 50 < L ≤ 100, offset - L = 15

[0033] else if L > 100, offset - L = L / 4.

[0034] Annotation 2: Define the positions of the shell boundary and rib in the length direction within different length ranges.

[0035] Formula 3: hight - Connector install pad = case hight + δpad - δConnector installpad

[0036] Annotation 3: Define the distance between the connector installation plate and the panel

[0037] Formula 4: distance of hole = (distance of hole spacing * number of hole) / 2

[0038] Annotation 4: Define the position of the screw lock hole

[0039] Formula 5: L - case = L - offset - L + 0.2

[0040] Annotation 5: Define the shell length

[0041] Formula 6: W - case = W - offset - W + 0.2

[0042] Annotation 6: Define the shell width

[0043] Other process functions are not shown here.

[0044] Step S2, construct a super copy of the structural features for switch installation: encapsulate the structural features for switch installation using the super copy function of CATIA software.

[0045] Step S3: Modify the key parameters according to the CPA to be designed.

[0046] Step S4: Update the CPA general basic model based on the modified key parameters, i.e., obtain the CPA model meeting the design requirements.

[0047] Step S5: Use the super copy to modify the structural details of the CPA model meeting the design requirements, and thus complete the entire design of the CPA model.

[0048] For the structural characteristics of various CPAs, the key parameters and general parameters in the CPA design process are abstracted, and a mapping is established through a functional relationship. Based on the above steps, the complex process data in the design process can be abstracted into equations. By only changing a small amount of initial data, the final data can be calculated through the operations of the function to generate the required model, avoiding manual modeling and calculation by designers.

[0049] By extracting the key parameters and establishing a function mapping, the intermediate steps of modeling are integrated into the function equation to achieve the purpose of automatic model generation. At the same time, because the general parameters are standardized in the function, the deviations that may occur in the manual calculation and manual definition processes are avoided, and the probability of design errors is also greatly reduced.

[0050] Among them, CATIA is an interactive CAD / CAE / CAM system developed by Dassault Systemes in France.

[0051] The above only expresses the implementation modes of the present invention, and its description is relatively specific and detailed, but it cannot be understood as a limitation to the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the appended claims.

Claims

1. An automatic generation design method for an aircraft integrated control panel based on CATIA, characterized in that The design method is implemented based on the CATIA software, and the design method includes: Step S1, constructing a general basic model of the CPA: constructing a general basic model of the CPA according to the modeling parameters; the modeling parameters include: key parameters and general parameters; wherein, the key parameters and the general parameters establish a mapping through a functional relationship; Step S2, constructing a super copy of the structural features for switch installation; Step S3, modifying the key parameters according to the CPA to be designed; Step S4, based on the modified key parameters, updating the general basic model of the CPA, that is, obtaining a CPA model meeting the design requirements; and, Step S5, using the super copy to perform structural detail modification on the CPA model meeting the design requirements, and thus completing the entire design of the CPA model.

2. The automatic generation design method of the aircraft integrated control panel based on CATIA according to claim 1, characterized in that In Step S2, the structural features for switch installation are encapsulated using the super copy function of the CATIA software.

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