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Hybrid programming modeling method based on Rhapsody tool

A technology of mixed programming and modeling methods, which is applied in the modeling field of aviation gas turbine engine numerical control system, and can solve the problems such as the inability to realize the complete support of the concept prototype of aviation gas turbine engine numerical control system

Active Publication Date: 2021-04-13
中国航发控制系统研究所
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Problems solved by technology

[0004] The invention provides a hybrid programming modeling method based on the Rhapsody tool, which solves the problem in the related art that the complete support for the conceptual prototype of the numerical control system of the aviation gas turbine engine cannot be realized

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  • Hybrid programming modeling method based on Rhapsody tool
  • Hybrid programming modeling method based on Rhapsody tool

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Embodiment Construction

[0055] It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0056] In order to enable those skilled in the art to better understand the solutions of the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only Embodiments of some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0057] It should be noted that the terms "f...

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Abstract

The invention relates to the technical field of modeling of numerical control systems of aviation gas turbine engines, and particularly discloses a hybrid programming modeling method based on a Rhapsody tool, which comprises the following steps: creating a Harmony project according to the Rhapsody tool; creating at least two functional blocks under the Harmony project according to the Rhapsody tool, whereindata interaction can be carried out between the functional blocks, and each functional block can achieve a function different from that of other functional blocks; establishing a Simulink model, wherein the Simulink model can automatically generate a code; establishing a dll project according to a code automatically generated by the Simulink model, and generating a dll file; and enabling the function block to acquire interaction demand parameters with other function blocks, and call the matched dll file according to the interaction demand parameters. The hybrid programming modeling method based on the Rhapsody tool provided by the invention can realize complete support for the concept prototype of the numerical control system of the aviation gas turbine engine.

Description

technical field [0001] The invention relates to the technical field of modeling of an aviation gas turbine engine numerical control system, in particular to a hybrid programming modeling method based on a Rhapsody tool. Background technique [0002] The development of numerical control system for aviation gas turbine engine belongs to a field of multidisciplinary integration, high complexity and strong technical innovation. Constructing the numerical control system model of aerogas turbine engine by formal graphical modeling language is the main method adopted in the design of numerical control system. In the content demonstration and scheme design stages of the model, both rely on well-supported modeling tools and modeling languages. [0003] At present, only the cooperation of multiple modeling languages / tools can realize the complete support for the concept prototype of the aviation gas turbine engine numerical control system. Contents of the invention [0004] The in...

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Application Information

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IPC IPC(8): G06F8/34G06F8/30
CPCG06F8/34G06F8/315
Inventor 田迪季春生汪松卢俊杰俞刚贾盼盼
Owner 中国航发控制系统研究所
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