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Rapid development method for aero-engine control system product

A technology of aero-engine and control system, which is applied in research and development, and in the field of aero-engine control system development. It can solve problems such as long iteration cycle, many design constraints, and difficult processing, so as to shorten the development cycle, reduce the development cycle and cost, and improve iteration. efficiency effect

Inactive Publication Date: 2020-03-10
中国航发控制系统研究所
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Problems solved by technology

[0002] The development of an aero-engine is a very complex system engineering. Due to the complexity of the control objects and the diversity of control parameters, the system-level architecture such as the control system still faces many design constraints, difficult processing, and iterative problems during the development process. Issues such as long cycle times restrict the iterative maturity of technology verification

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  • Rapid development method for aero-engine control system product

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Embodiment Construction

[0037] The present invention will be further described below in conjunction with specific drawings and embodiments.

[0038] Such as figure 1 Shown: In order to greatly improve the efficiency of the complex product development of the aero-engine control system, the development method of the present invention comprises the following steps:

[0039] Step 1, according to the functional requirements of the mechanical hydraulic device of the aero-engine control system, establish a one-dimensional architecture digital model of the aero-engine control system;

[0040] Specifically, the functional requirements include fuel supply characteristics or margin control within the flight envelope, etc. When establishing the one-dimensional architecture digital model of the aeroengine control system, first use the SysML software tool to establish the functional requirements model, and then combine the functional requirements model Design the key physical parameters, and use the AMESim softwa...

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Abstract

The invention relates to a rapid development method for an aero-engine control system product. In the rapid research and development iterative technology method based on combination of digital model driving and an SLM additive manufacturing technology, by establishing an efficient forward research and development mode of additive manufacturing enabling, an design-simulation-manufacturing-verification-authentication integrated iterative process and a technical path are broken through, and optimal development and implementation of functions and performance of aero-engine control system productsare achieved. The development period and cost of the product are greatly reduced, efficient seamless transmission of a digital model of a complex product can be achieved through model driving, the product optimization design iteration efficiency is greatly improved, and the development period is shortened by one time or above; the design and implementation of the additive manufacturing enable canachieve the effect that the comprehensive weight of the product is reduced by more than 30%, and also solve the technical problem of last kilometer achieved by rapid trial production of a physical prototype of a complex product.

Description

technical field [0001] The invention relates to a development method, in particular to a rapid development method for aero-engine control system products, and belongs to the technical field of aero-engine control system development. Background technique [0002] The development of an aero-engine is a very complex system engineering. Due to the complexity of the control objects and the diversity of control parameters, the system-level architecture such as the control system still faces many design constraints, difficult processing, and iterative problems during the development process. Issues such as long cycle times restrict the iterative maturity of technology verification. In addition, weight is an important index for the development of aero-engines, and the weight of the control system accounts for about 15% to 20% of the weight of the engine. Therefore, reducing the weight of the engine control system is one of the important ways to improve the thrust-to-weight ratio of ...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G05B13/04B33Y50/02B22F3/105
CPCB33Y50/02G05B13/042B22F10/00B22F10/34B22F10/385B22F12/90B22F10/28B22F10/30Y02P10/25
Inventor 陈静周毅博侯伟杨志逸储松林王修专
Owner 中国航发控制系统研究所
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