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Artificial intelligence-based method for establishing real time part level model of turbo shaft engine

A turboshaft engine, artificial intelligence technology, applied in special data processing applications, instruments, electrical digital data processing and other directions, can solve the problems of complex calculation process and poor real-time performance

Inactive Publication Date: 2014-10-15
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Application Information

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Problems solved by technology

However, due to its complex calculation process and poor real-time performance, it is restricted in airborne applications.

Method used

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  • Artificial intelligence-based method for establishing real time part level model of turbo shaft engine
  • Artificial intelligence-based method for establishing real time part level model of turbo shaft engine
  • Artificial intelligence-based method for establishing real time part level model of turbo shaft engine

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Embodiment Construction

[0071] The present invention will be further described below in conjunction with the accompanying drawings.

[0072] This specific implementation mode takes the T700 engine component-level mathematical model as an example. The simulation model has been verified by a large number of simulations and can accurately reflect the dynamic and static characteristics of the engine.

[0073] The artificial intelligence-based real-time component-level model calculation process of the turboshaft engine of the present invention is as follows: figure 1 shown. The specific establishment process is as follows:

[0074] Step A. On the component-level model of the rated turboshaft engine, the Newton-Raphson iterative method is used to solve the dynamic process balance equation, and the initial residual error of the balance equation before the iterative operation of the Newton-Raphson algorithm is collected and the guesswork of the balance equation after the iterative operation is converged V...

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Abstract

The invention discloses an artificial intelligence-based method for establishing a real time part level model of a turbo shaft engine. A method for solving a co-working equation of the turbo shaft engine is solved by adopting intelligent mapping. The method comprises the steps of taking a part co-working balance equation initial residual as an intelligent mapping network input and a balance equation guess value correction as a network output, training an extreme learning machine (ELM), and adopting an ADE (adaptive difference evolution) algorithm to optimize parameters of the extreme learning machine, thus improving the network mapping degree. An adaptive zoom factor is adopted in the ADE algorithm, and the optimizing capacity of a DE algorithm is improved. Results show that the maximal model error of the artificial intelligence-based method for establishing the real time part level model of the turbo shaft engine is one third of that of a one-shot algorithm, and the model operation time consumption is one third of the one-shot algorithm.

Description

technical field [0001] The invention belongs to the field of system control and simulation in aerospace propulsion theory and engineering, and in particular relates to an artificial intelligence-based method for establishing a real-time component-level model of a turboshaft engine. Background technique [0002] The mathematical model of an aero-engine plays a very important role in its development, control, health management, and performance optimization. Carrying out numerical simulation or semi-physical simulation tests with mathematical models instead of real engines is an effective means to reduce engine costs and improve test safety. Therefore, the mathematical model of the engine has always been the research focus of the aviation powers in the world. As early as the 1950s, the United States began the research on the nonlinear mathematical model of the engine, and established the single-shaft turbojet and turboprop engine models, and the research on the mathematical mo...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 李秋红焦洋聂友伟任冰涛廖光煌
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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