Modeling method of aviation gas turbine engine based on flight parameter data identification
A technology of aviation gas turbine and modeling method, applied in the field of modeling, aviation gas turbine engine modeling based on flight parameter data identification, can solve problems such as difficult aviation gas turbine engine modeling, complex characteristics of aviation gas turbine engine, etc. Achieve the effect of facilitating the design of engine control parameters, shortening the design cycle, and being easy to implement
Active Publication Date: 2022-03-04
中国航发控制系统研究所
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However, the characteristics of aviation gas turbine engines are complex, and the traditional least squares method is also difficult to carry out multi-parameter, multi-range, high-precision modeling of aviation gas turbine engines.
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[0068] The present invention will be further described below in conjunction with specific drawings and embodiments.
[0069] In order to directly obtain the model of the aviation gas turbine engine through the flight parameter data, the design cycle of the aviation gas turbine engine control system can be effectively shortened, and the control effect is significantly improved. The modeling method of the present invention includes the following steps:
[0070] Step 1, establish the model of aviation gas turbine engine, the model of described aviation gas turbine engine comprises integration link 100, proportional link 200 and addition link 300, the input of aviation gas turbine engine model is fuel supply WFr, aviation gas turbine engine model The output is the conversion speed N1r of the low-pressure rotor, the fuel supply WFr, and the fuel supply WFr_S at different state points output by the proportional link 200. After the addition link 300, the input dWFr of the integral lin...
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The invention relates to an aviation gas turbine engine modeling method based on flight parameter data identification. The model of the aviation fuel turbine engine uses a first-order integral link; in order to make the flight parameter data truly reflect the information of different states of the engine, it is necessary The parameter data is processed, and the steady-state data and dynamic data during the flight are separated and identified separately; in the model identification stage, the least squares support vector machine algorithm is used to make the output realistically approach the real flight data; by comparing the flight parameter data and model output, when the error meets the requirements, the established model of the aviation fuel turbine engine and the identification results are feasible, that is, the model of the aviation gas turbine engine can be obtained directly from the flight parameter data, which is easy to implement and convenient for the design of engine control parameters, and can be effectively The design cycle of the aviation gas turbine engine control system is shortened, and the control effect is significantly improved.
Description
technical field [0001] The invention relates to a modeling method, in particular to an aviation gas turbine engine modeling method based on flight parameter data identification, belonging to the technical field of aeroengines. Background technique [0002] The development of aviation gas turbine engine numerical control system belongs to a field of multidisciplinary integration, high complexity, and strong technological innovation. Among them, the aviation gas turbine engine model can be used for engine performance analysis, control law research, sensor analysis redundancy and engine fault diagnosis, etc. aspect. The modeling methods of aviation gas turbine engines are mainly divided into component method and data identification method. The data identification method does not need to determine the complex characteristics of the system and is more concerned. [0003] With the increase of data collected by the flight reference system, the application of flight reference data ...
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IPC IPC(8): G06F30/20
Inventor 季春生田迪柳亚冰乔伯真张腾飞
Owner 中国航发控制系统研究所