A Modeling Method for Aeroengine Transition Process
An aero-engine and transition process technology, applied in instruments, geometric CAD, calculation, etc., can solve the problem that the transition process cannot be represented by a model, and achieve the effects of good dynamic performance, high precision and wide applicability
Active Publication Date: 2019-10-11
DALIAN UNIV OF TECH
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[0004] Aiming at the problem that the aero-engine controller in the prior art can only be designed for a mathematical model near a certain steady state, and the transition process cannot be expressed by a model, the present invention provides an aero-engine transition state modeling method based on model identification
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[0037] Below in conjunction with accompanying drawing, the present invention will be further described, and the research object of the present invention is a turbofan engine for a small unmanned aerial vehicle, and its transition process model is established as follows figure 1 As shown in the flowchart, the detailed design steps are as follows:
[0038] Step 1: Generate a set of sinusoidal excitation signal sequences {Δu} with amplitudes within [-1, 1] consisting of superimposed sinusoidal signals with different amplitudes and phases within 1-80Hz, where the signal used in the sample Such as figure 2 shown.
[0039] Step 2 to get the given amount of oil W fsi The relative conversion speed sequence of the high-pressure turbine under {y i1} and low-pressure turbine relative conversion speed sequence {y i2}, i=1,2,3...n
[0040] 2.1) Input a given amount of fuel W to the aero-engine fs1 , when the relative conversion speed of the high-pressure turbine of the aero-engine r...
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The invention provides a modeling method of the transient process of an aero-engine, and belongs to the field of modeling and simulating of the transient state of the aero-engine. By distinguishing a dynamic model of the aero-engine in different steady states and combining the dynamic model with a corresponding steady-state model, the transient process of the aero-engine is presented as a dynamic variable parameter model through methods of polynomial fitting and a least squares support vector machine. The approximate transient process of multiple discrete steady state points is improved, the dynamic characteristics are better, and the situation that by means of an existing method, error accumulation exists when modeling of the transient state is conducted through output accumulation is improved; meanwhile, single input multiple output is modeling through the method, universality is wider, modeling can be promoted to modeling of the transient process of multiple input multiple output aero-engine through proper adjustment.
Description
technical field [0001] The invention relates to the field of aero-engine transition state modeling and simulation, in particular to a method for establishing a mathematical model for aero-engine transition state control and display. Background technique [0002] In the field of aero-engine control, aero-engine transition state modeling has always been a difficult problem to solve. Establishing a mathematical model for the transition state can, on the one hand, make the control method used in the aero-engine transition state more targeted, and on the other hand can effectively Therefore, the present invention has great significance for the transition state modeling of the aero-engine. [0003] The literature shows that the existing aero-engine modeling is mostly aimed at modeling the steady-state operating point, such as the steady-state point pumping method that can only be designed for the white-box model. This type of method modeling is based on nonlinear calculation progr...
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IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 刘佟建孙希明马艳华汪锐
Owner DALIAN UNIV OF TECH