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A Modeling Method for Steady-state Model of Scramjet Engine

A technology of scrambling and steady-state model, applied in geometric CAD, special data processing applications, etc., can solve the problems of low model accuracy, low real-time performance, long calculation time, etc., and achieve good real-time performance and simplified two-dimensional flow relationship. , high precision effect

Inactive Publication Date: 2020-04-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

The digital simulation model mainly realizes parameter calculation through characteristic map interpolation, empirical formula and other methods. This type of model has the advantages of simple calculation and high real-time performance, but often ignores the influence of the flow field in the component on the component characteristics, making the model accuracy relatively low
The CFD simulation model achieves parameter calculation through flow field calculation. This type of model can clearly reflect the flow field characteristics in the component, and the model accuracy is high, but the calculation time is long and the real-time performance is relatively low.

Method used

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  • A Modeling Method for Steady-state Model of Scramjet Engine
  • A Modeling Method for Steady-state Model of Scramjet Engine
  • A Modeling Method for Steady-state Model of Scramjet Engine

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Embodiment Construction

[0050] Aiming at the deficiencies of the prior art, the present invention converts the two-dimensional airflow into one-dimensional airflow calculation by establishing a control body at the outlet section of the inlet duct and the isolation section, so as to improve the real-time calculation of the model; and further adopts the reference temperature method for further calculation. The airway boundary layer is corrected. At the same time, based on the difference of the airflow in the isolation section according to the back pressure of the isolation section, the present invention further divides the working state of the isolation section into a weak shock wave working state and an oblique shock wave working state for modeling respectively. And considering the viscosity of the isolation section, the boundary layer correction is carried out.

[0051] The reference temperature method is to approximate the boundary layer of the compressible fluid to the incompressible flat plate boun...

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Abstract

The invention discloses a modeling method for a scramjet steady-state model. The invention converts the two-dimensional airflow into one-dimensional airflow for calculation by establishing a control body in the outlet section of the inlet port and the isolation section, so as to improve the real-time calculation of the model. At that same time, based on the airflow in the isolation section according to the difference of the back pressure of the isolation section, the isolation section work state is further divided into a weak shock wave working state and an oblique shock wave work state for modeling respectively, and the boundary layer correction is carried out considering the viscosity of the isolation section. Compared with the prior art, the modeling method of the invention can improvethe calculation precision of the scramjet, and simultaneously ensure the real-time calculation of the model.

Description

technical field [0001] The invention relates to a scramjet engine, in particular to a modeling method for a scramjet steady-state model, and belongs to the technical field of aeroengine control. Background technique [0002] A hypersonic vehicle (Hypersonic Vehicle) generally refers to an aircraft with an incoming flow Mach number greater than 5. It is favored by countries all over the world with its own speed advantage and defense breaking ability. In order to make hypersonic aircraft have better performance, its power plant usually adopts scramjet engine. In the early stage of aircraft design, the scramjet model should meet the requirements of real-time calculation while achieving a certain accuracy, so as to facilitate the design of the control system. [0003] Aiming at the modeling and simulation of scramjet, many studies have been carried out at home and abroad. [Joseph W.Connolly, George Kopasakis, Daniel Paxson, et al. Nonlinear dynamic modeling and controls devel...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17
CPCG06F30/17
Inventor 席志华刘明磊张海波叶东鑫陈名扬高远
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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