A simulation method based on SIMULINK for a supersonic inlet

Author

Bao, Wen ; Yao, Zhaohui ; He, Baocheng ; Chang, Juntao

Author_Institution

Harbin Inst. of Technol.

fYear

2006

fDate

19-21 Jan. 2006

Lastpage

127

Abstract

This paper has developed a computational platform of a supersonic inlet with variable geometry, using MATLAB/SIMULINK. A method based on this for simulation of a complicated model has been presented. The correctness and reliability of the new method have been testified by simulating the stationary flow fields of an inlet under back pressure gust and gust of parameters of incoming air flow. Based on the method, the dynamic behavior of the terminal normal shock wave in the inlet has been obtained by carrying out a simulation of the object model of an inlet, and it´s dynamic and stationary characteristics have also been obtained. A complicated distributed-parameter problem of a ID supersonic inlet has been transformed to a OD problem which reduced the inlet model and solved the concentrative-parameter difficult that could never be realized in system analysis and controller design. The work of the study has much significance for future work

Keywords

aerodynamics; aerospace propulsion; aerospace simulation; shock waves; supersonic flow; MATLAB; SIMULINK; back pressure gust; stationary flow fields; supersonic inlet; terminal normal shock wave; variable geometry; Computational fluid dynamics; Computational geometry; Computational modeling; Control system synthesis; Differential equations; Electric shock; Engines; Mathematical model; Partial differential equations; Pressure control;

fLanguage

English

Publisher

ieee

Conference_Titel

Systems and Control in Aerospace and Astronautics, 2006. ISSCAA 2006. 1st International Symposium on

Conference_Location

Harbin

Print_ISBN

0-7803-9395-3

Type

conf

DOI

10.1109/ISSCAA.2006.1627595

Filename

1627595