Numerical modelling of the thermo-mechanical response of a rocket motor to exhaust gases load

• Autorzy: Orłowska M. , Panas A. J. , Rećko K. , Żyluk A.
• Języki publikacji: EN

Abstrakty

EN

A numerical model for analysis of thermal and mechanical loads of a rocket motor has been developed. This model of a solid propellant motor corresponds to a short range, fast lunch and cruise type missile. It has been elaborated using the Finite Element Method (FEM) incorporated into commercial Comsol/M code. The experimental data on the thrust profile have been utilised to develop proper initial and boundary conditions for forgoing numerical calculations. The studies have been focused on the temperature and stress evolution within the case and nozzle section of the rocket engine. A special attention has been paid to the graphite insert of the rocket motor throat. The performed analyses proved effectiveness of the modelling methodology that will be applied to investigations of the modified motor performance.

Słowa kluczowe

EN

solid propellant rocket motors; thermo-elastic FEM analysis; nozzle thermal load

• Wydawca: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
• Czasopismo: Journal of Theoretical and Applied Mechanics
• Rocznik: 2014
• Tom: Vol. 52 nr 3
• Strony: 803--814
• Opis fizyczny: Bibliogr. 16 poz., rys., tab.

Twórcy

autor

Orłowska M.

• Military University of Technolgy, Faculty of Mechatronics and Aerospace, Warsaw, Poland

autor

Panas A. J.

• Military University of Technolgy, Faculty of Mechatronics and Aerospace, Warsaw, Poland and Air Force Institute of Technology, Warsaw, Poland

autor

Rećko K.

• Military University of Technolgy, Faculty of Mechatronics and Aerospace, Warsaw, Poland

autor

Żyluk A.

• Air Force Institute of Technology, Warsaw, Poland

Bibliografia

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