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Thermo-Mechanical Analysis of Continuous-Adjustment Thruster using Explosion Pressure  

Kim, Kyung-Sik ((주)한화 구미사업장 개발2부)
Kwon, Young-Doo (경북대학교 기계공학부)
Kwon, Soon-Bum (경북대학교 기계공학부)
Gil, Hyuck-Moon (경북대학교 기계공학부)
Publication Information
Journal of the Computational Structural Engineering Institute of Korea / v.24, no.6, 2011 , pp. 699-705 More about this Journal
Abstract
High-maneuver missile is a projectile which demands a strong momentum at short time. To produce a necessary thrust for the flight, the gas of high temperature and pressure is generated through explosive combustion of solid propellant, and a great thrust can be obtained by expanding this high temperature and pressure gas. Although the operating time of a rocket motor is less than a few seconds, a failure of part or ablation near the throat of nozzle may take place during the expansion of high temperature and pressure gas for great thrust. In other words, for the precise control of a missile an exact stress analysis considering both, the thermal stress caused by the heat transfer between combustion gas and wall, and the mechanical stress caused by the pressure change in the flow, should be considered first. In this connection, this study investigated the safety, as a point of view of stress and melting point of the material, of the pre-designed thrust generating structure which is subjected to high temperature and pressure as a function of motor operating time.
Keywords
Thermal stress; Thermo-mechanical analysis; Finite Elements Method; Melting point; Heat transfer coefficient; Rocket motor;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
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