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강경태,Kang, Kyoung-Tai 한국군사과학기술학회 2008 한국군사과학기술학회지 Vol.11 No.4
Missile operating at supersonic conditions experiences considerable high temperature environments that is caused by aerodynamic heating as a result of the temperature gradient through boundary layer that surrounds it. This is one of important problems to the designer due to temperature limitation of structural materials. Because prediction of aerodynamic heating on missile needs unsteady calculation according to a flight trajectory, approximate method approach is efficient at design stage. In this paper, improved aerodynamic heating analysis scheme is introduced, which calculates heat flow and temperature by simple pressure field prediction on a missile body and fin. The prediction results are compared with measured data and MINIVER codes results.
움직이는 격자계를 이용한 유도탄의 비정상 분리 유동해석
강경태,이복직,안창수,Kang, Kyoung-Tai,Lee, Bok-Jik,Ahn, Chang-Soo 한국군사과학기술학회 2007 한국군사과학기술학회지 Vol.10 No.2
Missile staging and airframe separation simulation were performed by using a numerical technique for simulating the dynamics of multiple moving bodies. A 6DOF model is fully integrated into the CFD solution procedure to determine the body dynamics. Chimera grid technique offered efficient CFD simulation of multiple moving bodies. Through this simulation the safety of deployed staging and airframe separation mechanism was verified.