C-사업 유도탄의 카나드 및 자유회전미익의 플러터 해석 (Flutter Analyses of CANARD and Roll Free Fin Assembly for C-Project Guided Missile)

서지정보

· 발행기관 : 한국방위산업학회
· 수록지 정보 : 한국방위산업학회지 / 17권 / 1호 / 127 ~ 146페이지
· 저자명 : 정상영, 장종진, 박민수

초록

This paper presents the flutter analysis results of CANARD and tail fin assembly for the C-Project (a system development project lead by Hanwha Co.). The CANARD includes an actuator and actuator backup structure. The Roll Free Fin (RFF) assembly includes a hub and fins modeled by MSC PATRAN with FEM. The stiffness of CANARD was corrected as the consequence of the static stiffness load test of the actuator group. Flutter speeds were calculated with a V-g plot. Using the flutter speeds calculated for several altitudes (density) and flight conditions (Mach number), the flutter boundary curves for CANARD and RFF assembly were easily drawn with Excel spreadsheets. It was possible to draw the analytical flutter characteristics of CANARD and RFF of project guided missile with the calculated results. The flutter margins of CANARD and RFF were high enough. However, the flutter margins of RFF showed zero frequency flutter at low speed. It is most likely that this phenomenon is caused by the roll free fin assembly, but not because of the flutter or divergence.

영어초록

This paper presents the flutter analysis results of CANARD and tail fin assembly for the C-Project (a system development project lead by Hanwha Co.). The CANARD includes an actuator and actuator backup structure. The Roll Free Fin (RFF) assembly includes a hub and fins modeled by MSC PATRAN with FEM. The stiffness of CANARD was corrected as the consequence of the static stiffness load test of the actuator group. Flutter speeds were calculated with a V-g plot. Using the flutter speeds calculated for several altitudes (density) and flight conditions (Mach number), the flutter boundary curves for CANARD and RFF assembly were easily drawn with Excel spreadsheets. It was possible to draw the analytical flutter characteristics of CANARD and RFF of project guided missile with the calculated results. The flutter margins of CANARD and RFF were high enough. However, the flutter margins of RFF showed zero frequency flutter at low speed. It is most likely that this phenomenon is caused by the roll free fin assembly, but not because of the flutter or divergence.

참고자료

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