http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
후퇴각 날개끝이 있는 헬리콥터 로터깃의 회전주파수 해석
황호연,정건교 한국소음진동공학회 2000 소음 진동 Vol.10 No.2
To reduce the drag rise on the advancing helicopter rotor blade tips, the tip of the blade is modified to have sweep, anhedral and pretwist. The equations of motion of rotor blade with these tip angles were derived using Hamilton principle, programmed using FORTRAN and named as ARMDAS(Advanced Rotorcraft Multidisplinary Design and Analysis System). Rotating frequency analysis of rotor blades with swept tipe was performed that is necessary in conceptual and preliminary design phases of the helicopter design. Vibration analysis of non-rotating blades was also accomplished and compared with MSC/NASTRAN resutls for the basis of comparison with the vibration test data. The rotating frequency analysis of blades with an actual rotor blade data was also performed to verify coded program and to check the possibility of a resonance of an actual rotor blade at the specific rotating speed.
황호연 울산대학교 1997 공학연구논문집 Vol.28 No.2
중형항공기 전기체 구조물의 진동 해석 및 비행중 동적 불안정성인 플러터 해석이 수행되었다. 구조물은 보(beam) 형태의 유한 요소로 모델링 하였으며, 플러터 해석을 위한 공기력은 준정상(Quasi-steady) 패널 방법을 사용하였다. 구조물의 대칭, 역대칭 조건에 대해 진동 모드를 해석하였으며, 이를 토대로 플러터 해석을 수행하였다. 해석 소프트웨어로는 러시아에서 개발한, 항공기 구조 종합해석 프로그램 IMAD를 사용하였다. Vibration and flutter analyses that are dynamic instability caused by the increase of the elastic airplane flight speed were performed for the 100 seated aircraft. Beam type finite elements were used for the structural modeling and the Quasi-steady panel method was used in the aerodynamic calculation for flutter analyses. Vibration and flutter analyses are based on the symmetric and anti-symmetric vibration modes of an aircraft. IMAD (Interactive Multidisciplanary Aircraft Design) software that was developed by Russian scientists was used for these analyses.