세미나 및 이벤트
Helicopter Performance, Loads and Vibration
세미나 날짜
2003-05-20
작성자
정기훈
작성일
2003-05-20
조회
1307
1. 제 목 : Helicopter Performance, Loads and Vibration
2. 연 사 : 여 현 수 박사
Research Scientist
Raytheon ITSS, Army/NASA Rotorcraft Division
NASA Ames Research Center, Moffett Field, California
3. 일 시 : 2003년 5월 23일 (금) 16:00 - 17:00
4. 장 소 : 서울대 신공학관(301동) 117호 세미나실
5. 내 용 :
- Performance
Performance of the UH-60 Black Hawk helicopter with both standard and advanced rotors are investigated. Flight test measurements are compared with calculations obtained using the comprehensive rotorcraft analysis CAMRAD II.
- Loads
Blade section normal force and flap bending moment were investigated for UH-60 Black Hawk helicopter rotor operating at transition speed. The measured data from both flight and full-scale wind tunnel tests are compared with calculations obtained using the comprehensive rotorcraft analysis CAMRAD II.
- Vibration
A comprehensive vibration analysis of a coupled rotor/fuselage system for a two-bladed teetering rotor was developed for the comprehensive rotorcraft analysis UMARC. The elastic line and detailed 3-D NASTRAN finite element models of the AH-1G helicopter airframe are integrated into the elastic rotor finite element model. Analytical predictions of rotor control angles, blade loads, hub forces, and vibration are compared with AH-1G Operation Load Survey flight test data.
6. 약력 : B.S. 서울대 항공우주공학과 (1992. 2)
M.S. 서울대 항공우주공학과 (1994. 2)
Ph.D. University of Maryland, Aerospace Engineering (1999.8)
Research Associate, University of Maryland (1999. 6. 9)
Research Scientist, NASA Ames Research Center (1999.9~현재)
7. 문 의 : 기계항공공학부 김 승 조 교수 (☏ 880-7388)
2. 연 사 : 여 현 수 박사
Research Scientist
Raytheon ITSS, Army/NASA Rotorcraft Division
NASA Ames Research Center, Moffett Field, California
3. 일 시 : 2003년 5월 23일 (금) 16:00 - 17:00
4. 장 소 : 서울대 신공학관(301동) 117호 세미나실
5. 내 용 :
- Performance
Performance of the UH-60 Black Hawk helicopter with both standard and advanced rotors are investigated. Flight test measurements are compared with calculations obtained using the comprehensive rotorcraft analysis CAMRAD II.
- Loads
Blade section normal force and flap bending moment were investigated for UH-60 Black Hawk helicopter rotor operating at transition speed. The measured data from both flight and full-scale wind tunnel tests are compared with calculations obtained using the comprehensive rotorcraft analysis CAMRAD II.
- Vibration
A comprehensive vibration analysis of a coupled rotor/fuselage system for a two-bladed teetering rotor was developed for the comprehensive rotorcraft analysis UMARC. The elastic line and detailed 3-D NASTRAN finite element models of the AH-1G helicopter airframe are integrated into the elastic rotor finite element model. Analytical predictions of rotor control angles, blade loads, hub forces, and vibration are compared with AH-1G Operation Load Survey flight test data.
6. 약력 : B.S. 서울대 항공우주공학과 (1992. 2)
M.S. 서울대 항공우주공학과 (1994. 2)
Ph.D. University of Maryland, Aerospace Engineering (1999.8)
Research Associate, University of Maryland (1999. 6. 9)
Research Scientist, NASA Ames Research Center (1999.9~현재)
7. 문 의 : 기계항공공학부 김 승 조 교수 (☏ 880-7388)
