인문학
사회과학
자연과학
공학
의약학
농수해양학
예술체육학
복합학
DBpia AI
AI 에이전트
AI 아이디어
AI 리더
AI 뷰어
Citeasy
크롬 서지관리 다운로드
지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
초록·키워드
To analyze the dynamic coupling mechanisms between the nonlinear motion of a helicopter's bluff-body slung load and its unsteady aerodynamic load, and to further improve the prediction accuracy of coupling effects during the helicopter' slung load operations, this paper establishes the numerical simulation method based on computational fluid dynamics (CFD), which is applicable to the bluff-body slung load. Then, the mathematical model of the sling constraining the motion of the slung load is developed, and its rigid-body dynamics model of the slung load is also established. By coupling the CFD model of the slung load with the six-degree-of-freedom rigid-body dynamics model, the dynamic coupling mechanisms between the nonlinear motion of the bluff-body slung load and its unsteady aerodynamic loads are analyzed. The paper clarifies the influence of the transition from narrow-side to broad-side orientations of the slung load on the aerodynamic motion coupling characteristics. The analysis results indicate that the transition, which is triggered by the continuous increase in yaw angle oscillation amplitude, is the primary cause of instability during high-speed flight. During the transition, the drag, the side force and the roll and pitch moments of the slung load rapidly exchange and redistribute. This leads to the rapid attenuation of longitudinal oscillation, while the lateral oscillation amplitude increases significantly. Simultaneously, the yaw angle enters into a stable "spinning" mode. When the speed increases from 40 km/h to 64 km/h, the instability time occurs 40% earlier, and the oscillation amplitude increases by 150%.
인공지능 문자 인식 모델을 통해 추출된 텍스트로, 일부 오타나 오류가 포함될 수 있으나 지속적으로 개선 중입니다.
오류를 발견하셨다면 해당 부분을 드래그한 후 ' 를 통해 신고해주세요.
오류를 발견하셨다면 해당 부분을 드래그한 후 ' 를 통해 신고해주세요.
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