مهندسی مکانیک مدرس

مهندسی مکانیک مدرس

مدل‌سازی و شبیه‌سازی دینامیک غیرخطی فلپینگ روتور هلیکوپتر با احتساب آفست، گشتاور وزن پره و فرکانس فلپینگ

نوع مقاله : پژوهشی اصیل

نویسندگان
دانشکده مهندسی فناوری‌های نوین، دانشگاه شهید بهشتی، تهران، ایران
چکیده
فلپینگ تیغه روتور هلیکوپتر منجر به تقارن لیفت در روتور هلیکوپتر می‌شود و تاثیر قابل توجهی در پایداری و کنترل دارد. در این مقاله به مدل‌سازی فلپینگ هلیکوپتر در حضور نیروها و گشتاورهای آیرودینامیکی و بررسی اثر آفست، گشتاور وزن پره، فنر مقاوم در لولا، هندسه پره، اثر فرکانس طبیعی و نسبت پیشروی برای دستیابی به رفتار قابل اطمینانی از فلپینگ مورد بررسی قرار گرفته است. در شبیه‌سازی به اثرات زوایای کوچک و بزرگ فلپینگ و نقش آفست در گشتاورهای وارد شده بر پره و همچنین نقش نسبت پیشروی در گشتاورها پرداخته شده است. مدل‌های مختلف دینامیکی فلپینگ و معادلات برای پرواز هاور و کروز هلیکوپتر به طور کامل ارائه می‌شود و برای یک مثال عددی همه موارد مهم مورد بررسی قرار می‌گیرد. همچنین اثر جریان غیریکنواخت در معادلات فلپینگ پره، تاثیر فرکانس طبیعی حرکت فلپینگ با آفست پره ارائه می‌شود. این مهم منجر به افزایش دقت در مدل‌سازی پدیده فلپینگ در هلیکوپتر می‌شود. نتایج شبیه‌سازی نشان‌دهنده اهمیت و میزان تاثیر آفست، گشتاورها و نیروهای وارد شده بر پره در حرکت فلپینگ است که منجر به افزایش دقت در مدل‌سازی می‌شود.
کلیدواژه‌ها

موضوعات


عنوان مقاله English

Modeling and Simulation of Nonlinear Dynamics of Helicopter Rotor Flapping Considering Offset, Blade Weight Moment and Frequency of Flapping

نویسندگان English

M. Navabi
H. Ghaffari
New Technologies Engineering Depatment, Shahid Beheshti University, Tehran, Iran
چکیده English

The helicopter rotor blade flapping results in a helicopter rotor symmetry lift and has a significant impact on stability and control. In this paper, the modeling of helicopter flapping in the presence of aerodynamic forces and moments and the effect of offset, blade torque, hinge resistant spring, blade geometry, natural frequency effect, and forward ratio to achieve reliable relief from flapping was investigated. In the simulation, the effects of small and large flapping angles and the role of offset on the momentum entered on the blade, as well as the role of the forward ratio in moments were investigated. Different models of flapping dynamics and equations for the flight of a hover and are fully presented and all of the important issues are examined for a numerical example. Also, the effect of non-uniform flow in the flapping equations of the blade is the effect of the natural frequency of the flapping motion with the blade offset. This leads to increasing the accuracy in modeling the phenomenon of on a helicopter. Simulation results show the importance and impact of offsets, moments and forces imposed on the blade in the motion of the flapping, which leads to an increase of accuracy in modeling.

کلیدواژه‌ها English

Helicopter
Flapping Dynamics
simulation
Offset
Blade Weight Moment
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