عنوان المقالة:MOHAMMED MAHDI ABDULLA, TAREG M. HASSAN NONLINEAR FLIGHT SIMULATION OF LIGHT AIRCRAFT SUBJECTED TO GUST WIND

محمد مهدي عبدالله محمد | Mohammed Mahdi Abdulla Mohammed | 2443

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نوع النشر

مجلة علمية

المؤلفون بالعربي

الملخص الانجليزي

This work analyzes and simulates the behavior and performance of a light aircraft in steady level flight subjected to gust wind utilizing a nonlinear 6-degree-of-freedom (DOF) equation of motion. The aerodynamic behavior of the aircraft was investigated using CFD at different angles of attack (α) and side slip angles (β). The x, y and z forces and moments were calculated at a flight speed of 50 m/s and sea level conditions. Lift and drag curves for different α were plotted. The maximum lift coefficient for this aircraft is 1.67 which occurs at an α of 17°, the maximum lift to drag ratio is 14 which occurs at α = 3°, and the zero-lift drag coefficient is 0.0342. The rolling and yawing moment coefficients were plotted for different βs. The static stability of the aircraft was analyzed. The USAF digital DATCOM was used to estimate the dynamic derivatives of the vehicle. The engine was modelled by a simple model such that engine power and thrust vary with altitude and speed. A home-made code was developed using MATLAB to simulate the aircraft’s behavior utilising the nonlinear 6-DOF. The aerodynamics and engine model were included in the code. The gust model used in this analysis was a sine-wave-shaped gust. The simulation results indicate that the aircraft is stable and controllable, and that the gust wind effect is eliminated and damped in a few seconds. The load factor increment due to gust effect is not critical. © Marques Aviation Ltd.

تاريخ النشر

01/06/2013

الناشر

IJUSEng

رقم المجلد

3

رقم العدد

3

ISSN/ISBN

2052-112X

رابط DOI

10.14323/IJUSENG.2013.13

رابط خارجي

http://www.ijuseng.com/ijuseng-1-3-68-79-2013/4578171762

الكلمات المفتاحية

Aerodynamics model, CFD, Gust alleviation, Nonlinear equation of motion, 6 degrees of freedom