كنترل زواياي اويلر هواپيما با استفاده از وارون ديناميك غيرخطي افزايشي مقاوم

Controlling the Euler angles of aircraft using incremental nonlinear dynamic inversion

وارون ديناميك غيرخطي يكي از روش‌هاي مطرح در زمينه كنترل ديناميك پرواز است كه از توسعه آن به عنوان وارون ديناميك غيرخطي افزايشي (INDI) ياد مي ‌شود. بر اين اساس، در اين مقاله ابتدا مود‌هاي غيرخطي تند و كند هواپيما به دو بخش مجزا تقسيم و براي هر يك از بخش ‌ها كنترل جداگانه ‌اي طراحي مي­گردد كه در حلقه خارجي از كنترل‌كننده PID و در حلقه داخلي از كنترل‌كننده مود لغزشي استفاده مي­ شود. علاوه ­بر اثبات پايداري، نتايج شبيه ‌سازي به همراه مقايسه با حالت ‌هاي مدل مرجع و INDI مرسوم براي هواپيماي بويينگ 747 ارائه مي­ شود.

Nonlinear dynamic inversion is one of the well-known methods in the field of dynamic flight control, which its development refers to the Incremental Nonlinear Dynamic Inversion (INDI). Based on this, in this paper, the non-linear slow and fast modes of the aircraft is separated into two parts. Then, a distinct control is designed for each part. In the outer and inner loops, the PID and the sliding mode controller are designed, respectively. In addition stability analysis, the simulation results for Boeing 747 are presented and compared with the reference model modes and the conventional INDI. Nonlinear dynamic inversion is one of the well-known methods in the field of dynamic flight control, which its development refers to the Incremental Nonlinear Dynamic Inversion (INDI). Based on this, in this paper, the non-linear slow and fast modes of the aircraft is separated into two parts. Then, a distinct control is designed for each part. In the outer and inner loops, the PID and the sliding mode controller are designed, respectively. In addition stability analysis, the simulation results for Boeing 747 are presented and compared with the reference model modes and the conventional INDI.