@article { author = {Tamaskani, Reza and Alfi, Alireza and Sadrnia, صدرنیا}, title = {Controlling the Euler angles of aircraft using incremental nonlinear dynamic inversion}, journal = {Iranian Journal of Mechanical Engineering Transactions of ISME}, volume = {23}, number = {4}, pages = {29-56}, year = {2022}, publisher = {ISME}, issn = {2538-4775}, eissn = {}, doi = {10.30506/ijmep.2020.122693.1686}, abstract = {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.}, keywords = {Nonlinear dynamic inversion,dynamic flight control,Sliding Mode,PID}, title_fa = {کنترل زوایای اویلر هواپیما با استفاده از وارون دینامیک غیرخطی افزایشی مقاوم}, abstract_fa = {وارون دینامیک غیرخطی یکی از روش‌های مطرح در زمینه کنترل دینامیک پرواز است که از توسعه آن به عنوان وارون دینامیک غیرخطی افزایشی (INDI) یاد می ‌شود. بر این اساس، در این مقاله ابتدا مود‌های غیرخطی تند و کند هواپیما به دو بخش مجزا تقسیم و برای هر یک از بخش ‌ها کنترل جداگانه ‌ای طراحی می­گردد که در حلقه خارجی از کنترل‌کننده PID و در حلقه داخلی از کنترل‌کننده مود لغزشی استفاده می­شود. علاوه ­بر اثبات پایداری، نتایج شبیه ‌سازی به همراه مقایسه با حالت ‌های مدل مرجع و INDI مرسوم برای هواپیمای بویینگ 747 ارائه می­ شود.}, keywords_fa = {وارون دینامیک,کنترل دینامیک پرواز,مود لغزشی,PID}, url = {https://jmep.isme.ir/article_46946.html}, eprint = {https://jmep.isme.ir/article_46946_326ffc0199ee94788251cfc2b8409bdf.pdf} }