Simultaneous flight control system and twist-morphing wing design of an unmanned aerial vehicle

Öz

Over the last years, the application of morphing technologies in the aircraft design field has become widespread together with developments in material technologies. In this context, this study discusses the design of an innovative twist-morphing wing on a fixed-wing unmanned aerial vehicle (UAV) aiming to obtain improvement in stall behavior (i.e. stall propagation) and autonomous flight performance. The twist-morphing wing design was designed to be capable of twisting in terms of wash-out angle between 0-degree and 6-degree. In order to have such a multidisciplinary improvement, simultaneous design approach was integrated and SPSA optimization algorithm was used. The washout angle and longitudinal and lateral PID controller coefficients were optimized to have enhancement in autonomous flight performance defined in rise time, settling time and maximum overshoot, which are related with step responses. In result, longitudinal, lateral and total performances were improved by 33.92%, 33.81% and 65.14%, respectively.

Anahtar Kelimeler

• Aircraft design
• twist-morphing
• autonomous flight performance

Bir insansız hava aracının eşzamanlı uçuş kontrol sistemi ve burularak-başkalaşabilen kanat tasarımı

Öz

Son yıllarda malzeme teknolojilerindeki gelişmelerle birlikte hava aracı tasarımı alanında başkalaşım teknolojilerinin de uygulamaları yaygınlaşmıştır. Bu bağlamda, bu çalışmada, sabit kanatlı bir insansız hava aracı (İHA) üzerinde, perdövites davranışında (yani perdövites yayılımı) ve otonom uçuş performansında iyileşme elde etmeyi amaçlayan yenilikçi bir burularak-başkalaşabilen kanat tasarımı tartışılmaktadır. Burularak-başkalaşabilen kanat tasarımı, 0-derece ile 6-derece arasında burulabilecek şekilde tasarlanmıştır. Böylesi bir multidisipliner iyileştirme için eşzamanlı tasarım yaklaşımı sürece entegre edilmiş ve SPSA optimizasyon algoritması kullanılmıştır. Burulma açısı ile boylamsal ve yanal PID kontrolcü katsayıları, birim basamak tepkisi parametreleri olan yükselme zamanı, yerleşme zamanı ve maksimum aşım ile ifade edilerek otonom uçuş performansında iyileştirme sağlamak için optimize edilmiştir. Sonuç olarak, boylamsal, yanal ve toplam otonom uçuş performanslarının sırasıyla %33.92, %33.81 ve %65.14 oranında iyileştirildiği görülmüştür.

Anahtar Kelimeler

• Hava aracı tasarımı
• burularak-başkalaşım
• otonom uçuş performansı

Kaynakça

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