Experimental investigation on the control and load characteristics of active wing morphing aircraft concept

Yıl 2025, Cilt: 40 Sayı: 3, 1589 - 1598, 21.08.2025

Erdoğan Kaygan , Alvin Gatto

https://doi.org/10.17341/gazimmfd.1533853

Öz

Recent developments in morphing aircraft research have made researchers re-examine more “morphing” technologies and techniques. The purpose of this study was to explore new concepts of adaptive wings and/or winglets to improve aircraft control and performance. The primary variable investigated involves varying the twist angle of the configurations with the purpose of evaluating the concept using experimental approaches. Another main goal was to evaluate and demonstrate the developed concept in a wind tunnel environment. Both the traditional control surface model and the variable morphing wing model were designed and tested in the wind tunnel Through the wind tunnel results, the adaptive wing structure at -6 degree was found to achieve a drag reduction which resulted in a lift to drag ratio improvement of approximately 22% comparable to the fixed wing structure. Furthermore, it has been observed that the morphing twist structure and the traditional control mechanism showed similar control moment coefficients. This research also aimed to develop an alternative approach for a morphing skin technology.

Anahtar Kelimeler

Aerodynamics , active wings , morphing skin , twist , wind tunnel

Aktif kanatlı dönüşen uçak konseptinde kontrol ve yük karakteristiklerinin deneysel olarak incelenmesi

Öz

Değişken kanatlı(Morphing) uçak araştırmalarındaki son gelişmeler, uyumlu geçişli sistemlere, yani ayrı hareketli parçalar olmadan şekil değişikliğine veya kanat profilindeki ani değişikliklere yönelik araştırmaların tekrardan tetiklenmesine neden olmuştur. Bu çalışmanın amacı, uçak kontrolü ve performansını artırmak için uyarlanabilir kanat ve/veya kanatçık kavramlarına ilişkin yeni kavramları keşfetmekti. Araştırılan birincil değişken, deneysel yaklaşımlar kullanarak konsepti değerlendirmek için tek bir amaç doğrultusunda konfigürasyonların bükülme açısının değiştirilmesini içeriyor. Bir diğer temel amaç ise geliştirilen konsepti rüzgar tüneli ortamında değerlendirmek ve göstermekti. Hem geleneksel kontrol yüzeyi modeli hemde değişebilen kanatçık modelleri tasarlanıp rüzgar tünelinde denenmiştir. Yapılan deneyler sonrasında uçak kanadının -6 derecelik bir büküm(twist) açısına ulaştığı zaman ve normal düz kanat profili ile yapılan karşılaştırmada yaklaşık %22’lik bir performans artışı göze çarpmaktadır. Bununla birlikte farklı twist açılarında geleneksel yöntemlerin kullanıldığı kontrol yüzey kullanımlarıyla benzer bir moment katsayıları elde edilmiştir. Bu araştırma aynı zamanda değişen bir yüzey kaplama için alternatif bir yaklaşım geliştirmeyi de amaçlamıştır.

Anahtar Kelimeler

Aerodinamik , aktif kanat , değişime uyumlu kaplama , bükülme , rüzgar tüneli.

Kaynakça

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