Eğrisel Fiber Yollu İkili Motorlu-Kanat Sisteminin Aeroelastik Enerji Optimizasyonu

Abstract

Bu çalışmada, bir çift motorlu kompozit kanat sisteminin aeroelastik enerji tepkisi, sıralı karesel programlama (SQP) yöntemine göre optimize edilmiştir. Değişken sertlik, TWB'nin laminatlarının, öngörülen yollara sahip eğrisel liflerle oluşturulmasıyla elde edilir. Spanverse lokasyonların ve motor kütlesinin TWB'nin aeroelastik özellikleri üzerindeki etkisini hesaba katmak için, yeni yönlendirme denklemleri Hamilton'un varyasyon prensibi kullanılarak elde edilir. Kağıt, farklı çift motor kanadı konfigürasyonu için geliştirilmiş aeroelastik özelliklere sahip arzu edilen lif yollarından faydalanmayı amaçlamaktadır. Ritz tabanlı çözüm metodolojisi, Wagner'in fonksiyonuna dayanan sıkıştırılamaz sıkıştırılmamış kararsız aerodinamik model ile denklemleri çözmek için kullanılır. Aeroelastik sistemin toplam enerjisine dayanan yeni bir optimizasyon stratejisi tanıtıldı. Maliyet fonksiyonu olarak önerilen toplam enerji, iki motor lokasyonunun dört optimizasyon değişkeni ve iki parametreli konak yapısı eğrisel fiber açısı açısından en aza indirilir. Toplam enerji, kinetik ve potansiyel enerjinin kontrollü tepkilerinin belirli bir zaman aralığına entegre edilmesiyle elde edilir. Minimum toplam enerji, en yüksek çarpışma performansına yol açan ideal optimizasyon değişkenlerinin bir göstergesidir. Sayısal sonuçlar, optimizasyon değişkenlerinin aeroelastik sistemin toplam enerjisi üzerindeki etkinliğini gösterir ve minimum toplam enerji ve geliştirilmiş aeroelastik özellikler durumunda sokulan değişkenlerin optimal değerlerini belirler.

Keywords

• aeroelastik optimizasyon,ikiz motor kanat sistemi,kompozit ince cidarlı kiriş,eğrisel lif yolu

Sequential Quadratic Optimization of Aeroelastic Energy of Twin-Engine Wing System with Curvilinear Fiber Path

Abstract

In the present study, the aeroelastic energy response of a twin-engine composite wing system is optimized based on sequential quadratic programming (SQP) method. The variable stiffness is acquired by constructing laminates of thin wall beam (TWB) with curvilinear fibers having prescribed paths. In order to account the effect of spanwise locations and mass of the engines on the aeroelastic characteristics of TWB, the novel governing equations of motion are obtained using Hamilton's variational principle. The paper aims to exploit desirable fiber paths with improved aeroelastic properties for different twin-engine wing configuration. Ritz based solution methodology is employed to solve the equations with coupled incompressible unsteady aerodynamic model based on Wagner’s function. A novel optimization strategy based on the total energy of the aeroelastic system is introduced. The proposed total energy, as a cost function, is minimized in terms of four optimization variables of two engine’s locations and wing structure curvilinear fiber angle with two design parameters. The total energy is obtained by integrating responses of kinetic and potential energy in a specific time interval. The minimum total energy is an indication of ideal optimization variables which leads to the optimum flutter performance. Numerical results demonstrate the effectiveness of the optimization variables on the total energy of the aeroelastic system and determine the optimal values of introduced variables in case of minimum total energy and improved aeroelastic characteristics.

Keywords

• aeroelastic optimization,twin engine-wing system,composite thin walled beam,curvilinear fiber path

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