Roketlerde kanat geometrisinin statik stabiliteye etkilerinin sayısal olarak incelenmesi

Öz

Bu çalışmada, roket sistemlerinde kullanılan farklı kanatçık geometrilerinin statik kararlılık üzerindeki etkisi sayısal analiz yoluyla araştırılmıştır. Roket sistemlerinde aerodinamik kararlılığın sağlanması, özellikle yüksek hızlı uçuş sırasında sapma ve kararsızlığın önlenmesi için büyük önem taşımaktadır. Bu bağlamda, ileri süpürülmüş delta, ileri süpürülmüş delta, eliptik ve trapez olmak üzere dört farklı kanatçık geometrisi hem OpenRocket simülasyonları hem de ANSYS Fluent tabanlı Hesaplamalı Akışkanlar Dinamiği analizi kullanılarak değerlendirilmiştir. OpenRocket, roketin basınç merkezini (CP) ve kütle merkezini (CG) belirlemiş ve statik marjları hesaplamıştır. Her kanatçık tipi için kaldırma kuvveti, sürükleme kuvveti ve moment değerleri HAD analizi yoluyla elde edilmiştir. Ayrıca, elde edilen veriler MATLAB'da oluşturulan bir uçuş dinamiği modeline beslenerek zamanla değişen yönelimleri analiz edilmiştir. Sonuçlar, eliptik kanatçıkların minimum sürükleme katsayılarıyla en verimli çözümü sunduğunu, ileri süpürülmüş delta kanatların ise irtifa ve kaldırma performansı açısından üstün olduğunu göstermiştir. Çalışmanın sonuçları, roket tasarım sürecinde stabilizatörlerin optimum seçimi için mühendislik tabanlı öneriler sunmaktadır.

Anahtar Kelimeler

• Roket aerodinamiği
• kanat geometrisi
• statik marj
• HAD
• OpenRocket

Numerical investigation of the effects of wing geometry on static stability in rockets

Öz

In this study, the effects of different fin geometries used in rocket systems on static stability were investigated through numerical analysis. Ensuring aerodynamic stability in rocket systems is crucial for preventing yaw and instability, especially during high-speed flight. In this context, four different fin geometries—forward-swept delta, forward-swept delta, elliptical, and trapezoidal—were evaluated using both OpenRocket simulations and ANSYS Fluent-based Computational Fluid Dynamics (CFD) analysis. OpenRocket determined the rocket's Center of Pressure (CP) and center of mass (CG) and calculated the static margins. Lift, drag, and moment values for each fin type were obtained through CFD analysis. Furthermore, the obtained data were fed into a flight dynamics model created in MATLAB to analyze their time-varying orientations. The results showed that elliptical fins offer the most efficient solution with minimum drag coefficients, while forward-swept delta wings are superior in terms of altitude and lift performance. The results of the study provide engineering-based recommendations for the optimum selection of stabilizers in the rocket design process.

Anahtar Kelimeler

• Rocket aerodynamics
• wing geometry
• static margin
• CFD
• OpenRocket.

Kaynakça

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