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UID:0-1571@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20260608T133000

DTEND;TZID=Asia/Jerusalem:20260608T143000

DTSTAMP:20260608T084725Z

URL:https://aerospace.technion.ac.il/events/seminar-dor-naftaly-08-06-2026
 /

SUMMARY:Coupled Flight Dynamics and Aeroelasticity of Maneuvering Aircraft:
  Nonlinear Modeling and Linearized Stability Analysis
DESCRIPTION:Lecturer:Dor Naftaly\n Faculty:The Stephen B. Klein Faculty of 
 Aerospace Engineering\n Institute:Technion – Israel Institute of Technol
 ogy\n Location:Online Only\n Zoom: https://technion.zoom.us/j/98372598857\
 n Abstract: Modern aircraft designs are trending toward increasingly light
 weight\, high-aspect-ratio\, and highly flexible configurations for improv
 ed aerodynamic efficiency and performance. As structural flexibility incre
 ases\, the traditional separation between flight dynamics and aeroelastici
 ty becomes less valid: elastic deformations influence rigid-body motion\, 
 and maneuver-induced accelerations and loads impact the structural respons
 e. This study investigates the coupled flight dynamics and aeroelastic beh
 avior of flexible aircraft\, focusing on the effects of maneuvering on flu
 tter instability.\nA unified analytical and computational framework is der
 ived for modeling both nonlinear and linearized coupled equations of motio
 n\, capturing the interaction between rigid-body dynamics and structural e
 lasticity. A general formulation of the nonlinear equations of motion is f
 irst derived for a general coordinate system. The equations are then linea
 rized about steady maneuvering flight conditions and cast in state-space f
 orm. A modal representation is then introduced\, yielding a compact formul
 ation suitable for aeroelastic stability analysis. This process reveals ei
 ght inertial coupling terms\, including both stiffness and damping contrib
 utions\, expressed explicitly as functions of flight parameters such as ai
 rspeed and load factor.\nThe formulation is applied to multiple configurat
 ions\, including the Active Aeroelastic Aircraft Testbed (A3TB) flying-win
 g UAV and an F-16 fighter jet aircraft model. For the A3TB configuration\,
  maneuvering conditions significantly alter flutter characteristics and re
 duce flutter onset speed. For the F-16\, a comprehensive survey of a wide 
 range of external store configurations highlights the sensitivity of flutt
 er behavior to operational conditions. The results show that neglecting ri
 gid-elastic coupling leads to non-conservative flutter predictions. Overal
 l\, this work provides both insight and practical tools for analyzing mane
 uvering aeroelastic systems\, improving the prediction of flutter boundari
 es\, and advancing the understanding of coupled flight-mechanics–aeroela
 stic interactions.\n\nThis work is towards a Ph.D. degree under the superv
 ision of Prof. Daniella E. Raveh\, The Stephen B. Klein Faculty of Aerospa
 ce Engineering\, Technion.\n Details: \n 
CATEGORIES:Seminars
LOCATION:Online Only

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