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

DTSTART;TZID=Asia/Jerusalem:20260701T133000

DTEND;TZID=Asia/Jerusalem:20260701T143000

DTSTAMP:20260430T142003Z

URL:https://aerospace.technion.ac.il/events/seminar-dor-naftaly-01-07-2026
 /

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:Classroom 240\, 1st floor\, Aerospace Eng. building\n Zoom:
  https://technion.zoom.us/j/98372598857\n Abstract: Modern aircraft design
 s are trending toward increasingly lightweight\, high-aspect-ratio\, and h
 ighly flexible configurations for improved aerodynamic efficiency and perf
 ormance. As structural flexibility increases\, the traditional separation 
 between flight dynamics and aeroelasticity becomes less valid: elastic def
 ormations influence rigid-body motion\, and maneuver-induced accelerations
  and loads impact the structural response. This study investigates the cou
 pled flight dynamics and aeroelastic behavior of flexible aircraft\, focus
 ing on the effects of maneuvering on flutter instability.\nA unified analy
 tical and computational framework is derived for modeling both nonlinear a
 nd linearized coupled equations of motion\, capturing the interaction betw
 een rigid-body dynamics and structural elasticity. A general formulation o
 f the nonlinear equations of motion is first derived for a general coordin
 ate system. The equations are then linearized about steady maneuvering fli
 ght conditions and cast in state-space form. A modal representation is the
 n introduced\, yielding a compact formulation suitable for aeroelastic sta
 bility analysis. This process reveals eight inertial coupling terms\, incl
 uding both stiffness and damping contributions\, expressed explicitly as f
 unctions of flight parameters such as airspeed and load factor.\nThe formu
 lation is applied to multiple configurations\, including the Active Aeroel
 astic Aircraft Testbed (A3TB) flying-wing UAV and an F-16 fighter jet airc
 raft model. For the A3TB configuration\, maneuvering conditions significan
 tly alter flutter characteristics and reduce flutter onset speed. For the 
 F-16\, a comprehensive survey of a wide range of external store configurat
 ions highlights the sensitivity of flutter behavior to operational conditi
 ons. The results show that neglecting rigid-elastic coupling leads to non-
 conservative flutter predictions. Overall\, this work provides both insigh
 t and practical tools for analyzing maneuvering aeroelastic systems\, impr
 oving the prediction of flutter boundaries\, and advancing the understandi
 ng of coupled flight-mechanics–aeroelastic interactions.\n Details: \n 
CATEGORIES:Seminars
LOCATION:Classroom 240\, 1st floor\, Aerospace Eng. building

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