Title page for ETD etd-01072002-135844

Type of Document Dissertation
Author Tuzcu, Ilhan
Author's Email Address ituzcu@vt.edu
URN etd-01072002-135844
Title Dynamics and Control of Flexible Aircraft
Degree PhD
Department Mechanical Engineering
Advisory Committee
Advisor Name Title
Meirovitch, Leonard Committee Chair
Inman, Daniel J. Committee Co-Chair
Ahmadian, Mehdi Committee Member
Librescu, Liviu Committee Member
Wicks, Alfred L. Committee Member
  • Multidisciplinary Formulation
  • LQG Control
  • Extended Aeroservoelasticity
  • Perturbation Approach
  • Flexible Aircraft Dynamics
Date of Defense 2001-12-19
Availability unrestricted
This dissertation integrates in a single mathematical formulation the disciplines pertinent to the

flight of flexible aircraft, namely, analytical dynamics, structural dynamics, aerodynamics

and controls. The unified formulation is based on fundamental principles and incorporates

in a natural manner both rigid body motions of the aircraft as a whole and elastic deformations

of the flexible components (fuselage, wing and empennage), as well as the aerodynamic,

propulsion, gravity and control forces. The aircraft motion is described in terms of three

translations (forward motion, sideslip and plunge) and three rotations (roll, pitch and yaw)

of a reference frame attached to the undeformed fuselage, and acting as aircraft body axes,

and elastic displacements of each of the flexible components relative to corresponding body

axes. The mathematical formulation consists of six ordinary differential equations for the

rigid body motions and one set of ordinary differential equations for each elastic displacement.

A perturbation approach permits division of the problem into a nonlinear "zero-order Problem"

for the rigid body motions, corresponding to flight dynamics, and a linear "first-order

problem" for the elastic deformations and perturbations in the rigid body translations and

rotations, corresponding to "extended aeroelasticity." Due to computational speed advantages,

the aerodynamic forces are derived by means of strip theory. The control forces for the flight

dynamics problem are obtained by an "inverse" process. On the other hand, the feedback control

forces for the extended aeroelasticity problem are derived by means of LQG theory. A numerical

example corresponding to steady level flight and steady level turn maneuver is included.

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