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Proceedings Paper

Aeroservoelastic design with distributed actuation for high-performance aircraft
Author(s): Hayrani Oz
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Paper Abstract

A new aeroelastic modal formulation in terms of real modal matrices and modal-state variables is introduced. Real biorthonormality relationships for aeroelastic modes are given with respect to structural matrices. The solution for distributed-parameter-control of an aeroelastic system is developed by modal synthesis from modal-state-space control inputs. In particular, the globally power optimal Independent Modal-Space Control technique is used for maneuver (set-point) control of an aeroelastic system by a modal-performance-output synthesis approach. Control power functionals for an aeroelastic system are defined by any actuation profile and control design. The known solution for the synthesized distributed-parameter closed-loop aeroelastic system is optimally approximated via a gain distribution error minimization technique integrating the transient and power performance characteristics of the system for implementation by distributed, spatially-discrete actuation profiles. For the same purpose, a Galerkin approximation is also given. The method is illustrated for a lifting surface simulating a wing to twist the wing tip to a prescribed angle of attack by using different distributed actuation profiles. Various warped wing shapes can be affected by the approach by synthesizing through different selections of aeroelastic modes for control design resulting in different control power requirements.

Paper Details

Date Published: 24 July 1998
PDF: 15 pages
Proc. SPIE 3323, Smart Structures and Materials 1998: Mathematics and Control in Smart Structures, (24 July 1998); doi: 10.1117/12.316288
Show Author Affiliations
Hayrani Oz, The Ohio State Univ. (United States)

Published in SPIE Proceedings Vol. 3323:
Smart Structures and Materials 1998: Mathematics and Control in Smart Structures
Vasundara V. Varadan, Editor(s)

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