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Proceedings Paper

Static aeroelastic control for pull-up maneuver of a flexible wing with internal actuation
Author(s): Narendra S. Khot; Kari Appa; Duane E. Veley
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Paper Abstract

A technique of deforming a flexible wing to hold the airplane in a steady pull-up maneuver with required load factor at high dynamic pressures is examined. Rather than using an elevator system for pull-up, symmetric elastic twist and camber is determined to achieve the required pitching moment for increase in the angle of attack and change in the pitch rate to generate the required lift forces for pull-up maneuver. The elastic twist and camber is achieved by providing a system of actuating elements distributed within the internal substructure of the wing to provide control forces. The modal approach is used to develop equilibrium equations for the steady pull-up maneuver of a wing subjected to aerodynamic loads and the actuating forces. The distribution of actuating forces required to achieve specified load factor was determined by using an iterative procedure in conjunction with an optimal control design approach. Here, a full-scale flexible realistic wing is considered for the assessment of strain energy as a measure of the necessary power required to produce the symmetric twist and camber deformation to achieve the required lift forces. Subsonic and supersonic design conditions are investigated.

Paper Details

Date Published: 21 August 2001
PDF: 12 pages
Proc. SPIE 4326, Smart Structures and Materials 2001: Modeling, Signal Processing, and Control in Smart Structures, (21 August 2001); doi: 10.1117/12.436485
Show Author Affiliations
Narendra S. Khot, Air Force Research Lab. (United States)
Kari Appa, Appa Technology Initiatives (United States)
Duane E. Veley, Air Force Research Lab. (United States)

Published in SPIE Proceedings Vol. 4326:
Smart Structures and Materials 2001: Modeling, Signal Processing, and Control in Smart Structures
Vittal S. Rao, Editor(s)

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