Conceptual Control Law Design for Aircraft With Reduced Tail Size

Document Number: 2001-01-3003

Date Published: September 2001

Author(s):
Cees Bil - RMIT University
Endang S. L. Handayani - RMIT University
-- Mudjijanto - Aerospace Indonesia

Abstract:
The design of a longitudinal stability augmentation system (SAS) for an aircraft with reduced tail size in the preliminary design phase is presented. Reducing tail size will reduce drag and weight and result in better fuel consumption, but it will reduce the level of stability. A control law is designed to give the aircraft the same stability level as that with the initial tail size. The feedback gains of the control law is computed with the equivalent stability derivative criteria of C\dm\da and C\dm\dq. The paper also gives an overview of classical root locus and pole placement method and demonstrates that equivalent stability derivative criteria is suitable for preliminary aircraft design applications. Moreover, the control laws are also synthesized using robust control LQG/LTR which can be elaborated more in the detail design phase.

File Size: 180K
Product Status: In Stock

See other papers presented at World Aviation Congress _® & Exposition, September 2001, Seattle, WA, USA, Session: Innovative Design Methods I

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