Conceptual Control Law Design for Aircraft with Reduced Tail Size RMIT University

Format:

Conference/Event

Author/Creator:

Handayani, Endang S.L., author.

Conference Name:

World Aviation Congress & Exposition (2001-09-11 : Seattle, Washington, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2001

Summary:

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 and CmαCmq . 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

Notes:

Vendor supplied data

Publisher Number:

2001-01-3003

Access Restriction:

Restricted for use by site license