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Conceptual Control Law Design for Aircraft with Reduced Tail Size
Technical Paper
2001-01-3003
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
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 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.
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Authors
Citation
Handayani, E., Bil, C., and Mudjijanto, ., "Conceptual Control Law Design for Aircraft with Reduced Tail Size," SAE Technical Paper 2001-01-3003, 2001, https://doi.org/10.4271/2001-01-3003.Also In
References
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