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Multidisciplinary optimization of aeroservoelastic systems using reduced-size modelsEfficient analytical and computational tools for simultaneous optimal design of the structural and control components of aeroservoelastic systems are presented. The optimization objective is to achieve aircraft performance requirements and sufficient flutter and control stability margins with a minimal weight penalty and without violating the design constraints. Analytical sensitivity derivatives facilitate an efficient optimization process which allows a relatively large number of design variables. Standard finite element and unsteady aerodynamic routines are used to construct a modal data base. Minimum State aerodynamic approximations and dynamic residualization methods are used to construct a high accuracy, low order aeroservoelastic model. Sensitivity derivatives of flutter dynamic pressure, control stability margins and control effectiveness with respect to structural and control design variables are presented. The performance requirements are utilized by equality constraints which affect the sensitivity derivatives. A gradient-based optimization algorithm is used to minimize an overall cost function. A realistic numerical example of a composite wing with four controls is used to demonstrate the modeling technique, the optimization process, and their accuracy and efficiency.
Document ID
19920073552
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Karpel, Mordechay
(Technion - Israel Institute of Technology Haifa, United States)
Date Acquired
August 15, 2013
Publication Date
October 1, 1992
Publication Information
Publication: Journal of Aircraft
Volume: 29
Issue: 5 Se
ISSN: 0021-8669
Subject Category
Aircraft Design, Testing And Performance
Accession Number
92A56176
Funding Number(s)
CONTRACT_GRANT: NAGW-1708
Distribution Limits
Public
Copyright
Other

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