Sensitivity derivatives of flutter characteristics and stability margins for aeroservoelastic design

Author:

KARPEL M.1

Affiliation:

1. Technion - Israel Institute of Technology, Haifa

Publisher

American Institute of Aeronautics and Astronautics

Reference23 articles.

1. . where the matrices are the t , t. xa and xac related partitions of [A] of Eq. 7 [A")], and are not a function of q. can be expressed as: CA(2)l = - [n1-1ci(2)l

2. gains and the associated flutter derivatives. Consequently, the design strategy in this case is to advance in steps uhere only G4 is changed (along uith the dependent G =-0.124-0.368*G4) to produce an expected

3. 3 G =-0-057 which

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