Application of the mixed finite-element method to rotor blade modal reduction
被引:7
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作者:
Ruzicka, GC
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机构:
USA, Army NASA Rotorcraft Div, Aeroflightdynam Directorate, AMRDEC,Aviat & Missile Command,Ames Res Ctr, Moffett Field, CA 94035 USAUSA, Army NASA Rotorcraft Div, Aeroflightdynam Directorate, AMRDEC,Aviat & Missile Command,Ames Res Ctr, Moffett Field, CA 94035 USA
Ruzicka, GC
[1
]
Hodges, DH
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机构:USA, Army NASA Rotorcraft Div, Aeroflightdynam Directorate, AMRDEC,Aviat & Missile Command,Ames Res Ctr, Moffett Field, CA 94035 USA
Hodges, DH
机构:
[1] USA, Army NASA Rotorcraft Div, Aeroflightdynam Directorate, AMRDEC,Aviat & Missile Command,Ames Res Ctr, Moffett Field, CA 94035 USA
[2] Georgia Inst Technol, Sch Aerosp Engn, Atlanta, GA 30332 USA
A mixed finite element is investigated as a means for achieving accurate modal reduction of rotor blades in finite-element software. A rationale for mixed finite elements is developed by investigating the modal reduction accuracy of a series of blade analysis methods that introduces, in a step-by-step fashion, the key features of the mixed element. During this investigation, the shortcomings of classical, displacement-based finite elements are examined qualitatively and through calculations of articulated blade response. The formal derivation of the mixed element starting from a mixed variational principle is then summarized, and finally, numerical examples are presented to demonstrate the element's modal reduction accuracy. (C) 2001 Elsevier Science Ltd. All rights reserved.