Abstract
The paper addresses the integration of blade dynamics, aerodynamics, structures and aeroelasticity in the design of helicopter rotors using a formal optimization technique. The interaction of the disciplines is studied inside a closed-loop optimization process. The goal is to reduce vibratory shear forces at the blade root with constraints imposed on dynamic, structural and aeroelastic design requirements. Both structural and aerodynamic design variables are used. Multiobjective formulation. procedures are needed since more than one design objective is used. A nonlinear programming technique and an approximate analysis procedure are used for optimization. Substantial reductions are obtained in the vibratory root forces and moments while satisfying the remaining design criteria. The results of the optimization procedure using two multiobjective formulation procedures, are compared with a baseline or reference design.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 59-72 |
| Number of pages | 14 |
| Journal | Computers and Mathematics with Applications |
| Volume | 25 |
| Issue number | 2 |
| DOIs | |
| State | Published - 1993 |
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ASJC Scopus subject areas
- Applied Mathematics
- Computational Mathematics
- Modeling and Simulation
Cite this
A multidisciplinary optimization approach for vibration reduction in helicopter rotor blades. / Chattopadhyay, Aditi; McCarthy, Thomas R.
In: Computers and Mathematics with Applications, Vol. 25, No. 2, 1993, p. 59-72.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - A multidisciplinary optimization approach for vibration reduction in helicopter rotor blades
AU - Chattopadhyay, Aditi
AU - McCarthy, Thomas R.
PY - 1993
Y1 - 1993
N2 - The paper addresses the integration of blade dynamics, aerodynamics, structures and aeroelasticity in the design of helicopter rotors using a formal optimization technique. The interaction of the disciplines is studied inside a closed-loop optimization process. The goal is to reduce vibratory shear forces at the blade root with constraints imposed on dynamic, structural and aeroelastic design requirements. Both structural and aerodynamic design variables are used. Multiobjective formulation. procedures are needed since more than one design objective is used. A nonlinear programming technique and an approximate analysis procedure are used for optimization. Substantial reductions are obtained in the vibratory root forces and moments while satisfying the remaining design criteria. The results of the optimization procedure using two multiobjective formulation procedures, are compared with a baseline or reference design.
AB - The paper addresses the integration of blade dynamics, aerodynamics, structures and aeroelasticity in the design of helicopter rotors using a formal optimization technique. The interaction of the disciplines is studied inside a closed-loop optimization process. The goal is to reduce vibratory shear forces at the blade root with constraints imposed on dynamic, structural and aeroelastic design requirements. Both structural and aerodynamic design variables are used. Multiobjective formulation. procedures are needed since more than one design objective is used. A nonlinear programming technique and an approximate analysis procedure are used for optimization. Substantial reductions are obtained in the vibratory root forces and moments while satisfying the remaining design criteria. The results of the optimization procedure using two multiobjective formulation procedures, are compared with a baseline or reference design.
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UR - http://www.scopus.com/inward/citedby.url?scp=38249005134&partnerID=8YFLogxK
U2 - 10.1016/0898-1221(93)90223-I
DO - 10.1016/0898-1221(93)90223-I
M3 - Article
VL - 25
SP - 59
EP - 72
JO - Computers and Mathematics with Applications
JF - Computers and Mathematics with Applications
SN - 0898-1221
IS - 2
ER -