Sensitivity derivatives of blade loads and stability in forward flight are calculated as an integral part of the basic aeroelastic analysis using a computationally efficient analytical approach. Design variables include nonstructural mass and its placement, blade bending stiffnesses (flap, lag, torsion), and blade geometry (sweep, anhedral and planform taper). Aeroelastic and sensitivity analyses of the rotor based on a finite element method in space and time are linked with automated optimization algorithms to perform optimization of rotor blades. The objective function constitutes minimization of oscillatory hub loads including constraints on frequency placement, autorotational inertia and aeroelastic stability of the blade in forward flight. Optimum design solutions are calculated for a four-bladed, soft-inplane hingeless rotor. Analytical predictions show a 25 to 60 percent reduction in all the 4/revolution loads, compared to the starting design. The optimum design is swept back, drooped down and tapered along the blade span, with nonstructural mass distributed behind the elastic axis along the outer 60 percent of the blade.
Aerolastic optimization of an advanced geometry helicopter rotor
Die aeroelastische Optimierung eines Hubschrauberrotors mit fortgeschrittener Geometrie
Journal of the American Helicopter Society ; 41 , 1 ; 18-28
1996
11 Seiten, 12 Bilder, 3 Tabellen, 15 Quellen
Article (Journal)
English
Hubschrauber , Rotor (Drehflügel) , Flugverhalten , geometrische Form , Systemoptimierung , dynamische Stabilität , Lastkollektiv , Betriebsfestigkeit , Empfindlichkeit , Auslegung (Dimension) , Masse (physikalische Größe) , Biegesteifigkeit , Torsion , Pfeilflügel , Finite-Elemente-Methode , Algorithmus , Lösung (Mathematik)
Aerolastic optimization of a helicopter rotor
TIBKAT | 1988
|Aeroelastic optimization of an advanced geometry helicopter rotor
Online Contents | 1996
|Aeroelastic optimization of an advanced geometry helicopter rotor
Tema Archive | 1992
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