An aeroelastic analysis based on a finite element method in space and time is developed for an advanced geometry composite rotor. Optimization studies are carried out for a four-bladed, soft-inplane hingeless rotor with variable sweep, anhedral and planform taper, and with a two-cell composite box-beam spar. The objective function includes vibratory hub loads and vibratory bending moments; constraints are imposed on blade rotating frequencies, aeroelastic stability and autorotational inertia. Design variables include ply angles of the laminated walls of the box-beam, sweep, anhedral and planform taper, and nonstructural mass and its chordwise offset from the elastic axis. Aeroelastic optimization is performed for different combinations of design variables. The starting design is a straight blade with no composite coupling. Compared to the starting design, an optimized solution achieved a reduction in the 4/rev loads of 40 % - 60 %, and 15 % - 25 % in the peak-to-peak vibratory flap and lag bending moments.
Aeroelastic tailoring of composite couplings and blade geometry of a helicopter rotor using optimization methods
Das aeroelastische Auslegen von Verbundstoff-Kupplungen und der Rotorblattgeometrie eines Hubschraubers mit Hilfe der Optimierungsmethode
Journal of the American Helicopter Society ; 42 , 3 ; 218-228
1997
11 Seiten, 20 Bilder, 4 Tabellen, 15 Quellen
Article (Journal)
English
Rotor (Drehflügel) , Hubschrauber , Auslegung (Dimension) , Finite-Elemente-Methode , geometrische Form , Aerodynamik , Carbonfaser , Epoxidharz , Schichtstoff , Differenzialgleichung , Schwingungsverhalten , Nabe , Biegemoment , Resonanzfrequenz , Stabilität , Schwingungsdämpfung , Steifigkeit , Torsion , Sensitivitätsanalyse
Aeroelastic Optimization of a Helicopter Rotor with Composite Tailoring
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