A new aeroelastic formulation for the advanced geometry blades, involving variable sweep, droop, pretwist and planform, is presented. The blade is modeled as a series of arbitrarily-oriented elastic segments with each segment divided into finite elements. Interelement compatibility relations governing non-Eulerian moderte rotations of the finite elements are also presented. Fuselage dynamic interaction with the advanced geometry blades is included in the formulation. The nonlinear partial differential equations of motion are discretized in space and time using Hamilton's principle. Selective results are presented in hover and forward flight. Results indicate that sweep, and droop in particular, can have a strong influence on both the rotor aeroelastic stability and the rotorcraft aeromechanical stability. Droop can be considerably stabilizing. Sweep increases the blade torsional loads, but is not detrimental to flap and lag vibratory loads.
Aeromechanical stability of rotorcraft with advanced geometry blades
Die aerodynamische Stabilität der Rotorkraft mit verbesserter Geometrie der Rotorblätter
1993
25 Seiten, 13 Bilder, 1 Tabelle, 13 Quellen
Aufsatz (Konferenz)
Englisch
Luftfahrttechnik , Hubschrauber , Rotor (Drehflügel) , geometrische Form , technische Entwicklung , Prozessoptimierung , Aeromechanik , Finite-Elemente-Methode , Euler-Gleichung , Flugzeugrumpf , Differenzialgleichung , Betriebsverhalten , Schweben , Drehschwingung , Schwingungsverhalten , belastetes Bauteil , mechanische Stabilität , Flugverhalten