Various tools for the aeroelastic stability and response analysis of rotor blades in hover and forward flight were developed and incorporated in a comprehensive package capable of performing aeroelastic tailoring of rotor blades in forward flight. The results indicate that substantial vibration reductions, of order 15-40%, in the vibratory hub shears can be achieved by relatively small modifications of the initial design. Furthermore the optimized blade can be up to 20% lighter than the original design. Accomplishments are reported for the following tasks: (1) finite element modeling of rotary-wing aeroelastic problems in hover and forward flight; (2) development of numerical methods for calculating the aeroelastic response and stability of rotor blades in forward fight; (3) formulation of the helicopter air resonance problem in hover with active controls; and (4) optimum design of rotor blades for vibration reduction in forward flight.
Response studies of rotors and rotor blades with application to aeroelastic tailoring
1982-12-01
Report
No indication
English
AEROELASTIC TAILORING OF COMPRESSOR BLADES
British Library Conference Proceedings | 2022
|Aeroelastic response characteristics of rotor blades
AIAA | 1980
|Aeroelastic Analysis of Helicopter Rotor Blades
AIAA | 2004
|