Publication Date:
2019-06-27
Description:
A theoretical analysis is developed for a coupled helicopter rotor system to allow determination of the loads and dynamic response behavior of helicopter rotor systems in both steady-state forward flight and maneuvers. The effects of an anisotropically supported swashplate or gyroscope control system and a deformed free wake on the rotor system dynamic response behavior are included.
Keywords:
AERODYNAMICS
Type:
NASA-CR-2453
Format:
application/pdf