Abstract

Boeing Helicopters has developed and incorporated a nonlinear lag damper model into the TECH-01 interdisciplinary rotor analysis program. This modification has improved the predicted chordwise bending moments. The model represents the nonlinear kinematic effects of the damper mounting geometry, and the nonlinear characteristics of elastomeric and hydraulic dampers. This paper will show correlation with elastomeric damper bench test results, illustrate the importance of damper kinematics on blade loads, and show some correlation of chordwise bending moment loads on rotors with hydraulic and elastomeric lag dampers.

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