Vibration Reduction of Helicopter Blade Using Variable Dampers: A Feasibility Study

By National Aeronautics and Space Administration

In the report, the investigation of controlling helicopter-blade lead-lag vibration is described. Current practice of adding passive damping may be improved to handle large dynamic range of the blade with several peaks of vibration resonance. To minimize extra-large damping forces that may damage the control system of blade, passive dampers should have relatively small damping coefficients, which in turn limit the effectiveness. By providing variable damping, a much larger damping coefficient to suppress the vibration can be realized. If the damping force reaches the maximum allowed threshold, the damper will be automatically switched into the mode with smaller damping coefficient to maintain near-constant damping force. Furthermore, the proposed control system will also have a fail-safe feature to guarantee the basic performation of a typical passive damper. The proposed control strategy to avoid resonant regions in the frequency domain is to generate variable damping force in combination with the supporting stiffness to manipulate the restoring force and conservative energy of the controlled blade system. Two control algorithms are developed and verified by a prototype variable damper, a digital controller and corresponding algorithms. Primary experiments show good potentials for the proposed variable damper: about 66% and 82% reductions in displacement at 1/3 length and the root of the blade respectively.Lee, George C. and Liang, Zach and Gan, Quan and Niu, TiechengAmes Research CenterHELICOPTERS; ROTORS; VIBRATION DAMPING; ALGORITHMS; RESONANCE; FAIL-SAFE SYSTEMS; VIBRATION

• Format: Paperback
• Language: English
• ISBN: 1723908770
• ISBN13: 9781723908774
• Release Date: January 1
• Publisher: Independently Published
• Length: 70 Pages
• Weight: 0.41 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"