Experimental and numerical investigation of a novel strut-mounted roller-screw inerter for helicopter vibration attenuation

Engineering

• Main Rotor 100%
• Non-Linear Effect 50%
• Critical Condition 50%
• Lumped Parameter 50%
• Axisymmetric 50%
• Excitation Force 50%
• Ideal Solution 50%
• Reduce Vibration 50%
• Gearbox 50%
• Vibratory Loads 50%
• Rotor Excitation 50%