Accession Number : ADA261809


Title :   Helicopter Forced Response Vibration Analysis Method RTVIB20


Descriptive Note : Final rept. Jan 1990-Jun 1992


Corporate Author : ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD


Personal Author(s) : Fries, Joseph


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a261809.pdf


Report Date : Feb 1993


Pagination or Media Count : 40


Abstract : This report describes a helicopter vibration analysis method. In the method the rotor forcing for a single main rotor is calculated by integrating the forces and moments at the rotor center, and then applying them to a rigid helicopter airframe. The vibrations (any place in the airframe) are calculated as the to the applied hub center forces and moments. The method of analysis allows for dissimilar blades in the main rotor to simulate various type of blade damage and the resulting increase vibrations transmitted into the airframe. The analysis method is generic and can be used to analyze any single main rotor helicopter. An application is made for the UH-60A helicopter, resulting from the loss of outboard sections of one blade of the rotor, and the resulting vibrations in the cockpit are calculated.


Descriptors :   *VIBRATION , *ROTOR BLADES(ROTARY WINGS) , *ROTOR BLADES , *HELICOPTERS , COMPUTATIONS , DAMAGE , KILL PROBABILITIES , AIRFRAMES , AERODYNAMICS , OUTBOARD , HUBS , AERODYNAMIC FORCES , COCKPITS , DAMAGE ASSESSMENT , MOMENTS , HELICOPTER ROTORS


Subject Categories : Helicopters
      Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE