A general purpose nonlinear rigid body mass finite element for application to rotary wing dynamicsThe Second Generation Comprehensive Helicopter Analysis System employs the present formulation of the general-purpose nonlinear rigid body mass finite element, which represents the hub masses, blade tip masses, and pendulum vibration absorbers. The rigid body mass element has six degrees of freedom, and accounts for gravitational as well as dynamic effects. A consequence of deriving the element's equations from various physical principles is that, prior to the transformation which couples the rigid body mass element to the rotor blade finite element, the forces obtained for each element are fundamentally different; this is true notwithstanding the degrees-of-freedom of each element are parameterized using the same coordinates.
Document ID
19920064300
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hamilton, B. K. (NASA Ames Research Center Moffett Field, CA, United States)
Straub, F. K. (McDonnell Douglas Helicopter Co. Mesa, AZ, United States)
Ruzicka, G. C. (U.S. Army, Aeroflightdynamics Directorate; NASA, Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: AHS International Specialists'' Meeting on Rotorcraft Basic Research