Development of a finite element human vibration model for use in spacecraft coupled loads analysis

Abstract

Finite element human vibration models were developed and implemented for use in human-tended spacecraft-coupled loads analysis, an analytical process used to predict low-frequency spacecraft loads which occur during dynamic phases of flight of such as launch, ascent, or ascent aborts. Human vibration may also affect stress predictions for spacecraft systems which the crew interacts with, such as crew seats and crew impact attenuation systems. These human vibration models are three-dimensional, distributed-mass representations of 1st-percentile female, 50th-percentile male, and 99th-percentile male American crew members and provide a relatively simple linear and low-load representation of the nonlinear dynamic response of a seated human. The most significant features of these finite element models are anthropometrically based geometric human mass distribution, soft tissue vibration attributes, and skeleton and joint stiffness.

Hypersingular integral equations of the first kind: A modified homotopy perturbation method and its application to vibration and active control

“…In the mathematical modeling for which the hypersingular integral equations 1 own significant place in different scientific fields, elasticity, solid mechanics and electrodynamics, vibration, active control and nonlinear vibration 2–4 can be modeled into the hypersingular integral equations. In Liu and Rizzo, 5 a weaker singular form of the hypersingular boundary integral equation which applied to acoustic wave problems, was proposed.…”