Abstract
The mass reduction of satellite solar arrays results in significant panel flexibility. When such structures are launched there is a possible striking at one with another dynamically, leading ultimately to structural damage during the launch stage. To prevent this, rubber snubbers are mounted at well chosen points of the structure and they act as one sided linear spring; as a negative consequence, the dynamic of these panels becomes nonlinear. In this paper a solar array and a snubber are simply modeled as a linear Euler-Bernoulli beam with a one sided linear spring respectively. In this investigation, a numerical and an experimental study of a beam striking a one-sided spring under harmonic excitation is presented. The finite element approximation is used to solve the partial differential equations governing the structural dynamics. The models are subsequently validated and updated with experiments.
Connections
Explore this paper’s authors, topics and related work.
Building this map preview
BZPEER is loading the nearby papers, people, topics and institutions for this page.
Reviews 0
Write a review
No reviews yet.
Discussion 0
Add a comment
No comments yet.