Dynamics of a Strongly Nonlinear Spacecraft Structure Part I: Experimental Identification

This paper deals with the global existence, and the uniqueness of the state trajectories for a mathematical model of a population consisting of several species with coupled

Compilation of the composite elastic modulus deduced from nano and microindentation tests applied to the porous oxide film as a function of the relative indentation depth where the

A computational model, which uses a nonlinear beam theory with rotatory inertia and shear deformation of the beam cross section, as well as the coupling between

APPLICATION TO A MODEL OF FLAME In this section, we illustrate the identification method introduced above by implementing it on data ( u, x ∗ ) elab- orated from numerical simulations

Its shape involving two folded lines and the associated stability properties provide an analytical tool to explain and predict the existence of three regimes: periodic response

Secondly, we generalize those methods to study a many-node thermal model of a spacecraft: this model also has a stable steady state under constant heat inputs that becomes a limit

Com- parisons to nonlinear SU methods will be addressed in the next paragraph (scenario 2). Table III shows the RNMSEs obtained with the proposed and the FLCS algorithms for this

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