Add to ORKGInternational audienceIn order to save mass of satellite solar arrays, the flexibility of the panels becomes not negligible and they may strike each other; this may damage the structure. 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. The finite element approximation is used to solve partial differential equations governing the structural dynamic. Frequency sweep has been performed numerically to study the dynamic behavior. Non linear normal modes are under stud
The purpose of the present thesis is to furnish diverse studies on the dynamic response of satellite...
In order to be cost-effective, space structures must be extremely light-weight, and subsequently, ve...
Recent NASA mission plans require spacecraft to undergo potentially significant maneuvers (or dynami...
International audienceThe mass reduction of satellite solar arrays results in significant panel flex...
The mass reduction of satellite solar arrays results in significant panel flexibility, so possibly s...
International audienceSolar arrays are structures which are connected to satellites; during launch, ...
In this paper the dynamic behaviour of a multi degree of freedom beam model of a solar array struct...
In this paper the dynamic behaviour of a multi degree of freedom beam model of a solar array structu...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
The thesis consists of two parts presented in four chapters. The first one deals with the modelling,...
In order to be cost effective, space structures must be extremely light weight, and subsequently, ve...
The thesis consists of two parts presented in four chapters. The first one deals with the modelling,...
The purpose of the present thesis is to furnish diverse studies on the dynamic response of satellite...
In order to be cost-effective, space structures must be extremely light-weight, and subsequently, ve...
Recent NASA mission plans require spacecraft to undergo potentially significant maneuvers (or dynami...
International audienceThe mass reduction of satellite solar arrays results in significant panel flex...
The mass reduction of satellite solar arrays results in significant panel flexibility, so possibly s...
International audienceSolar arrays are structures which are connected to satellites; during launch, ...
In this paper the dynamic behaviour of a multi degree of freedom beam model of a solar array struct...
In this paper the dynamic behaviour of a multi degree of freedom beam model of a solar array structu...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
In this paper the nonlinear dynamic behaviour of two simplified solar array systems is investigated ...
The thesis consists of two parts presented in four chapters. The first one deals with the modelling,...
In order to be cost effective, space structures must be extremely light weight, and subsequently, ve...
The thesis consists of two parts presented in four chapters. The first one deals with the modelling,...
The purpose of the present thesis is to furnish diverse studies on the dynamic response of satellite...
In order to be cost-effective, space structures must be extremely light-weight, and subsequently, ve...
Recent NASA mission plans require spacecraft to undergo potentially significant maneuvers (or dynami...