Airbus Group Sas

Astrium Sas

Jean-Francois Geneste

Jean-Francois Poussin

A spacecraft includes: a body a surface of revolution connected with the body, and a heat engine positioned at the center of the surface of revolution. The surface of revolution has a substantially open hollow torus shape with a transverse cross-section of a circle and two diametrically opposite portions each having a curvature extending from the circle. A first portion of the diametrically opposite portions has an opening and forms a solar concentrator for concentrating solar radiation in the direction of the heat engine. The first portion forms a primary solar radiation reflector. A second portion of the diametrically opposite portions is coaxial with the first portion and forms a secondary solar radiation reflector. The opening is configured so that the solar radiation passes in the direction of the center of the surface of revolution after reflection at the primary and secondary reflectors.

Spacecraft architecture having torus-shaped solar concentrator

A three-dimensional structural framework having inflatable rings and a T-shaped cross-section along a plane passing through an axis of revolution of the inflatable rings in an inflated state. Shape-stabilizing elements are provided to stabilize the shape of the structural framework in space. Two inflatable rings are connected by at least one shape-stabilizing element. The structural framework is preferably used to produce stratospheric balloons.

Stratospheric balloon having improved compressive strength

A method is disclosed for placing a satellite in an operational orbit. The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device. The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher. The separate propulsion device is controlled by a satellite. The satellite is transferred from the transfer orbit to an intermediate orbit by means of the separate propulsion device. The separate propulsion device is separated from the satellite in the intermediate orbit. The satellite then enters and operational orbit from the intermediate orbit by means of its own satellite propulsion system. The intermediate orbit is disposed between the transfer and operational orbits, and is in relatively close proximity to the operational orbit but is far enough away from the operational orbit to prevent possible interferences.

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Toulouse, France

Jean-Francois Geneste