Abstract: The present invention relates to a process for producing a three-dimensional (3D) object by employing a three-dimensional (3D) printing process wherein a granulate having an particle size in the range of 0.2 to 1 mm is used as a starting material to be printed within said 3D printing process, employing a 3D extrusion printer. In one preferred embodiment, the process according to the present invention is employed for producing a 3D greenbody. The invention further relates to 3D objects as such and the corresponding processes for obtaining such 3D objects, in particular a 3D green body, a 3D brown body and a 3D sintered body.

Abstract: A space vehicle element configured to be at least partially destroyed during re-entry of a space vehicle into the atmosphere comprises a heat generating part comprising a metallo-thermal composition for providing additional heat during re-entry of the space vehicle into the atmosphere by an exothermic reaction of the metallo-thermal composition. The destruction of the space vehicle element is expedited by the additional heat provided by the heat generating part. The heat generating part is at least partially integrated within the space vehicle element or at least partially surrounds a portion of the space vehicle element. The application further relates to a corresponding method of manufacturing a space vehicle element configured to be destroyed during re-entry of the space vehicle into the atmosphere.

Abstract: A space vehicle element configured to be at least partially destroyed during re-entry of a space vehicle into the atmosphere comprises a heat generating part comprising a metallo-thermal composition for providing additional heat during re-entry of the space vehicle into the atmosphere by an exothermic reaction of the metallo-thermal composition. The destruction of the space vehicle element is expedited by the additional heat provided by the heat generating part. The heat generating part is at least partially integrated within the space vehicle element or at least partially surrounds a portion of the space vehicle element. The application further relates to a corresponding method of manufacturing a space vehicle element configured to be destroyed during re-entry of the space vehicle into the atmosphere.

Abstract: According to the invention, a “Geneva” movement mechanism is used which is turned in one direction or the other by an electric motor. The mechanism comprises a “Maltese” cross turning about the axis of rotation of the rotor and supporting an annular piece. The Maltese cross is mechanically coupled to a ball screw lying on said axis of rotation so as to transform the turning notion into motion that includes a linear component, thereby enabling the annular piece to be moved at will towards and away from the rotor so as to make it possible to obtain contact and then blocking in a self-blocking manner against a fixed wall, or on the contrary so as to release the rotor by moving the annular piece in translation in the opposite direction. The invention is applicable to an inertia wheel for controlling the attitude of a satellite.

Abstract: According to the invention, a “Geneva” movement mechanism is used which is turned in one direction or the other by an electric motor. The mechanism comprises a “Maltese” cross turning about the axis of rotation of the rotor and supporting an annular piece. The Maltese cross is mechanically coupled to a ball screw lying on said axis of rotation so as to transform the turning notion into motion that includes a linear component, thereby enabling the annular piece to be moved at will towards and away from the rotor so as to make it possible to obtain contact and then blocking in a self-blocking manner against a fixed wall, or on the contrary so as to release the rotor by moving the annular piece in translation in the opposite direction. The invention is applicable to an inertia wheel for controlling the attitude of a satellite.