Abstract: An assembly includes at least one first collection of a plurality of spacecraft intended to be fastened to a launcher during a launch phase, wherein the spacecraft are arranged about a central axis (Z) in a given transverse plane perpendicular to the central axis, the spacecraft having edges along a longitudinal axis and being moreover arranged in such a way that a spacecraft is linked to a neighboring spacecraft of the collection by one edge by means of at least one fastener (B) positioned on the edge, so as to mechanically hold the spacecraft to one another, and a satellites-launcher adaptor to which the spacecraft are fastened in a transverse plane.

Abstract: A deployment device intended to be positioned on a bearing structure, includes a first instrument and a second instrument, a deployment mechanism comprising: a main arm connected to a face of the bearing structure at a first attachment point, on the one hand, and to the first instrument on the other hand, the second instrument being connected to the main arm, a main motor configured to actuate the main arm in relation to the face, a secondary motor configured to actuate the second instrument in relation to the main arm, and in that the two instruments are suitable for passing from a stored configuration, one over the other, on the face of the bearing structure, to a deployed configuration wherein the two instruments are at a distance from one another and from the bearing structure, and/or vice versa.

Abstract: An assembly includes at least one first collection of a plurality of spacecraft intended to be fastened to a launcher during a launch phase, wherein the spacecraft are arranged about a central axis (Z) in a given transverse plane perpendicular to the central axis, the spacecraft having edges along a longitudinal axis and being moreover arranged in such a way that a spacecraft is linked to a neighboring spacecraft of the collection by one edge by means of at least one fastener (B) positioned on the edge, so as to mechanically hold the spacecraft to one another, and a satellites-launcher adaptor to which the spacecraft are fastened in a transverse plane.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for receiving, at the one or more wireless access points and from a first device, a request to connect to a first network through a wireless network managed by the one or more wireless access points, wherein the one or more wireless access points is controlling access to the first network through a plurality of ports; determining each port in the plurality of ports is connected to a respective device, each respective device being allowed to access the first network through the respective port; and adding the first device to a queue, wherein the queue includes at least a second device that was added prior to the first device, where devices in the queue are not allowed to access the first network while in the queue.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for receiving, at the one or more wireless access points and from a first device, a request to connect to a first network through a wireless network managed by the one or more wireless access points, wherein the one or more wireless access points is controlling access to the first network through a plurality of ports; determining each port in the plurality of ports is connected to a respective device, each respective device being allowed to access the first network through the respective port; and adding the first device to a queue, wherein the queue includes at least a second device that was added prior to the first device, where devices in the queue are not allowed to access the first network while in the queue.

Abstract: The invention proposes a solution to the problem of installing an antenna with long focal length on a satellite, and, as a non-limiting example, on satellites at a height that is less than the required focal length. It is based, on the one hand, on a reflector stored “inverted and head down”, and, on the other hand, on a deployment movement sequence employing a long arm taken up in the top portion of the reflector via an articulation (1 axis) and a conventional deployment mechanism (1 or 2 axes).

Abstract: Techniques are provided for implementing a rating engine that processes events about usage information regarding a product or service used by customers of the product/service. The rating engine represents a connected graph of objects whose function is to accept input (if necessary), perform one or more operations, and generate a result that is used to determine which other object to execute. The input might include information about an “event” that indicates usage information of the product/service by a particular customer. Because not all objects need to be executed to determine the appropriate response for some events, many computing resources can be used to process subsequent events.

Abstract: The invention proposes a solution to the problem of installing an antenna with long focal length on a satellite, and, as a non-limiting example, on satellites at a height that is less than the required focal length. It is based, on the one hand, on a reflector stored “inverted and head down”, and, on the other hand, on a deployment movement sequence employing a long arm taken up in the top portion of the reflector via an articulation (1 axis) and a conventional deployment mechanism (1 or 2 axes).

Abstract: A heat transfer system includes a heat transfer passage in the vicinity of a source of dissipated heat on a satellite to collect heat dissipated by the source and a fluid loop including an evaporator having over part of its path a maximum surface area of its external walls in contact with external walls of the heat transfer passage.

Abstract: A heat transfer system includes a heat transfer passage in the vicinity of a source of dissipated heat on a satellite to collect heat dissipated by the source and a fluid loop including an evaporator having over part of its path a maximum surface area of its external walls in contact with external walls of the heat transfer passage.

Abstract: The invention provides a deployable radiator for a space vehicle such as a satellite. The radiator of the invention has two radiating faces, one of which is insulating over a portion of its area so that during launch and while the satellite is being moved onto station, with the radiator in the stored position, it naturally serves to keep the highest possible temperature on board the vehicle.

Abstract: The invention provides a deployable radiator for a space vehicle such as a satellite. The radiator of the invention has two radiating faces, one of which is insulating over a portion of its area so that during launch and while the satellite is being moved onto station, with the radiator in the stored position, it naturally serves to keep the highest possible temperature on board the vehicle.