Abstract: A system and method for transferring a satellite from an initial orbit into a mission orbit. The method includes anchoring to the satellite of an external unit having a tank containing a reserve of propellants. The system includes an autonomous spacecraft having an electric propulsion module and a small internal reserve of propellants, located in a parking orbit close to the initial orbit. The spacecraft with the external unit attached to the satellite is docketed in an initial orbit, to produce a fluidic connection of the propellant tank of the external unit to the propulsion module of the spacecraft. The external unit and satellite is transferred into the mission orbit by the electric propulsion module of the spacecraft supplied with propellants directly from the external unit, thereby releasing the satellite into the mission orbit.

Abstract: A structure for integrating mobile services, includes a top structure and a bottom structure, the top structure including: a device suitable for selecting, according to selection criteria, a service domain so as to determine whether a requested application, such as voice applications, SDS applications, or IP data applications, belongs to the domain of legacy services or IP service; a device capable of managing the various requests; and a device capable of providing APIs for the voice, SDS, and IP applications, the bottom structure including: a unit for IP routing towards the wireless network, ensuring the IP routing of data to the suitable IP networks, configured so as to take into account the configuration of the network, the user profile, and the provision of QoS and security; and a unit for managing users, in particular in terms of user registration, deregistration, mobility and security, such as the use of the SSO.

Abstract: In order to offer domain name resolution services vis-à-vis resources of various security domains of a communication network, an item of equipment, on reception of a domain name resolution request coming from a client device, performs: authentication operations checking whether the client device that sent the request was previously registered; authorisation operations checking whether the client device actually has right of access to the resources of said domain name; and domain name resolution operations by means of a cache storing associations of IP addresses and domain names. The cache is populated by means of the results of domain name resolutions performed by external name servers to which said equipment resort to via respective secure tunnels, independently of said security domains, when the cache does not include data allowing to effect the domain name resolution required.

Abstract: A method for acquiring images using a constellation of satellites in non-geosynchronous terrestrial orbit. The satellites include respective devices for inter-satellite communication. An aggregate of work plans intended for various satellites is formed. A ground station transmits the aggregate intended for one satellite. The satellite receiving the aggregate retransmits the aggregate intended for at least one other satellite from the ground station. Each satellite receiving the aggregate from another satellite re-transmits the aggregate intended for at least one other satellite. Each satellite recovers its work plan from the aggregate received.

Abstract: A device for electrical connection intended to connect a super-insulating mattress to a structural panel of a spacecraft, said connection device comprising: a conducting sleeve having an axis extending in a first direction, said sleeve comprising a device for axial fastening of the insulating mattress and a support, a conductive pin suitable for being arranged in said sleeve, an elastic element carried by said support, said elastic element being suitable for exerting a force on the pin in a direction substantially perpendicular to the first direction in order to press the pin against the sleeve. A method for assembling a female portion of a device for electrical connection to a super-insulating mattress, a super-insulating mattress and a spacecraft.

Abstract: A satellite includes: at least one optical photography instrument including a main lens having an optical axis and the optical instrument having a field of view; at least one launcher interface system, intended for being removably secured to a satellite interface system of a launcher of the satellite; a linking device between the launcher interface and the optical instrument extending substantially parallel to the optical axis of the main lens between an upper end and a lower end; the launcher interface system is connected to the linking device by the lower end and the optical axis of the optical instrument is directed from the upper end towards the lower end of the linking device, the launcher interface system being outside the field of view of the instrument.

Abstract: A method of controlling the attitude of a spacecraft in spinning around itself with a non-zero total angular momentum HTOT. The spacecraft includes a set of inertia flywheels configured to form an internal angular momentum HACT. The axis of the total angular momentum HTOT is aligned with a principal axis of inertia of the spacecraft, in the course of which the inertia flywheels are controlled to form an internal angular momentum HACT. The following expression, in which J is the inertia matrix of the spacecraft: Hact×J?1(Htot?J?1Htot) is negative if the principal axis of inertia targeted is the axis of maximum inertia of the spacecraft and is positive if the principal axis inertia targeted is the axis of minimum inertia of the spacecraft.

Abstract: A device for the shock-absorbing attachment of two elements to be assembled, the attachment device including: an inner part that is tubular along an attachment axis; an outer part that is tubular along the attachment axis, and hollow, the inner part being accommodated in the outer part such that the outer surface of the inner part is facing the inner surface of the outer part; an elastomer layer between the outer part and the inner part, the elastomer layer, when seen in section in a longitudinal plane including the attachment axis, including: to either side of the attachment axis, at least three so-called longitudinal portions, and at least two so-called transverse portions.

Abstract: A device for determining the attitude or variation in attitude of a satellite fitted with an attitude control system comprising at least one inertial actuator. The inertial actuator comprises a rotary element mounted to rotate about an axis of rotation. The rotation of the rotary element is controlled to generate a torque to control controlling the attitude of the satellite. The angular sensor of the device measures the angular rotation of the rotary element about its axis of rotation. The computation unit determines the attitude or variation in attitude of the satellite induced by the rotation of the rotary element as a function of the measurements of angular rotation of the rotary element by the angular sensor. A satellite carrying such a device and a method for determining the attitude or variation in attitude.

Abstract: A method for planning the acquisition of images of areas Z1, . . . , ZN of the Earth, by a spacecraft on a mission around the Earth. Each area Zi of the Earth being associated with a request Ri such that a visual accessibility time interval Ti corresponds to the area Zi. For each interval Ti, discrete acquisition opportunities for acquiring area Zi are determined such that a start date, a period of execution, a local kinematic constraint and a weight is associated with each of the discrete acquisition opportunities. The discrete acquisition opportunities for acquiring areas Zi are grouped into a set D. The discrete acquisition opportunities Di of the set D are categorized by ascending start date. The kinematic compatibility between the discrete acquisition opportunities of set D is assessed. An optimal sequence of discrete acquisition opportunities is determined having a maximum weight, and being kinematically compatible.

Abstract: A method for controlling the orbit of a satellite in earth orbit. The orbit of the satellite is controlled by commanding, according to a maneuver plan, a propulsion system having at least one thruster and a transporter to move the propulsion system. The maneuver plan includes at least two orbit-control maneuvers. The thrust powers of the propulsion system during the two orbit control maneuvers have respective thrust directions that are not parallel in an inertial frame of reference. Each thrust power is determined to simultaneously control the inclination and the position of the orbit of the satellite as well as to form a momentum that is suitable for unloading a device for storing angular momentum of the satellite in a plane orthogonal to the direction of thrust of the thrust power.

Abstract: A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.

Abstract: A method for suppressing a spurious signal in a payload signal supplied by a receiving antenna of a payload of a satellite. The satellite also includes an array of measurement antennas supplying measurement signals. The measurement signals are combined with the payload signal. Reference weighting coefficients for weighting the measurement signals are determined as a function of the combined signals. A reference beam is formed by combining the measurement signals weighted based on the reference weighting coefficients. Anti jamming weighting coefficients for weighting the payload signal and the reference beam are determined. An anti jammed beam is formed by combining the payload signal and the reference beam weighed based on the corresponding anti jamming weighting coefficients.

Abstract: A photovoltaic generator deployable for a satellite stabilized on three axes. The photovoltaic generator includes an assembly of planar panels articulated with respect to each other, and an attachment arm to the structure of the body of the satellite. In a first or launch position of the photovoltaic generator, the planar panels are folded one over the other. In a second or deployed position of the photovoltaic generator, the planar panels are fully deployed with at least a part of the planar panels being photovoltaic panels. At least one planar panel consists of a thermal radiator, with the radiative face thereof being orientated to be opposite the face of the photovoltaic panels carrying the photovoltaic sensors when the photovoltaic generator is in the deployed position. This radiative face is termed the “shade” face, and the face opposite the panel shaped radiator is termed the “sun” face.

Abstract: The subject matter of the invention is a method for draping on a form, which includes a step of deposition on the form of a first fold support in the form of one or more polymer nonwoven fabrics. The invention further relates to a thermoplastic nonwoven material manufactured with a nonwoven fabric of polymer fibers.

Abstract: In the context of half-duplex communications in a communication network composed of a plurality of sub-networks associated respectively with supernode devices, a supernode device receiving a floor request: transmits a floor pre-grant message; determines a timer duration according to a distribution law f?(t) for time period between a floor release and the next floor control, and a network-latency distribution law f?(d), so that the probability of subsequent dismissing of the floor control is below a predefined threshold; and broadcasts the data transmitted in the context of the floor control, when the timer has elapsed. When a floor request with higher priority is detected before the expiration of the timer, the supernode device does not broadcast the data and notifies that the floor control is finally refused.

Abstract: A method and device enable the linear separation of two elements attached to each other through two connecting plates of the first element and the second element respectively. An arrangement connecting and separating the two connecting plates are mixed and comprise a layer. The connecting arrangement comprises soldering, glue, or resin, whereas the separating arrangement comprises thermite. These elements can also be layered rather than mixed. An electrical triggering of this assembly causes its quick and local warming-up and thus enables both of these elements to be separated.

Abstract: Disclosed is an artificial satellite including one face from the North face and the South face supporting at least one main radiator having an outer face turned towards space and an inner face opposite the outer face. The satellite includes a bearing structure carrying the North face, the South face, the East face and the West face. At least one part of the at least one main radiator protrudes from at least one face from the East face and the West face. The inner face of the at least one protruding part is covered with a high infrared emissivity material. The value of the dimension of the at least one protruding part is between 19% and 50% of the value of the distance between the East and West faces.

Abstract: Disclosed is a spacecraft including:—a housing defining an inner space and an outer space, the housing having a first surface and a second surface opposite the first surface; a first radiator and a second radiator supported by the first surface and the second surface, respectively, the first radiator and the second radiator each having a main inner surface, a main outer surface opposite the main inner surface and side surfaces. The spacecraft further includes a first auxiliary radiator and a first auxiliary heat-transfer device thermally connecting the first auxiliary radiator to the main inner surface of the second radiator, the first auxiliary radiator being arranged in a first portion of the outer space, the first portion being defined by the main outer surface of the first radiator and by the first planes containing the side surfaces of the first radiator.

Abstract: In order to detect congestion on a transmission link, endpoint items of network equipment are associated with congestion-detection applications. Per class of service, one application sends to the other control messages indicating volumes of data transmitted by the concerned item of network equipment via the transmission link. On reception of the control messages, the other application obtains information on volumes of data received by the other item of network equipment. By determining a first divergence in volumes of data transmitted between two control messages and a second divergence in volumes of data received, between two control messages, this other application is able to detect a situation of congestion on the transmission link occurring for one or more classes of service, and to generate an alarm signal accordingly.