42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Communication via computer terminals, by digital transmission or by satellite; Satellite communication services; Satellite transmission services; Satellite, cable, network transmission of sounds, images, signals and data Providing temporary use of non-downloadable communications software for connecting users over satellite networks; providing temporary use of non-downloadable computer software used for the control of voice controlled information and communication devices
2.
SATELLITE SYSTEM AND METHOD FOR ADDRESSING RAIN FADE
A method for operating a satellite, wherein a beam frequency-assignment schedule for the satellite is based on rain fade information. And a communications payload for a satellite that is capable of implementing the changes required by the schedule.
H04W 36/14 - Resélection d'un réseau ou d'une interface hertzienne
H04W 16/22 - Outils ou modèles de simulation de trafic
H04W 40/02 - Sélection d'itinéraire ou de voie de communication, p.ex. routage basé sur l'énergie disponible ou le chemin le plus court
H04W 48/04 - Restriction d'accès effectuée dans des conditions spécifiques sur la base des données de localisation ou de mobilité de l'utilisateur ou du terminal, p.ex. du sens ou de la vitesse de déplacement
H04W 48/06 - Restriction d'accès effectuée dans des conditions spécifiques sur la base des conditions de trafic
H04W 48/18 - Sélection d'un réseau ou d'un service de télécommunications
H04B 10/118 - Dispositions spécifiques à la transmission en espace libre, c. à d. dans l’air ou le vide spécialement adaptées aux communications par satellite
A method for operating a satellite, wherein a beam frequency-assignment schedule for the satellite is based on rain fade information. And a communications payload for a satellite that is capable of implementing the changes required by the schedule.
H04W 36/14 - Resélection d'un réseau ou d'une interface hertzienne
H04W 40/02 - Sélection d'itinéraire ou de voie de communication, p.ex. routage basé sur l'énergie disponible ou le chemin le plus court
H04W 48/04 - Restriction d'accès effectuée dans des conditions spécifiques sur la base des données de localisation ou de mobilité de l'utilisateur ou du terminal, p.ex. du sens ou de la vitesse de déplacement
H04W 48/06 - Restriction d'accès effectuée dans des conditions spécifiques sur la base des conditions de trafic
H04W 16/22 - Outils ou modèles de simulation de trafic
H04W 48/18 - Sélection d'un réseau ou d'un service de télécommunications
H04B 10/118 - Dispositions spécifiques à la transmission en espace libre, c. à d. dans l’air ou le vide spécialement adaptées aux communications par satellite
A configuration for a satellite constellation has a plurality of planes, each plane including a plurality of satellites therein, at least some of the planes situated at a different altitude than other of the planes, in some embodiments, all planes contain the same number of satellites; in some other embodiments, at least one plane includes a different number of satellites than the other planes in the constellation, in some embodiments, the satellites in each plane are evenly spaced.
A satellite communications system comprising satellites in low earth orbit (LEO) as well as one or more satellites in orbits other than LEO, such as satellites in medium earth orbit (MEO) and/or satellites in geostationary orbit (GEO). The system routes data packets, such as may be received from the Internet, to either the LEO satellites or non-LEO satellites in accordance with routing logic. In some embodiments, the routing logic is based on the latency of the communications.
A satellite communications system comprising satellites in low earth orbit (LEO) as well as one or more satellites in orbits other than LEO, such as satellites in medium earth orbit (MEO) and/or satellites in geostationary orbit (GEO). The system routes data packets, such as may be received from the Internet, to either the LEO satellites or non-LEO satellites in accordance with routing logic. In some embodiments, the routing logic is based on the latency of the communications.
Improved systems and methods and techniques for satellite-based Internet access and transport that provides a broader view of satellite-based access facilities including full demand and supply in any locale, at any scale, independent of SNP/ACP coverage or Beam mobility. Accordingly, methods and systems according to aspects of the present disclosure, advantageously dimension and deploy the IP services (demand) against a predictable and geo-spatially-computable supply model so that no administrative region (i.e. AR) is oversubscribed beyond a desired threshold in any of its capacity allocations (CAs (supply)) areas.
H04W 40/12 - Sélection d'itinéraire ou de voie de communication, p.ex. routage basé sur l'énergie disponible ou le chemin le plus court sur la base de la qualité d'émission ou de la qualité des canaux
A user-terminal clamp that receives a user terminal of a satellite communications system, wherein the clamp clamps to a roof of a structure in either of two orthogonal orientations. The clamp includes a frame having a pair of movable clamping members that are actuated by a handle. The frame includes slots or channels that receive ribs that are disposed on the underside of the user terminal.
F16B 2/18 - Brides ou colliers, c. à d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif utilisant des cames, des leviers, des excentriques ou des rotules
A user-terminal clamp that receives a user terminal of a satellite communications system, wherein the clamp clamps to a roof of a structure in either of two orthogonal orientations. The clamp includes a frame having a pair of movable clamping members that are actuated by a handle. The frame includes slots or channels that receive ribs that are disposed on the underside of the user terminal.
F16B 2/18 - Brides ou colliers, c. à d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif utilisant des cames, des leviers, des excentriques ou des rotules
10.
ADMISSION CONTROL SYSTEM FOR SATELLITE-BASED INTERNET ACCESS AND TRANSPORT
Disclosed are improved systems and methods and techniques for satellite-based Internet access and transport that provides a broader view of satellite-based access facilities including full demand and supply in any locale, at any scale, independent of SNP/ACP coverage or Beam mobility. Accordingly, methods and systems according to aspects of the present disclosure, advantageously dimension and deploy the IP services (demand) against a predictable and geo-spatially-computable supply model-so that no (i.e. AR) is oversubscribed beyond a desired threshold in any of its CAs (supply) area.
H04W 40/12 - Sélection d'itinéraire ou de voie de communication, p.ex. routage basé sur l'énergie disponible ou le chemin le plus court sur la base de la qualité d'émission ou de la qualité des canaux
11.
SATELLITE SYSTEM HAVING INCREASED COMMUNICATIONS CAPACITY AND METHODS FOR INCREASING THE CAPACITY OF SATELLITE SYSTEMS
A reconfigurable satellite access point including a transport-mounting structure and at least one antenna integrated with the transport-mounting structure, the transport-mounting structure allowing the satellite access point to be easily reconfigured between a shipping configuration and an deployed configuration, the satellite access point in the shipping configuration having a form factor of a shipping container which allows the satellite access point to be shipped to a remote satellite access site on earth and the satellite access point in the deployed configuration revealing the at least one antenna to the sky at the satellite access site. Further, a method for constructing and rapidly deploying a satellite access site, the method including integrating at least one antenna with a transport-mounting structure to create a satellite access point, configuring the satellite access point into a shipping configuration wherein the satellite access point has a form factor of a shipping container, shipping the satellite access point to a desired location on earth for the satellite access site, and reconfiguring the satellite access point into an deployed configuration at the satellite access site to reveal the at least one antenna to the sky.
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
H01Q 19/13 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p.ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes où les surfaces sont concaves la source rayonnante primaire étant un élément rayonnant unique, p.ex. un dipôle, une fente, une terminaison de guide d'onde
14.
RECONFIGURABLE SATELLITE ACCESS POINTS AND SATELLITE ACCESS SITES
A reconfigurable satellite access point including a transport‐mounting structure and at least one antenna integrated with the transport‐mounting structure, the transport‐mounting structure allowing the satellite access point to be easily reconfigured between a shipping configuration and an deployed configuration, the satellite access point in the shipping configuration having a form factor of a shipping container which allows the satellite access point to be shipped to a remote satellite access site on earth and the satellite access point in the deployed configuration revealing the at least one antenna to the sky at the satellite access site. Further, a method for constructing and rapidly deploying a satellite access site, the method including integrating at least one antenna with a transport‐mounting structure to create a satellite access point, configuring the satellite access point into a shipping configuration wherein the satellite access point has a form factor of a shipping container, shipping the satellite access point to a desired location on earth for the satellite access site, and reconfiguring the satellite access point into an deployed configuration at the satellite access site to reveal the at least one antenna to the sky.
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
H01Q 19/13 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p.ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes où les surfaces sont concaves la source rayonnante primaire étant un élément rayonnant unique, p.ex. un dipôle, une fente, une terminaison de guide d'onde
15.
METHOD FOR MAINTAINING SIGNAL-TO-NOISE RATIO AT A USER TERMINAL IN A SATELLITE SYSTEM
A system and method for maintaining signal-to-noise ratio when a user terminal switches beams includes a user terminal that generates beam-pointing information. The beam- pointing information is used either to alter the time at which the user terminal switches communications from a first beam to a second beam transmitted from a satellite or to adjust the attitude of the satellite, thereby correcting any error in pointing angle of the beams transmitted from the satellite to the user terminal.
A system and method for maintaining signal-to-noise ratio when a user terminal switches beams includes a user terminal that generates beam-pointing information. The beam- pointing information is used either to alter the time at which the user terminal switches communications from a first beam to a second beam transmitted from a satellite or to adjust the attitude of the satellite, thereby correcting any error in pointing angle of the beams transmitted from the satellite to the user terminal.
A passive thermal system for use in aerospace vehicles includes a first passive thermal panel having at least one internal resident heat pipe, wherein the first passive thermal panel is further configured to provide an embedded interface between a portion of the resident heat pipe and at least one heat pipe extending from a neighboring passive thermal panel. The embedded interface is facilitated via an internal channel that is adjacent to the internal resident heat pipe. The channel is dimensioned and arranged to receive a portion of a heat pipe extending from a passive thermal panel that will be situated adjacent to the first passive thermal panel. The embedded interface is also facilitated by an arrangement that imparts a compressive force to the non-resident heat pipe that urges it against the resident heat pipe.
B23P 15/26 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe d'échangeurs de chaleur
18.
COMMUNICATION-SATELLITE SYSTEM WITH ENHANCED CAPACITY IN DESIGNATED LOCATIONS
A communication-satellite system for providing communication services to the entire Earth is based on a plurality of satellites in low-earth-orbit (LEO). The satellites orbit the Earth in a plurality of orbits, with multiple satellites in each orbit. This orbital arrangement results in some locations on the surface of the Earth receiving redundant satellite coverage. Embodiments of the present invention can selectively and adaptively rotate the orientation of some of the satellites so as to transfer some of the redundant coverage from locations where it is not needed to locations where the redundant coverage is advantageous.
CONSTELLATION OF SATELLITES IN LOW EARTH ORBITS, EACH SATELLITE COMPRISING AN ATTITUDE CONTROL MODULE FOR ROTATING THE SATELLITE ABOUT ITS ROLL AXIS TO ASSURE EARTH RADIO COVERAGE
A communication-satellite system for providing communication services to the entire Earth is based on a plurality of satellites in low-earth-orbit (LEO). The satellites orbit the Earth in a plurality of orbits, with multiple satellites in each orbit. This orbital arrangement results in some locations on the surface of the Earth receiving redundant satellite coverage. Embodiments of the present invention can selectively and adaptively rotate the orientation of some of the satellites so as to transfer some of the redundant coverage from locations where it is not needed to locations where the redundant coverage is advantageous.
A payload dispenser (100) and a method for populating same with satellites (600) is disclosed. The payload dispenser comprises a shell (102). A plurality of rail assemblies (320) are each configured to receive plural satellites. The satellite laden rail assemblies are then coupled to the shell.
A payload dispenser (100) and a method for populating same with satellites (600) is disclosed. The payload dispenser comprises a shell (102). A plurality of rail assemblies (320) are each configured to receive plural satellites. The satellite laden rail assemblies are then coupled to the shell.
A device and method for estimating the elevation angle of one or more objects surrounding a user terminal, include a light-collecting lens arrangement that collects sky scene light from a wide angle, an eyepiece lens arrangement that collimates the sky scene light collected by the light-collecting lens arrangement, and an elevation limit marking that is superimposed over the sky scene light. The elevation limit marking defines an elevation angle above a horizon of the earth that all the one or more objects in a field of view of the device must remain below so that the user terminal has an unobstructed view of the sky in all azimuthal directions.
A device and method for estimating the elevation angle of one or more objects surrounding a user terminal, include a light-collecting lens arrangement that collects sky scene light from a wide angle, an eyepiece lens arrangement that collimates the sky scene light collected by the light-collecting lens arrangement, and an elevation limit marking that is superimposed over the sky scene light. The elevation limit marking defines an elevation angle above a horizon of the earth that all the one or more objects in a field of view of the device must remain below so that the user terminal has an unobstructed view of the sky in all azimuthal directions.
A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner
A stackable satellite includes a satellite frame and at least one vertical pillar attached to the frame The vertical pillar has an upper end and a lower end. The upper end is coupled to the lower end of the vertical pillar of the satellite above and the lower end is coupled to the upper end of the vertical pillar of the satellite below The vertical pillar receives substantially all of the vertical load of the stackable satellite and any other satellites stacked above Use of such vertical pillars removes the need for a dispenser or substantially lightens the dispenser mass to allow substantially more satellites to be earned in a payload
A stackable satellite includes a satellite frame and at least one vertical pillar attached to the frame. The vertical pillar has an upper end and a lower end. The upper end is coupled to the lower end of the vertical pillar of the satellite above and the lower end is coupled to the upper end of the vertical pillar of the satellite below. The vertical pillar receives substantially all of the vertical load of the stackable satellite and any other satellites stacked above. Use of such vertical pillars removes the need for a dispenser or substantially lightens the dispenser mass to allow substantially more satellites to be carried in a payload.
A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites. Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit. Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner.
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
G05D 3/00 - Commande de la position ou de la direction
G06F 7/00 - Procédés ou dispositions pour le traitement de données en agissant sur l'ordre ou le contenu des données maniées
G06F 17/00 - TRAITEMENT ÉLECTRIQUE DE DONNÉES NUMÉRIQUES Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
28.
PASSIVE THERMAL SYSTEM COMPRISING COMBINED HEAT PIPE AND PHASE CHANGE MATERIAL AND SATELLITES INCORPORATING SAME
A passive thermal system for use in a satellite and other aerospace applications includes a container having a heat-pipe working fluid disposed in a first chamber and a Phase Change Material (PCM) disposed in a second chamber that substantially surrounds the first chamber The first chamber contains a wick for transporting the heat-pipe working fluid. The exterior the first chamber has fins, etc., that extend into the PCM for heat spreading and increased interface area.
F28D 15/02 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p.ex. tubes caloporteurs
B64G 1/50 - Aménagements ou adaptations des dispositifs de contrôle de l'environnement ou des conditions de vie pour la commande de la température
29.
FLUIDICIALLY COUPLED HEAT PIPES AND METHOD THEREFOR
A passive thermal system for use in aerospace vehicles includes a plurality of core-bearing radiator panels having at least one heat pipe embedded therein. The portion of the heat pipe embedded in each panel is fluidically coupled to the portions of the heat pipe in the other core-bearing radiator panels.
F28D 15/02 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p.ex. tubes caloporteurs
30.
ELEVATION ANGLE ESTIMATING SYSTEM AND METHOD FOR USER TERMINAL PLACEMENT
A system and a method for estimating the elevation angle of one or more objects surrounding a user terminal include a camera device for capturing an image of the sky and a display device for displaying the image of the sky captured by the camera device. One of the camera device and the display device generates an elevation limit marking in the image of the sky displayed by the display device. The elevation limit marking in the image of the sky defines an elevation angle above a horizon of the earth that all the one or more objects in a field of view of the camera device must remain below so that the user terminal has an unobstructed view of the sky in all azimuthal directions.
A system and a method for estimating the elevation angle of one or more objects surrounding a user terminal include a camera device for capturing an image of the sky and a display device for displaying the image of the sky captured by the camera device. One of the camera device and the display device generates an elevation limit marking in the image of the sky displayed by the display device. The elevation limit marking in the image of the sky defines an elevation angle above a horizon of the earth that all the one or more objects in a field of view of the camera device must remain below so that the user terminal has an unobstructed view of the sky in all azimuthal directions.
A passive thermal system for use in satellites includes a solid radiator panel with a plurality of longitudinal heat pipes attached to a surface thereof. In order to add strength to the radiator panel and resist bending, in addition to their heat transporting capability, the heat pipes have an extension from their top that increases a component of an area moment-of-inertia along an axis that is orthogonal to a plane of the radiator panel. Thus, the radiator panels can be thinner than otherwise would be possible, which results in weight and cost savings. .
B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
B64G 1/50 - Aménagements ou adaptations des dispositifs de contrôle de l'environnement ou des conditions de vie pour la commande de la température
F28D 15/02 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p.ex. tubes caloporteurs
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
33.
METHOD FOR THERMAL STABILIZATION OF A COMMUNICATIONS SATELLITE
A method for thermally stabilizing a communication satellite in orbit around the Earth relies on the discrete rotational symmetry of the pattern of antenna beams of the satellite. Exploiting the symmetry, the orientation of the satellite is changed from time to time by rotating the satellite through a symmetry angle of the rotational symmetry. Because of the symmetry, the beam pattern is unchanged after the rotation; but, because the rotation angle is less than 360°, a different side of the satellite is exposed to sunlight. The use of different thermal radiators and thermal shields on different sides of the satellite means that the thermal budget of the satellite is different after the rotation. By judiciously applying rotations as needed, as the orbit's orientation relative to the Sun evolves in time, it is possible to achieve effective control on the thermal budget of the satellite.
A passive thermal system for use in satellites includes a solid radiator panel with a plurality of heat pipes attached to a surface thereof. In addition to their heat transporting capability, the heat pipes strengthen the radiator panel to which they are coupled. In some embodiments, the heat pipes are structurally modified to increase their area moment of inertia.
F28D 15/02 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p.ex. tubes caloporteurs
A satellite frame includes a one-piece integrated body defining a plurality of sides for attaching satellite components thereto. Use of the single integrated satellite body minimizes the amount of fasteners and alignment equipment and processes. Use of the single piece frame also allows for the maximum possible specific stiffness by greatly reducing the number of connections and structural interfaces.
A device and method for estimating the elevation angle of one or more objects surrounding a user terminal include a convex image-reflecting surface, a transparent sighting surface disposed above the convex image-reflecting surface, and an elevation limit marking formed on or in the sighting surface. The elevation limit marking generates a reflected image in the convex image-reflecting surface that defines an elevation angle above a horizon of the earth that the one or more objects in a field of view of the convex image-reflecting surface must remain below so that the user terminal has an unobstructed view of the sky in all azimuthal directions.
A device and method for estimating the elevation angle of one or more objects surrounding a user terminal include a convex image-reflecting surface, a transparent sighting surface disposed above the convex image-reflecting surface, and an elevation limit marking formed on or in the sighting surface. The elevation limit marking generates a reflected image in the convex image-reflecting surface that defines an elevation angle above a horizon of the earth that the one or more objects in a field of view of the convex image-reflecting surface must remain below so that the user terminal has an unobstructed view of the sky in all azimuthal directions.
A method for thermally stabilizing a communication satellite in orbit around the Earth relies on the discrete rotational symmetry of the pattern of antenna beams of the satellite. Exploiting the symmetry, the orientation of the satellite is changed from time to time by rotating the satellite through a symmetry angle of the rotational symmetry. Because of the symmetry, the beam pattern is unchanged after the rotation; but, because the rotation angle is less than 360°, a different side of the satellite is exposed to sunlight. The use of different thermal radiators and thermal shields on different sides of the satellite means that the thermal budget of the satellite is different after the rotation. By judiciously applying rotations as needed, as the orbit's orientation relative to the Sun evolves in time, it is possible to achieve effective control on the thermal budget of the satellite.
A device and method for tracking satellites and handing off from one satellite to another includes a linear phased array antenna capable of generating and receiving a radio signal beam and electronically pointing the beam, a first motor for tilting the antenna to mechanically point a radio signal beam generated with the antenna, a second motor for spinning or rotating the antenna to mechanically point the beam, and a controller for controlling the electronic and the mechanical pointing of the beam. The directions of the electronic and mechanical pointing of the beam is performed by selecting a certain angular profile for the second motor from the start point to the end point of the path and calculating a path of a satellite to be tracked from a start point to an end point.
H01Q 3/08 - Dispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne utilisant un mouvement mécanique de l'ensemble d'antenne ou du système d'antenne pour faire varier deux coordonnées de l'orientation
H01Q 3/26 - Dispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne faisant varier la distribution de l’énergie à travers une ouverture rayonnante
40.
COMMUNICATION-SATELLITE SYSTEM THAT CAUSES REDUCED INTERFERENCE
A system of low-orbiting communication satellites that can share radio spectrum with geostationary satellites and methods mitigating interference to enable sharing are disclosed. In some embodiments, the satellite progressively tilts as it travels along its orbit, or its transmission beams are mechanically or electronically tilted. As a consequence of the tilting, as a satellite approaches the equatorial plane, its transmission beams are aimed more and more toward the equatorial plane, compared to when the satellite is far from the equatorial plane. Using this technique, an angular separation sufficient to prevent interference between the satellite's radio signals and GEO radio signals at all satellite positions is maintained, and, as a result good coverage is provided to all ground locations.
A system of low-orbiting communication satellites that can share radio spectrum with geostationary satellites and methods mitigating interference to enable sharing are disclosed. In some embodiments, the satellite progressively tilts as it travels along its orbit, or its transmission beams are mechanically or electronically tilted. As a consequence of the tilting, as a satellite approaches the equatorial plane, its transmission beams are aimed more and more toward the equatorial plane, compared to when the satellite is far from the equatorial plane. Using this technique, an angular separation sufficient to prevent interference between the satellite's radio signals and GEO radio signals at all satellite positions is maintained, and, as a result good coverage is provided to all ground locations.
