42 - Scientific, technological and industrial services, research and design
Goods & 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 40/02 - Communication route or path selection, e.g. power-based or shortest path routing
H04W 48/04 - Access restriction performed under specific conditions based on user or terminal location or mobility data, e.g. moving direction or speed
H04W 48/06 - Access restriction performed under specific conditions based on traffic conditions
H04W 48/18 - Selecting a network or a communication service
H04B 10/118 - Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
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 - Reselecting a network or an air interface
H04W 40/02 - Communication route or path selection, e.g. power-based or shortest path routing
H04W 48/04 - Access restriction performed under specific conditions based on user or terminal location or mobility data, e.g. moving direction or speed
H04W 48/06 - Access restriction performed under specific conditions based on traffic conditions
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.
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 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening using cams, levers, eccentrics, or toggles
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 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening using cams, levers, eccentrics, or toggles
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.
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 - Housings not intimately mechanically associated with radiating elements, e.g. radome
H01Q 19/13 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source being a single radiating element, e.g. a dipole, a slot, a waveguide termination
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 - Housings not intimately mechanically associated with radiating elements, e.g. radome
H01Q 19/13 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source being a single radiating element, e.g. a dipole, a slot, a waveguide termination
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.
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.
G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
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 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
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 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
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.
G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
H04W 84/10 - Small scale networksFlat hierarchical networks
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.
G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
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 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
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 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
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.
G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
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 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
H01Q 3/26 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elementsArrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the distribution of energy across a radiating aperture
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.
