Space Systems Loral LLC

Dulles Town Center, VA, United States

Space Systems Loral LLC

Dulles Town Center, VA, United States

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Patent
Space Systems Loral Llc | Date: 2015-10-05

A satellite comprises an antenna system configured to provide a plurality of spot beams including one or more small spot beams illuminating a first region of a coverage area, one or more large spot beams illuminating a second region of the coverage area separate from the first region and one or more intermediate sized spot beams illuminating a transition region of the coverage area that is located between the first region and the second region so that the one or more small spot beams are separated from the one or more large spot beams by the one or more intermediate sized spot beams. The one or more intermediate sized spot beams serve to mitigate C/I for the one or more spot beams.


Patent
Space Systems Loral LLC | Date: 2017-02-28

A spacecraft includes a payload subsystem including a digital channelizer. The digital channelizer provides at least a portion of spacecraft command or telemetry functionality. The spacecraft may optionally also include a telemetry and command (T&C) subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter. The digital channelizer may be communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.


Patent
Space Systems Loral LLC | Date: 2017-02-22

A spacecraft includes a payload subsystem, the payload subsystem including a phased array of feed elements configured to illuminate an antenna reflector, a beam forming network (BFN) disposed proximate to the array of feed elements, and a plurality of power amplifiers disposed between the BFN and the array of feed elements. The BFN includes a plurality of variable amplitude and phase adjusting arrangements disposed between (i) m:1 power combiners that are communicatively coupled with the power amplifiers and (ii) at least one 1:n power splitter, where m is greater than 1, and n is greater than 2


A payload subsystem of a satellite includes a plurality of transmit antenna feeds, a plurality of frequency filters, and a power amplification arrangement including a plurality of power amplifiers. The power amplification arrangement has at least one multiport amplifier, the multiport amplifier including a plurality of output ports, each output port coupled with a respective one of the plurality of transmit antenna feeds by way of a respective one of the plurality of frequency filters.


Patent
Space Systems Loral LLC | Date: 2015-06-03

A power combining arrangement includes an input divider waveguide and an output combiner waveguide, and a first and second amplifier. The power combining arrangement is configured to amplify RF energy having a characteristic wavelength . The first amplifier has a first input electrically coupled with a first output port of the divider waveguide. The second amplifier has a second input electrically coupled with a second output port of the divider waveguide. The first and second output ports are separated by a first distance corresponding to a phase delay _(1), the first distance being selected substantially independently of the characteristic wavelength. The first amplifier has a first output electrically coupled with a first input port of the combiner waveguide and the second amplifier has a second output electrically coupled with a second input port of the combiner waveguide. The first and second input ports are separated by the first distance.


Interference information is obtained from one or more interference information sources (502, 504, 506, 508, 510, 512, 514) external to a particular communication system (100, 500), wherein the interference information is indicative of non-weather related interference that can adversely affect efficacy of the particular communication system (100, 500). Configurable link parameters of the particular communication system (100, 500) are dynamically adapted and/or resources of the particular communication system (100, 500) are dynamically allocated based on the interference information obtained from the interference information source(s) (502, 504, 506, 508, 510, 512, 514) that is/are external to the particular communication system (100, 500). Such embodiments can advantageously be performed proactively to prevent or mitigate adverse effects of non-weather related interference on the efficacy of the particular communication system (100, 500).


Patent
Space Systems Loral LLC | Date: 2016-02-25

Design of a 3-D truss structure, including a plurality of coupling nodes and a plurality of struts, is optimized by performing a quantitative optimization of an objective function corresponding to a figure of merit of the design. The quantitative optimization includes: generating a finite element analysis model, the analysis model a 3-D lattice mesh of strut-like finite elements; computing, with the finite element analysis model, a value for the objective function; and optimizing the objective function by executing at least two cycles of an optimization loop. The optimization loop includes a) computing a respective parameter of each strut-like finite element; b) deleting, from the finite element analysis model, selected finite elements for which a resulting mechanical property is less than a threshold; (c) computing an updated value for the objective function; and repeating the optimization loop until the objective function is within a desired tolerance of the specified value.


Patent
Space Systems Loral LLC | Date: 2016-02-25

A spacecraft includes a 3-D closed truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each coupling node including at least two legs, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes. Each coupling node is attached, at respective ones of the plurality of joints, with at least two strut elements. Each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.


Present location information about a present location of a mobile terminal is obtained, as is destination information about a target destination for the mobile terminal, wherein the target destination can be a waypoint destination or a final destination for the mobile terminal. Also obtained is wireless communication coverage information about wireless communication coverage associated with one or more geographic regions between the present location of the mobile terminal and the target destination for the mobile terminal. In dependence on the wireless communication coverage information, a navigational route is determined for the mobile terminal that mitigates a probability that the mobile terminal will lose a specific type of communication capability while travelling between the present location of the mobile terminal and the target destination for the mobile terminal.


Patent
Space Systems Loral LLC | Date: 2016-04-13

A first satellite and a second satellite are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. The launch vehicle includes a primary payload adapter and the first satellite includes a secondary payload adapter. In the launch configuration, the first satellite is mechanically coupled with the primary payload adapter and the second satellite is mechanically coupled with the secondary payload adapter. Following injection into a first orbit by the launch vehicle, the first satellite separates from the primary payload adapter while the second satellite is mechanically coupled with the secondary payload adapter. The second satellite is detached from the secondary payload adapter of the first satellite only after an orbit transfer maneuver executed by a propulsions system of the first satellite. In the launch configuration, the mass of the second satellite is at least 30% of the mass of the first satellite.

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