Abstract: A heat switch includes a heat sink, a coolant tube, and an actuator. The coolant tube is movable with respect to the heat sink. The actuator couples between the heat sink and the coolant tube and configured to move the coolant tube between a first position and a second position. Heat flow from the coolant tube into the heat sink is greater in the second position than in the first position for enhanced heat transfer from the coolant tube.

Abstract: A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.

Abstract: Described herein is a space based subsystem of a satellite, and methods for use therewith, for receiving an RF uplink feeder beam and in dependence thereon producing one or more optical ISL beams for transmission to one or more other satellites. The subsystem can include an antenna to receive an RF feeder uplink beam and produce an RF signal therefrom. The subsystem can also include, inter alia, RF components, local oscillator(s), lasers, EOMs, a WDM multiplexer, an optical amplifier and transmitter optics. Such components can be used to convert the RF signal to one or more ISL beams for transmission to one or more other satellites. Where RF frequencies of optical data signals output by the EOMs are within the same RF frequency range within which the other satellite(s) transmit RF service downlink beams, there is an elimination of any need for the other satellite(s) to perform frequency conversions.

Abstract: Described herein is a space based subsystem of a satellite, and methods for use therewith, for producing and transmitting an optical ISL beam to another satellite. The subsystem can include, inter alia, receiver optics, optical amplifiers, a WDM demultiplexer, beam splitters, a WDM multiplexer, and transmitter optics. The transmitter optics may be configured to receive an amplified wavelength division multiplexed optical signal and, in dependence thereon, transmit an optical ISL beam to another satellite. In certain embodiments, because RF frequencies of a wavelength division multiplexed optical signal produced by the WDM multiplexer are within a same specified RF frequency range within which the other satellite is configured to transmit RF service downlink beams, there is an elimination of any need for the other satellite to perform any frequency conversions when producing the RF service downlink beams in dependence on the optical ISL beam.

Abstract: Described herein is a space based subsystem of a satellite, and methods for use therewith, for receiving an optical ISL beam from another satellite, and in dependence therein, producing a further optical ISL beam for transmission to a further satellite. Additionally, the subsystem can also produce RF service downlink beams for transmission to service terminals. The subsystem can include, inter alia, receiver optics, optical amplifiers, a WDM demultiplexer, beam splitters, a WDM multiplexer, and transmitter optics. In certain embodiments, because RF frequencies of a wavelength division multiplexed optical signal produced by the WDM multiplexer are within a same specified RF frequency range within which the satellite and the further satellite are configured to transmit RF service downlink beams, there is an elimination of any need for the satellite and further satellite to perform any frequency conversions when producing the RF service downlink beams in dependence on the optical ISL beams.

Abstract: A non-geostationary satellite is configured to provide a plurality of spot beams that implement a first frequency plan at Earth's Equator and a second frequency plan away from Earth's Equator. The second frequency plan is different than the first frequency plan. In one embodiment, the non-geostationary satellite is part of a constellation of non-geostationary satellites, with each of the satellites providing spot beams that implement a first frequency plan at Earth's Equator and implement a second frequency plan away from Earth's Equator as the satellites travel in orbit around Earth.

Abstract: An antenna system having a main reflector and at least two subreflectors is configured to provide at least two independently steerable beams. Each subreflector is configured to illuminate the main reflector, and each subreflector is configured to be illuminated by a respective dedicated feed element or dedicated feed array. At least one of the subreflectors is configured to steer a first beam, without affecting the shape or orientation of any other beam. One or more of the beams may also be independently shaped, by a contoured surface of one or more subreflectors and/or the main reflector.

Abstract: A counter is started on the falling edge of a tach pulse. This counter counts to the rising edge of a second tach pulse, such as the next tach pulse. During the duration of the tach pulse the FPGA calculates the RPM of a motor. In this way, during each commutation period, a RPM is calculated. The present system performs a RPM calculation during each commutation period and/or tach pulse duration.

Abstract: A wireless communication system includes frequency reuse between terminals in common coverage regions using a multiple satellite architecture with spatial diversity. Different terminals may be associated with different ones of the satellites such that a common frequency can be reused by the different terminals. A gateway may communicate with a first satellite using a feeder beam having an overlapping geographic coverage region with a user beam used for communication between a set of user terminals and a second satellite. Spatial diversity is provided between the satellites, and the feeder beam and the user beam operate at common frequencies within the overlapping coverage region. In this manner, the bandwidth of both satellites at the common coverage region is used to increase the available capacity.

Abstract: A wireless communication platform utilizes flexible bandwidth assignment to re-allocate bandwidth between spot beams. The platform may assign a first combination of frequency and polarization (FP) to a first spot beam and a second combination of frequency and polarization to a second spot beam that is adjacent and at least partially overlapping the first spot beam. The platform may assign to the first spot beam a reserved combination of frequency and polarization during a first time period, and at second time, assign the reserved combination to the second spot beam. The platform may also assign the reserved combination simultaneously to adjacent spot beams by managing user of the reserved combination by geographically isolated terminals in the spot beams. The platform may further assign different portions of the reserved combination to adjacent spot beams without geographical limitations.

Abstract: A communication platform such as a spacecraft, airborne platform, or terrestrial line of site wireless platform is provided with adaptive digital beamforming. The satellite digitizes a full spectrum allocation for digital channelization. A channelization engine can determine a particular user or user group associated with an uplink signal. In this manner, the communication platform can apply different processing based on the user or group associated with a signal. For example, the communication platform receives uplink signals associated with a first user group and a second user group in one embodiment. The platform dynamically generates one or more spot beams for the first user group and the second group. The platform discriminates the uplink signals to apply frequency hopping for the downlink frequency channel assignments to the second user group while the downlink frequency channel assignments for the first user group remain fixed.

Abstract: A thermal control arrangement includes a first heat pipe and a plurality of thermoelectric coolers. The plurality of thermoelectric coolers is disposed between the first heat pipe and a thermal load, each of the plurality of thermoelectric coolers having a first surface and a second surface, each respective first surface having a first thermally conductive coupling to the first heat pipe and each respective second surface having a second thermally conductive coupling to the thermal load.

Abstract: A release device having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. A tensioned tape is overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. The overlapping winding allows for a low profile housing for the-release device. The multiple segments require less radial motion for release of the tensioned member.

Abstract: A radio frequency (RF) dielectric resonator filter includes at least a first cavity and a second cavity, each cavity being loaded with a dielectric resonator. The first cavity is separated from the second cavity by a common wall, the common wall including a first and second aperture that couple an electromagnetic field between the first cavity and the second cavity. A first externally adjustable tuning screw extends from the second aperture, a portion of the tuning screw being external to the filter. The first aperture is an iris disposed in a central portion of the wall and the second aperture is disposed proximate to a perimeter of the wall. The second aperture has an effective area that is adjustable by the first externally adjustable tuning screw.

Abstract: An antenna reflector includes a laminated structure including a first layer and a second layer, where the first layer has an electrically conductive and electrically reflective front surface and includes a nonwoven metallized fiber matte and the second layer includes an open weave fabric. The laminated structure is acoustically permeable. In some implementations, a laminated structure is formed by co-curing the first layer and the second layer.

Abstract: Single or multi-axis positioning mechanisms are provided that include a caging mechanism that may be actuated without requiring axial displacement of rotational components of the positioning mechanisms. In some multi-axis positioning mechanism implementations, each rotational axis may have an associated caging mechanism that is transitioned between a caged and uncaged state using a common release device. In some implementations, the release device may be a single-use device. In other implementations, the release device may be capable of re-caging the positioning mechanism after uncaging the positioning mechanism.

Abstract: A large area, deployable flexible blanket photovoltaic solar array architecture for high power applications is disclosed. The structure is a modularized and scalable solar array system that provides high power level scalability. The structure is comprised of repeating, similar modular deployable roll-out solar array wings mounted in an opposing manner and along the length of a rigid, strong and efficiently packaged deployable backbone structure. The deployable roll-out solar array building block modular “winglet” elements can be comprised of either a rolled or z-folded flexible photovoltaic blanket configuration, and their structural deployment is motivated by the elastic strain energy of longitudinal roll-out booms. The backbone structure is comprised of a stiff deployable beam structure articulated that is deployed perpendicular with respect to the spacecraft sidewall and latched out.

Abstract: Techniques for performing orbit raising, north-south stationkeeping, east-west stationkeeping, and momentum management with thrusters disposed on a spacecraft are disclosed. The spacecraft includes at least one thruster support mechanism (TSM), including a pointing arrangement and an elongated structural member, the structural member having a long dimension defining a first axis a proximal portion of the structural member is attached to the pointing arrangement each of the thrusters is fixedly coupled with a distal portion of the structural member. The pointing arrangement includes a first, second, and third revolute joint, the first revolute joint being rotatable about the first axis; the third revolute joint being rotatable about a third axis, the third axis being fixed with respect to the spacecraft; and the second revolute joint being rotatable about a second axis, the second axis being orthogonal to each of the first axis and the third axis.

Abstract: A pliable multilayer blanket configured as a particle radiation shield, the blanket including multiple layers. A first layer of the multiple layers is composed of a first material and a second layer of the multiple layers is composed of a second material, different from the first material, each layer being less than 20 mils thick. At least one of the first material and the second material is a metal or metal alloy having an atomic number (Z) of at least 29.

Abstract: This disclosure provides systems, methods and apparatus for multi-channel satellite calibration. In one aspect, a calibration system can provide a transmit calibration signal based on a reference calibration signal to a satellite. The satellite can transmit back a receive calibration signal that can be obtained by the calibration system. Sub-carriers of the receive calibration signal can be compared with sub-carriers of the reference signal to determine adjustments to transmission properties of antennas of the satellite.