Abstract: A modularized feed array arrangement includes a plurality of radio frequency (RF) radiating elements, a plurality of waveguides positioned inboard of the plurality of RF radiating elements, each RF radiating element being electrically coupled with an outboard portion of one or more of the waveguides; and a plurality of modules, each module including a plurality of RF switches, a plurality of amplifiers, and a manifold panel that includes a plurality of RF choke joints. An inboard portion of each RF switch is electrically coupled with a respective amplifier. Each RF choke joint includes a proximal portion electrically coupled with an outboard portion of a respective one of the RF switches and a distal portion electrically coupled with an inboard portion of a respective one of the waveguides.

Abstract: A photonic switch device accepts a data modulated RF signal and outputs the data modulated RF signal or a frequency converted version thereof at one or more outputs of the switch device. Tunable laser(s) is/are controlled to cause peak wavelength(s) of the optical signal(s) emitted therefrom. An EOM receives the accepted data modulated RF signal and optical signal(s) produced using the tunable laser(s), and the EOM outputs an optical data signal modulated to include the data modulated RF signal. A WDM receives the optical data signal output by the EOM and the optical data signal received by the WDM demultiplexer is output at one or more outputs thereof based on peak wavelength(s) of the optical data signal. Photodetectors optically coupled to respective outputs of the WDM demultiplexer convert optical signals back to electrical signals. Related methods and system are also described herein.

Abstract: A spacecraft, configured to be operated in a geosynchronous orbit includes a power subsystem, including a battery, and a battery charge controller. The spacecraft is configured to have a power demand, during an eclipse season of the geosynchronous orbit, of ‘P’ kilowatts and the battery is sized to have a nominal capacity, measured in kilowatt-hours, smaller than 1.2*P/0.85. In some implementations, the battery has a rated charge voltage corresponding to the nominal capacity and the battery charge controller is configured to execute a battery charge management strategy that charges the battery to an above-rated charge voltage during selected portions of the eclipse season.

Abstract: Techniques are disclosed for providing a redundant telemetry transmission path on a spacecraft. The spacecraft includes a telemetry (TLM) transmitter having a modulation input coupled by a commandable switch with a signal source. The TLM transmitter is configured to receive an output from the signal source when the commandable switch is closed. The computer is configured to encode TLM data bits onto a TLM downlink signal by actuating the commandable switch, such that a signal from the signal source received by the TLM transmitter is temporally varied between an on condition and an off condition.

Abstract: 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.

Abstract: Cloud mask image data is obtained by a secondary imaging payload disposed on a communications or broadcast satellite operating in geosynchronous orbit. The obtained cloud mask image data is provisioned for use, in near real time, by one or more low earth orbit imaging satellite systems. Provisioning the obtained cloud mask image data may include collecting the data on the ground and making it available to one or more operators of the one or more LEO imaging satellite systems and/or transmitting the data from the communications or broadcast satellite to at least one spacecraft in the one or more LEO imaging satellite systems.

Abstract: A constellation of non-geosynchronous satellites are in a common orbit. Each time one of the satellites is at a trigger location, a new rolling wave of handovers is started that includes performing handovers of a group of dependent spot beams between adjacent satellites in sequence for pairs of adjacent satellites in a single direction around the orbit.

Abstract: A launch vehicle includes an upper stage and an integral fairing. In a launch configuration, the integral fairing is configured to enclose, between an aft portion and a forward portion, one or more payloads. The integral fairing includes a mechanical attachment with the upper stage proximal to the aft portion, and a nose cap proximal to the forward portion and a passive venting arrangement that equalizes pressures internal and external to the integral fairing. The integral fairing is configured to permit deployment of at least one payload, while avoiding: (i) separation of the integral fairing into two or more parts, (ii) separation of the integral fairing from the upper stage, and (iii) articulation of the mechanical attachment. The upper stage may provide single stage to orbit capability.

Abstract: A communication platform (e.g., a flexible satellite) includes electrical to optical converters configured to convert input electrical signals to input optical signals, an optical switching network connected to the electrical to optical converters that choose which input optical signals to route to which output beams, tunable optical filters (connected to the switching network) that are configured to select programmable sub-bands of the input optical signals to create output optical signals, and optical to electrical converters (connected to the tunable optical filters) that are configured to convert the output optical signals to output electrical signals for the output beams.

Abstract: Described herein is a ground based subsystem for inclusion in an optical gateway and for use in transmitting an optical feeder uplink beam to a satellite. The subsystem can include a wavelength-division multiplexing (WDM) multiplexer configured to receive optical data signals from optical network(s) external to the ground based optical gateway, and configured to combine the optical data signals into a wavelength division multiplexed optical signal. The subsystem can also include an optical amplifier to amplify the wavelength division multiplexed optical signal, and transmitter optics to receive the amplified wavelength division multiplexed optical signal and transmit an optical feeder uplink beam to the satellite in dependence thereon. In certain embodiments, the ground based optical gateway does not perform any modulation or demodulation of the optical data signals received from the optical network(s) external to the ground based optical gateway before they are provided to the WDM multiplexer.

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: Techniques for deorbiting a satellite include executing an orbit transfer maneuver that transfers the satellite from an operational orbit to an interim orbit. The operational orbit is substantially geosynchronous and has (i) an inclination of greater than 70 degrees; (ii) a nominal eccentricity in the range of 0.25 to 0.5; (iii) an argument of perigee of approximately 90 or approximately 270 degrees; (iv) a right ascension of ascending node of approximately 0; and (v) an operational orbit apogee altitude. The interim orbit has an initial second apogee altitude that is at least 4500 km higher than the first apogee altitude, and the interim orbit naturally decays, subsequent to the orbit transfer maneuver, such that the satellite will reenter Earth's atmosphere no longer than 25 years after completion of the orbit transfer maneuver.

Abstract: A satellite network comprises networks nodes including multiple satellites, multiple gateways, additional servers and a mobile vehicle (e.g., an aircraft). All of (or a subset) of the network nodes include switches. The network implements a software defined network that includes a mobility manager as part of the management plane, a network controller as part of the control plane, and the switches on the network nodes as the data plane. In one embodiment, the switches communicate using an Open Flow communications protocol and make routing decisions based on flow tables. The mobility manager communicates with, and manages, the switches via the network controller. The mobility manager proactively generate updates to flow tables based on satellite ephemeris data for the multiple satellites and itinerary data for the aircraft, and pushes the updates to the switches in response to determining that the aircraft needs to be handed off between satellites.

Abstract: Described herein is a satellite communications system that includes: two or more satellites using laser communications, and a communications relay aircraft adapted for flying at altitudes above clouds. The communications relay aircraft includes: a laser communications module to communicate with the satellite using laser communication and a Radio Frequency (RF) communications module to communicate with RF equipment at or near ground level using cloud-penetrating RF communications. The RF communications module is configured to take data received as laser communication and generate a corresponding RF transmission containing the data. The laser communications module is configured to take data received as RF communication and to generate a corresponding laser transmission containing the data.

Abstract: A spacecraft includes a first deployable module and a second deployable module and is reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable module is adjacent to the second deployable module. The first deployable module includes a first solar array, the first solar array being rotatable, in the on-orbit configuration, about a first axis of rotation, and the second deployable module includes a second solar array, the second solar array being rotatable, in the on-orbit configuration, about a second axis of rotation, the second axis of rotation being separated by a substantial distance from the second axis of rotation.

Abstract: A power splitting (or combining) arrangement includes a waveguide having a plurality of output (or input) ports and an input (or output) port configured to receive (or transmit) electromagnetic waves having a frequency in a designated frequency band. Each output (or input) port is configured to electrically couple with an input (or output) terminal of a corresponding one of a plurality of active devices. Each output (or input) port has a respective output impedance associated with the frequency band. The power splitting (or combining) arrangement is configured such that the respective output (or input) impedance of each output (or input) port substantially matches an input (or output) impedance of the corresponding one of the plurality of active devices.

Abstract: A satellite network comprises networks nodes including multiple satellites, multiple gateways, additional servers and a mobile vehicle (e.g., an aircraft). All of (or a subset) of the network nodes include switches. The network implements a software defined network that includes a mobility manager as part of the management plane, a network controller as part of the control plane, and the switches on the network nodes as the data plane. In one embodiment, the switches communicate using an Open Flow communications protocol and make routing decisions based on flow tables. The mobility manager communicates with, and manages, the switches via the network controller. The mobility manager proactively generate updates to flow tables based on satellite ephemeris data for the multiple satellites and itinerary data for the aircraft, and pushes the updates to the switches in response to determining that the aircraft needs to be handed off between satellites.

Abstract: Described herein are ground based subsystems, and related methods, for use in transmitting an optical feeder uplink beam to a satellite that includes a multiple element antenna feed array and that is configured to accept the optical feeder uplink beam and in dependence thereon use the multiple element antenna feed array to produce and transmit a plurality of radio frequency (RF) service downlink beams to service terminals. Certain embodiments are related to a ground based beamformer (GBBF) for inclusion in a ground based subsystem, and methods for use therewith. Beneficially, embodiments described herein allow for flexible antenna beam forming for large signal bandwidth without the limitation associated with the available gateway uplink and downlink spectrum at RF frequencies. Also described herein are space based subsystems for use with such ground based subsystems.

Abstract: A satellite communication system comprises a satellite configured to provide a plurality of spot beams adapted for communication using time domain beam hopping to switch throughput among spot beams of the plurality of spot beams. The plurality of spot beams includes a first spot beam that illuminates and communicates with a first gateway and a first set of subscriber terminals. The satellite is configured to implement a beam hopping plan that during a hopping period provides throughput to the first spot beam for an aggregated time duration based on bandwidth assignments to the first gateway and the first set of subscriber terminals.

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.