Abstract: In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

Abstract: A spacecraft propulsion system comprises an attitude adjustment thruster system with multiple thrusters (488a-d) receiving heated propellant via a shared thermal capacitance block (275). The thermal capacitance block (275) with integrated fluidic channels receives energy from a solar concentrator (320) and stores the heat.

Abstract: A spacecraft propulsion system comprises an attitude adjustment thruster system with multiple thrusters (488a-d) receiving heated propellant via a shared thermal capacitance block (275). The thermal capacitance block (275) receives energy from a solar concentrator (320) and stores the heat.

Abstract: A satellite receiver for wireless signals having carrier frequencies in the V or the W band of frequencies is described. The satellite receiver may receive the wireless signals at high elevation angles, such as greater than 62°. This high elevation angle may reduce losses, which may allow the satellite receiver to communicate at a data rate of at least 50 Mbps. In order to accommodate these system requirements, the one or more satellites that provide the wireless signals may have eccentric geosynchronous or near-geosynchronous orbits that are inclined relative to an equatorial plane of the Earth, such as an eccentricity between 0.12 and 0.3. Moreover, the one or more satellites may have ground tracks substantially along one or more continents, and may be in view of dense population regions in the one or more continents with a higher frequency than low-density population regions in the one or more continents.

Abstract: A satellite having a set of antenna elements with predefined directions and beam angles is described. This satellite may dynamically select at least a given antenna element based at least in part on utilization and/or availability of a terrestrial wireless communication network used by an electronic device that communicates with the satellite. Moreover, the satellite may change its attitude based at least in part on the given antenna element, where the changed attitude positions a region in a predefined beam angle of the given antenna element. The satellite may dynamically select the region to which it transmits wireless signals. For example, the region may be selected based at least in part on weather conditions associated with the region and/or priority of content conveyed by the wireless signals. Alternatively, the satellite may receive information specifying the region, the utilization and/or the availability of the terrestrial wireless communication network in the region.

Abstract: A satellite receiver with a switchable array of antenna elements for receiving wireless signals from at least a satellite is described. The antenna elements may be dynamically selected based at least in part on a location and motion of the satellite receiver, and a location and a motion of at least the satellite that provides wireless signals. Moreover, the antenna elements may also be dynamically selected based at least in part on utilization and/or availability of a terrestrial wireless communication network that communicates with the satellite receiver. The satellite receiver may predict availability of communication with at least the satellite. Furthermore, the array of antenna elements may provide improved power efficiency, pointing accuracy and/or isotropic gain relative to an array of antenna elements without switched antenna elements, such as for carrier frequencies in the V or the W band of frequencies.

Abstract: A satellite having a set of antenna elements with predefined directions and beam angles is described. This satellite may dynamically select at least a given antenna element based at least in part on utilization and/or availability of a terrestrial wireless communication network used by an electronic device that communicates with the satellite. Moreover, the satellite may change its attitude based at least in part on the given antenna element, where the changed attitude positions a region in a predefined beam angle of the given antenna element. The satellite may dynamically select the region to which it transmits wireless signals. For example, the region may be selected based at least in part on weather conditions associated with the region and/or priority of content conveyed by the wireless signals. Alternatively, the satellite may receive information specifying the region, the utilization and/or the availability of the terrestrial wireless communication network in the region.

Abstract: A satellite receiver for wireless signals having carrier frequencies in the V or the W band of frequencies is described. The satellite receiver may receive the wireless signals at high elevation angles, such as greater than 62° . This high elevation angle may reduce losses, which may allow the satellite receiver to communicate at a data rate of at least 50 Mbps. In order to accommodate these system requirements, the one or more satellites that provide the wireless signals may have eccentric geosynchronous or near-geosynchronous orbits that are inclined relative to an equatorial plane of the Earth, such as an eccentricity between 0.12 and 0.3. Moreover, the one or more satellites may have ground tracks substantially along one or more continents, and may be in view of dense population regions in the one or more continents with a higher frequency than low-density population regions in the one or more continents.

Abstract: In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

Abstract: To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

Abstract: A spacecraft structure for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

Abstract: To efficiently delivering payloads to respective orbits, a payload is received from a launch vehicle at a spacecraft operating as an orbital transfer vehicle. The payload is transferred, using the spacecraft, to a second orbit in accordance with a predefined fixed schedule that specifies at least the second orbit and a plurality of times at which the spacecraft transitions between the first and the at least second orbit.

Abstract: A system for delivery to space on a launch vehicle includes a first payload configured to directly couple to an adapter structure of the launch vehicle, a second payload configured to directly couple to the adapter structure of the launch vehicle, and a tether between the first payload and the second payload. Subsequently to separation from the launch vehicle, the first payload is configured to move relative to the second payload, using the tether, to dock with the second payload.

Abstract: A method in a spacecraft for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

Abstract: To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.