Abstract: An imaging array fed reflector for a spacecraft is included in a spacecraft payload subsystem. The payload subsystem includes a multi-beam antenna including a reflector, a plurality of amplifiers, and a plurality of radiating feed elements, the feed elements configured as a phased array, illuminating the reflector, operable at a frequency having a characteristic wavelength (?), and configured to produce, in a far field at the reflector, a set of contiguous abutting beams. The amplifiers are disposed proximate to the plurality of radiating feed elements. Each radiating feed element has a respective coupling with at least one respective amplifier of the plurality of amplifiers. Each radiating feed element, together with the at least one respective amplifier, is disposed in a closely packed triangular lattice such that separation between adjacent radiating feed elements is not greater than 1.5?.

Abstract: An imaging array fed reflector for a spacecraft is included in a spacecraft payload subsystem. The payload subsystem includes a multi-beam antenna including a reflector, a plurality of amplifiers, and a plurality of radiating feed elements, the feed elements configured as a phased array, illuminating the reflector, operable at a frequency having a characteristic wavelength (?), and configured to produce, in a far field at the reflector, a set of contiguous abutting beams. The amplifiers are disposed proximate to the plurality of radiating feed elements. Each radiating feed element has a respective coupling with at least one respective amplifier of the plurality of amplifiers. Each radiating feed element, together with the at least one respective amplifier, is disposed in a closely packed triangular lattice such that separation between adjacent radiating feed elements is not greater than 1.5?.

Abstract: A high capacity satellite having a launch configuration in which one or more antenna reflectors may be stored forward of a forward surface of the spacecraft and an on-orbit configuration in which a reflector boom may be rotated to displace the one or more antenna reflectors a substantial distance from the main body in the yaw axis direction and in a direction orthogonal to the yaw axis direction.

Abstract: A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.

Abstract: A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.

Abstract: A spacecraft battery system arranges battery cells in two planes with a common mounting plate between them allowing for a more compact arrangement so the battery assembly can be removed from a limited mounting area resource of the spacecraft such as the north/south faces and placed remotely. Accordingly, a first battery assembly comprised of a plurality of battery cells in electrical continuity are mounted on and spread in a single plane over a first mounting surface of a planar mounting panel and a similarly constructed second battery assembly is mounted on and spread in a single plane over a second, opposed, mounting surface of that same planar mounting panel, the plane of the second battery assembly being spaced from the plane of the first battery assembly. The system includes a plurality of heat pipes embedded in the planar mounting panel and thermally connected with each of the battery cells for distributing heat uniformly across the planar mounting panel.

Abstract: A spacecraft comprises a first module including a first assembly of components and a second module including a second assembly of components and a thermal radiator. The second module is movable between a stowed position proximate the first module whereat the thermal radiator is only partially operative and a deployed position distant from the first module whereat the thermal radiator means is fully operative for dissipating waste heat to deep space for at least one of the first and second assemblies of components. In one embodiment, the first module includes a housing defining an interior cavity, the second module including a casing so shaped and dimensioned as to be telescopically received within the internal cavity of the first module and the second module being translationally movable along a deploying axis between the stowed position and the deployed position but incapable of mutual rotation about the deploying axis.

Abstract: In one embodiment, a thermal radiative system for an earth orbiting satellite including a plurality of faces intermittently exposed to maximum solar illumination comprises a thermal radiator is mounted on a face for discharging heat from a thermal load to deep space. A heat conductor extends between the thermal load and the thermal radiator. Thermal switches are operable for connecting the thermal load to the thermal radiator for cooling when the temperature of the thermal load is above a predetermined level and for disconnecting the thermal load from the thermal radiator when the temperature of the thermal load falls below the predetermined level. A shield including phase change management (PCM) material is thermally connected to the thermal load for drawing heat away therefrom.

Abstract: A three-axis stabilized spacecraft having roll, pitch, and yaw axes and when on station in orbit about the earth having a north face and a south face is equipped with a first and second thruster which may be electric thrusters. A first support device mounts the first thruster adjacent the north face and the first thruster is positioned a spaced distance away from the north face in a first direction parallel to the pitch axis and spaced from the pitch axis in a second direction normal to the pitch axis. A second support device mounts the second thruster adjacent the south face, the second thruster being positioned a spaced distance away from the south face in a third direction opposite the first direction and spaced from the pitch axis in the second direction. A gimbal mechanism pivotally mounts the first and second thrusters on the first and second support devices, respectively, for selectively positioning the attitude of the first and second thrusters.

Abstract: A battery system for an body stabilized satellite traveling in a geosynchronous orbit comprises east and second battery modules and similarly facing radiators for discharging beat to deep space. Heat conduction arteries connect each battery module to its associated radiator. An east thermal switch is operable for thermally connecting the first battery module to and from the east facing radiator. Similarly, a west thermal switch is operable for thermally connecting the second battery module to and from the west facing radiator. A computer selectively operates the east and west thermal switches such that, in one instance, for a time between the satellite's emergence from the earth's shadow and its position nearest the sun, the respective thermal switches thermally connect the first battery module to its radiator while thermally disconnecting the second battery module from its radiator.