Abstract: A method and apparatus for deploying a fixed and canted solar array of a satellite. The solar array is rotated in a first plane and about a first axis from a stowed position to a first position, rotated about a second axis orthogonal to the first axis from the first position to a deployed position determined by a deployment orbit of the satellite, and locked in the deployed position to prevent further motion of the solar array relative to a satellite body for the operational life of the satellite.

Abstract: The invention discloses differing embodiments of thermal control coatings, spacecraft components having coatings, and methods for controlling the temperature of a component. In one embodiment, a thermal control coating under the invention may include one or more thermochromic multi-layer coatings and one or more solar rejection multi-layer coatings. The thermal control coating may have one or more transition temperatures at which the solar absorptance of the solar rejection coating substantially stays the same, while a thermal emittance of the thermochromic coating substantially changes.

Abstract: Systems and methods are disclosed herein providing an improved approach to phased array antenna communications. In one example, an antenna system includes a digital beamformer adapted to receive a plurality of input signals and selectively replicate and weight the input signals to provide a plurality of digital subarray signals. Digital to analog (D/A) converters convert the digital subarray signals to a plurality of composite analog subarray signals. Modules of a subarray are adapted to perform analog beamsteering on at least one of the composite analog subarray signals. In another example, a subarray of a phased array antenna may include a thermal cold plate, a plurality of feed/filter assemblies, a distribution board stacked on the thermal cold plate, and a plurality of modules adapted to perform analog beamsteering. The modules may be interconnected with each other through the distribution board and removably inserted into the distribution board.

Abstract: Systems and methods are disclosed herein providing an improved approach to phased array antenna communications. In one example, an antenna system includes a digital beamformer adapted to receive a plurality of input signals and selectively replicate and weight the input signals to provide a plurality of digital subarray signals. Digital to analog (D/A) converters convert the digital subarray signals to a plurality of composite analog subarray signals. Modules of a subarray are adapted to perform analog beamsteering on at least one of the composite analog subarray signals. In another example, a subarray of a phased array antenna may include a thermal cold plate, a plurality of feed/filter assemblies, a distribution board stacked on the thermal cold plate, and a plurality of modules adapted to perform analog beamsteering. The modules may be interconnected with each other through the distribution board and removably inserted into the distribution board.

Abstract: Systems and methods are disclosed herein providing an improved approach to phased array antenna communications. In one example, an antenna system includes a digital beamformer adapted to receive a plurality of input signals and selectively replicate and weight the input signals to provide a plurality of digital subarray signals. Digital to analog (D/A) converters convert the digital subarray signals to a plurality of composite analog subarray signals. Modules of a subarray are adapted to perform analog beamsteering on at least one of the composite analog subarray signals. In another example, a subarray of a phased array antenna may include a thermal cold plate, a plurality of feed/filter assemblies, a distribution board stacked on the thermal cold plate, and a plurality of modules adapted to perform analog beamsteering. The modules may be interconnected with each other through the distribution board and removably inserted into the distribution board.

Abstract: A method and apparatus for deploying a fixed and canted solar array of a satellite. The solar array is rotated in a first plane and about a first axis from a stowed position to a first position, rotated about a second axis orthogonal to the first axis from the first position to a deployed position determined by a deployment orbit of the satellite, and locked in the deployed position to prevent further motion of the solar array relative to a satellite body for the operational life of the satellite.

Abstract: The invention discloses differing embodiments of thermal control coatings, spacecraft components having coatings, and methods for controlling the temperature of a component. In one embodiment, a thermal control coating under the invention may include one or more thermochromic multi-layer coatings and one or more solar rejection multi-layer coatings. The thermal control coating may have one or more transition temperatures at which the solar absorptance of the solar rejection coating substantially stays the same, while a thermal emittance of the thermochromic coating substantially changes.

Abstract: A spacecraft (10) having a main body portion (12) comprising a payload module (14), a bus module (16) and an antenna potion (17), a first solar wing (24) having a first side (30) and a second side (32), a second solar wing (26) having a first side (36) and a second side (38), a first battery pack (50) secured to the first solar wing and a second battery pack (52) secured to the second solar wing.