Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a dual-launch adaptor, a first spacecraft, and a second spacecraft. The first spacecraft and the second spacecraft may be mounted on the dual-launch adaptor and may be arranged side by side on the dual-launch adaptor. An aspect ratio of each of the first and second spacecraft may be within a range of 0.55 and 0.8.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a first and second spacecraft mounted within a fairing. The first and second spacecraft may be mounted side by side on the dual-launch adaptor. A ratio of a first lateral dimension of the GEO spacecraft to a second lateral dimension of the GEO spacecraft may be within a range from 0.55 to 0.8, with the first lateral dimension and the second lateral dimension being perpendicular to each other and smaller than a height of the GEO spacecraft.

Abstract: An instrument mounting system for a geosynchronous host satellite provides independent heat rejection capability for a hosted instrument. The system may include an instrument mounting structure that is thermally coupled to a radiator component via heat pipes that may include one or both of rigid and flexible elements. In some embodiments, the system is mounted on the hosting satellite so as to provide satellite components and the hosted instrument with a clear field of view while rejecting heat in one or both of the north and south directions. The system may also provide structural support for components of one or both of the hosted instrument or the hosting satellite.

Abstract: A heat transfer assembly can include an equipment panel having an east end and a west end. East and west radiator panels are coupled to the east and west ends, respectively, of the equipment panel. The assembly also includes a plurality of flexible heat pipes each having a first rigid tube thermally coupled to the east radiator panel, a second rigid tube coupled to the equipment panel, a third rigid tube thermally coupled to the west radiator panel, a first flexible tube sealingly coupled between the first and second rigid tubes, and a second flexible tube sealingly coupled between the second and third rigid tubes. The equipment panel is configured to retain one or more equipment modules in thermal contact with the second rigid tube of at least one of the plurality of flexible heat pipes.

Abstract: A geostationary earth orbit (GEO) spacecraft is disclosed that includes a body with north, east, south, and west sides and a north-south axis. The spacecraft has at least one deployable radiator rotatably coupled to the body. The deployable radiator has a stowed position proximate to one of the east and west sides and a deployed position that is greater than 90 degrees from the north-south axis in a direction away from the respective one of the east and west sides.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a dual-launch adaptor, a first spacecraft, and a second spacecraft. The first spacecraft and the second spacecraft may be mounted on the dual-launch adaptor and may be arranged side by side on the dual-launch adaptor. An aspect ratio of each of the first and second spacecraft may be within a range of 0.55 and 0.8.

Abstract: A deployable radiator arrangement for cooling a geostationary earth orbit spacecraft is provided. In some aspects, the geostationary earth orbit spacecraft may comprise first and second deployable radiators mounted on an east or west surface of the spacecraft when stowed. The first and second deployable radiators are configured to rotate into a north and south facing position, respectively, when deployed. The geostationary earth orbit spacecraft may further comprise first and second fixed radiators disposed on a north and south surface of the spacecraft, respectively. The first and second deployable radiators are thermally coupled to the first and second fixed radiators, respectively.

Abstract: A deployable radiator arrangement for cooling a geostationary earth orbit spacecraft is provided. In some aspects, the geostationary earth orbit spacecraft may comprise first and second deployable radiators mounted on an east or west surface of the spacecraft when stowed. The first and second deployable radiators are configured to rotate into a north and south facing position, respectively, when deployed. The geostationary earth orbit spacecraft may further comprise first and second fixed radiators disposed on a north and south surface of the spacecraft, respectively. The first and second deployable radiators are thermally coupled to the first and second fixed radiators, respectively.

Abstract: A satellite (50) is disclosed having at least one deployable thermal radiator (64). Once deployed, this thermal radiator (64) may be repositioned. In one embodiment, the deployed thermal radiator (64) may be moved about a first axis (74), about a second axis (76), or both to move the deployed thermal radiator (64) from one deployed position to another deployed position.

Abstract: A satellite thermal management system for dissipating excess heat generated within a satellite. The thermal management system includes a central platform for mounting heat dissipating components. A first thermal radiator panel and a second thermal radiator panel are mounted to the central platform. The first thermal radiator panel is arranged to face East when the satellite is in orbit. The second thermal radiator panel is arranged to face West when the satellite is in orbit. The first and second thermal radiator panels are thermally coupled to the central platform and are configured to radiate heat dissipated by the heat dissipating component mounted on the central platform.

Abstract: A spacecraft is provided that includes a spacecraft body, a phased array coupled to a side of the spacecraft body by a first deployment couple, and a reflector coupled to the side of the spacecraft body by a second deployment couple. The first and second deployment couples are configured to permit stowing the reflector and the phased array parallel to the side of the spacecraft body. The reflector and the phased array share a common launch restraint mounting point on the side of the spacecraft body. A spacecraft is also provided that includes a spacecraft body, a mounting platform coupled to a side of the spacecraft body by a deployment couple, and a plurality of phased array assemblies. Each phased array assembly has a face with elements, and is coupled to the mounting platform by a gimbal. The deployment couple and the gimbals are configured to permit stowing the phased array assemblies parallel to the side of the spacecraft body and with the face of each phased array assembly oriented in a first direction.

Abstract: A satellite payload structure includes one side that includes at least two equipment mounting panels. Each of the equipment mounting panels are oriented substantially parallel to each other such that when the satellite is deployed, each of the equipment mounting panels are substantially parallel to a vector pointing from the deployed location of the satellite to a point on the earth's surface. The point on the earth's surface is located vertically beneath the satellite such that the vector is substantially normal to the earth's surface.

Abstract: A spacecraft is provided that includes a spacecraft body, a phased array coupled to a side of the spacecraft body by a first deployment couple, and a reflector coupled to the side of the spacecraft body by a second deployment couple. The first and second deployment couples are configured to permit stowing the reflector and the phased array parallel to the side of the spacecraft body. The reflector and the phased array share a common launch restraint mounting point on the side of the spacecraft body. A spacecraft is also provided that includes a spacecraft body, a mounting platform coupled to a side of the spacecraft body by a deployment couple, and a plurality of phased array assemblies. Each phased array assembly has a face with elements, and is coupled to the mounting platform by a gimbal. The deployment couple and the gimbals are configured to permit stowing the phased array assemblies parallel to the side of the spacecraft body and with the face of each phased array assembly oriented in a first direction.

Abstract: An antenna stowage and deployment system, including a spacecraft and at least one pair of adjacent nesting antenna assemblies. Each of the antenna assemblies further includes an articulating deployment couple affixed to the spacecraft for deploying the antenna assembly, a first antenna affixed to the deployment couple, and a second antenna affixed to the first antenna. The enhanced antenna stowage and deployment system according to the present invention permits the separation and orientation of more than two adjacent antennas which require an extremely precise deployed position relative to a main spacecraft body. As such, the deployment couple further includes a 1-axis separating hinge and/or a 2-axis primary deployment gimbal. At least one of the antenna assemblies further includes a 2-axis secondary deployment gimbal or a rigid connecting structure for affixing the second antenna to the first antenna.