Abstract: The present disclosure provides a thermal management system for a satellite. The system may include a plurality of photovoltaic cells configured to generate electrical power, an active array antenna including transmit-receive (T/R) modules with power amplifiers, a thermal core thermally coupled to the photovoltaic cells and antenna, and a phase-change material (PCM) element disposed within the thermal core and thermally coupled to the T/R modules. The thermal core may be configured to spread heat across the satellite. One or more of the photovoltaic cells may be configured to radiate heat generated by the T/R modules. The system may enable efficient thermal management in a compact satellite design by utilizing the photovoltaic cells as radiative surfaces and incorporating the PCM element to stabilize temperature fluctuations.

Abstract: One embodiment disclosed herein is related to a device for pointing a radiating element. The device includes an aligned radiating surface; a hinge that is circumferentially mounted to a rear side of the aligned radiating surface, the hinge configured to change azimuth of the aligned radiating surface; and a Tubular Universal joint (TU-joint) having one end coupled to a rear side of the aligned radiating surface and a second end coupled to a base, the TU-joint being configured to change an elevation of the aligned radiating surface. Another embodiment is related to a Tubular Universal-joint (TU-joint). In the embodiment, the TU-joint includes a hollow tube having a first end and a second end; a plurality of slits along the surface of the tube; and a plurality of members between the plurality of slits, each of the plurality of members configured to bear a portion of a load of the TU-joint, wherein the TU-joint is configured to be axially and torsionally stiff while being bendable.