Abstract: A fluid interface is disclosed including a fluid controller mounted onto a host structure. The fluid controller includes a manifold with a fluid outlet port and a fluid inlet port. The fluid controller includes fluid sensors operatively configured to measure flow characteristics of one or more fluids transferred between the fluid inlet port and the fluid outlet port, wherein the fluid inlet port is coupled to at least one fluid source. The fluid interface includes a fluid connector mounted onto the host structure. The fluid connector includes an actuator mounted onto the exterior side of the host structure, a valve coupled to an actuator rod of the actuator, and an elastically deforming tubing comprising a first end and a second end, wherein the first end is operatively connected to the valve and the second end is operatively connected to the fluid outlet port.

Abstract: The disclosed system comprises one or more small satellites (e.g., CubeSats), one or more ground transmitters, and one or more downlink receivers to facilitate ground-to-space short-burst data communications. The CubeSats are miniaturized or small-form satellites that orbit the Earth transmitting data to and from the ground transmitters and the downlink receivers in low Earth orbit. To efficiently use its surface area, in various embodiments, the CubeSats are designed with deployable and folding wings such that the zenith-pointing side of the wings comprises solar panels and the nadir-pointing side of the wings comprises an antenna. In various embodiments, to increase the data transmission capacity of the CubeSats, the CubeSats comprise a deployable phased array antenna and a software defined radio.

Abstract: The disclosed system comprises one or more small satellites (e.g., CubeSats), one or more ground transmitters, and one or more downlink receivers to facilitate ground-to-space short-burst data communications. The CubeSats are miniaturized or small-form satellites that orbit the Earth transmitting data to and from the ground transmitters and the downlink receivers in low Earth orbit. To efficiently use its surface area, in various embodiments, the CubeSats are designed with deployable and folding wings such that the zenith-pointing side of the wings comprises solar panels and the nadir-pointing side of the wings comprises an antenna. In various embodiments, to increase the data transmission capacity of the CubeSats, the CubeSats comprise a deployable phased array antenna and a software defined radio.