Abstract: A deployment system for a spacecraft may include a fitting for coupling a deployable device to the spacecraft, and a moment bearing shear ball assembly. The moment bearing shear ball assembly may include a shear ball engaged within the fitting, and a moment collar mounted onto the shear ball. The moment collar may have a planar surface engaged with a planar surface of the fitting. A separation interface may be defined between at least one of (1) mating surfaces of the fitting and the shear ball and (2) mating surfaces of the fitting and the moment collar. Engagement of the shear ball within the fitting constrains shear forces in at least two axes and axial forces in at least a third axis. Engagement of the moment collar with the shear ball and the fitting constrains overturning moments of the shear ball about at least two axes, and axial forces in at least a third axis.

Abstract: An electrical interface can include one or more connector devices that facilitate communication between components while they are connected. The connector devices can provide a secure communication and/or power link that resists infiltration by foreign object debris (“FOD”) as well as redundant electrical pathways. The connector devices can further provide mechanisms that are lightweight, are operable in a broad range of temperatures (e.g., low temperatures), accommodate displacement without loss of electrical continuity, and are of low resistance and induction. The connector devices can further provide a kickoff force upon separation of the components.