Abstract: A supporting frame for aerospace applications comprises a plurality of rods, which are arranged along two bases substantially parallel and opposite each other, and along two sides, which are substantially parallel and opposite to each other and are coupled to each other via the two bases; the rods are coupled to each other in a mutually rotating manner by nodes so as to be able to configure the supporting frame between a deployed operating condition and a compacted operating condition; the nodes are spaced apart from one another in the deployed operating condition and are each hinged to at least two of the rods; in the compacted operating condition, each of the nodes is placed side by side with two adjacent nodes so as to form, together, two supporting members arranged at opposite longitudinal ends of the supporting frame and each being ring-shaped.

Abstract: A connection unit comprising two female connectors configured to be connected to respective circuit branches of a fluidic line and a coupling element for coupling the connectors together and establish a fluidic connection between the circuit branches, wherein the connectors are provided with first, normally closed sealing elements to define a sealing termination of the circuit branches when the connectors are disconnected from each other; the coupling element includes a double-male connector separable from the female connectors and provided with a pair of shanks that can be coupled to the respective female connectors and a control element movable between a first position where the coupling element can be coupled to the connectors in a mechanical pre-coupling condition without fluidic connection between the female connectors and a second position where the shanks of the double-male connector engage the respective female connectors and establish a fluidic connection therebetween.

Abstract: An on-orbit servicing spacecraft includes an engagement system to engage a space vehicle or object to be serviced or tugged, so as to form a space system, and an electronic reaction control system to cause the spacecraft to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft to carry out given maneuvers.

Abstract: A supporting frame for aerospace applications comprises a plurality of rods, which are arranged along two bases substantially parallel and opposite each other, and along two sides, which are substantially parallel and opposite to each other and are coupled to each other via the two bases; the rods are coupled to each other in a mutually rotating manner by nodes so as to be able to configure the supporting frame between a deployed operating condition and a compacted operating condition; the nodes are spaced apart from one another in the deployed operating condition and are each hinged to at least two of the rods; in the compacted operating condition, each of the nodes is placed side by side with two adjacent nodes so as to form, together, two supporting members arranged at opposite longitudinal ends of the supporting frame and each being ring-shaped.