Abstract: A method of machining ceramic matrix composite components includes providing an ultrasonic vibration tool having a tool tip, and exciting the tool by providing a control current, such that the tool tip is repeatedly vibrated towards and away from a ceramic matrix composite workpiece. A slurry feed is supplied including abrasive particles to a surface to be machined by the tool tip. A vibration amplitude of the tool tip is controlled by sensing load on the tool and communicating with a computing device. The computing device controls the vibration amplitude of the tool tip. The computing device is provided with at least one memory programmed with historic data, and is operable to modify the vibration amplitude signal being sent to the tool, and comparing resulting load levels due to the change in vibration amplitude signals, and storing the change in vibration amplitude signals at the memory.

Abstract: An electrical socket assembly is provided with contactors (50,51, FIG. 3) lying in a pin-receiving hole, which provides a high withdrawal force for the pin (31). Each contactor is of the type that includes a pair of circular bands and a plurality of inwardly-bowed beams extending between the bands to resiliently contact the pin. The assembly includes two of such contactors lying in tandem in the socket hole, to more uniformly guide the pin along the hole, and provide low contact resistance and a high resistance to withdrawal for a pin of given diameter. The socket includes two internal grooves (82,84) that each hold one contactor, and an intermediate wall (80) between the grooves that prevents the contactors from riding up on one another to jam the pin in the hole.

Abstract: A socket assembly is provided at the end of a heavy electrical cable which includes sockets designed to be pushed into connection with pins on an aircraft, to pass current between them, which provides low resistance to avoid heating while also providing a high withdrawal force to prevent the weight of the cable end from pulling it out of connection with the aircraft pins. The sockets include pin-receiving holes, with grooves in the hole walls for holding multi-beam contactors. Each contactor includes a pair of spaced circular bands and a plurality of beams extending between the bands and bowed radially inwardly to resiliently contact the pin. A socket includes two of such contactors, whose beams engage the plug at two locations spaced along the hole to more uniformly guide the pin along the hole and provide low contact resistance and a high resistance to withdrawal. The contactors are initially plastically deformed when the pin is first inserted, to assure that a high withdrawal force is achieved.