A machine tool includes a machine element, an active vibration damper arranged on a region of the machine tool for damping a vibration of the machine element, and a vibration sensor facility arranged to detect the vibration of the machine element at a first point and at a second point of the machine tool, with the vibration of the machine element to be detected being smaller at the second point than at the first point. The active vibration damper is designed to damp the vibration of the machine element as a function of a variation between a first actual value detected by the vibration sensor facility at the first point and a second actual value detected by the vibration sensor facility at the second point.

A vibration controller includes: a piezoelectric element fixed to an object of control; and a quasi-inductor circuit and a negative resistance circuit connected in series to the piezoelectric element.

A microelectromechanical membrane transducer includes: a supporting structure; a cavity formed in the supporting structure; a membrane coupled to the supporting structure so as to cover the cavity on one side; a cantilever damper, which is fixed to the supporting structure around the perimeter of the membrane and extends towards the inside of the membrane at a distance from the membrane; and a damper piezoelectric actuator set on the cantilever damper and configured so as to bend the cantilever damper towards the membrane in response to an electrical actuation signal.

An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

A suspension assembly is described. The suspension assembly including a static member or plate; a moving member or plate movable about an x-axis and a y-axis with respect to the static plate; a sensor mounting region on the moving plate; and one or more shape memory alloy (SMA) elements extending between and coupled to the static plate and moving plate. The SMA elements, when driven by a controller, move the moving plate and the sensor mounting region thereon about the x-axis and the y-axis with respect to the static plate.

Methods, systems, and devices are described for mounting an antenna assembly to a vehicle, whereby rotational degrees of freedom between the antenna assembly and the vehicle are constrained. For example, an antenna mount may employ an intermediate structure between the antenna assembly and the vehicle. In various examples, the intermediate structure may be coupled with one of the vehicle or the antenna assembly by a linear coupling, and the intermediate structure may be coupled with the other of the vehicle or the antenna assembly by a planar coupling. The antenna assembly may be coupled with the vehicle by a compliant coupling that provides a centering force between the antenna assembly and the vehicle. According to various examples, rotational movement between the antenna assembly and the vehicle may be suppressed, and vibration from the vehicle to the antenna assembly may be attenuated.

Methods, systems, and devices are described for mounting an antenna assembly to a vehicle, whereby rotational degrees of freedom between the antenna assembly and the vehicle are constrained. For example, an antenna mount may employ an intermediate structure between the antenna assembly and the vehicle. In various examples, the intermediate structure may be coupled with one of the vehicle or the antenna assembly by a linear coupling, and the intermediate structure may be coupled with the other of the vehicle or the antenna assembly by a planar coupling. The antenna assembly may be coupled with the vehicle by a compliant coupling that provides a centering force between the antenna assembly and the vehicle. According to various examples, rotational movement between the antenna assembly and the vehicle may be suppressed, and vibration from the vehicle to the antenna assembly may be attenuated.

A method and an apparatus for isolating a vibration of a positioning device are provided. The apparatus includes a base plate for the positioning device, at least one active bearing element for bearing the base plate on/at a foundation and at least one evaluation and control device. The apparatus includes at least one means for determining a foundation movement-dependent quantity, wherein the active bearing element is controllable by the at least one control and evaluation device on the basis of the foundation movement-dependent quantity.

A hybrid drive includes an internal combustion engine, an electrical machine, at least one torsional vibration damper, and an electronic control unit. The torsional vibration damper is designed for optimal vibration damping during operation of the internal combustion engine with the full number of cylinders of the internal combustion engine switched-on in internal-combustion-engine mode. The electronic control unit is further designed such that, in purely electric-motor mode where no cylinders are switched on, the electrical machine simulates the cylinder-ignition-dependent torque excitations of the switched-off internal combustion engine substantially identically until the internal combustion engine is switched back on.