A dynamic balancer includes a support frame with a frame plate that has a spindle opening through which a spindle assembly with a rotatable spindle shaft is received. A sensor plate is coupled to at least the support frame, and at least one force sensor is coupled between the sensor plate and the spindle assembly to detect force variations therebetween as the rotatable spindle shaft rotates. A related method for detecting a balance condition of a tire includes providing a plurality of force sensors maintained in a substantially horizontal plane with respect to the tire's rotation, chucking and inflating the tire, spinning the tire to a predetermined speed, generating force data from the plurality of force sensors, calculating an imbalance condition from the force data, and marking the tire at a location of imbalance if the imbalance condition exceeds a predetermined threshold.

A method for controlling the motor of a tool magazine that rotates around a horizontal rotation axis is configured so that: at least two indexing positions for the tool magazine are determined; the load torque acting on the tool magazine when stopped at said indexing positions is measured; an unbalance torque, which is the load torque when stopped at the indexing position at which the load torque when stopped is maximal, is calculated from multiple load torques when stopped; and the servo motor for the tool magazine is controlled on the basis of the unbalance torque.

A method for monitoring an aircraft engine during flight, which includes the steps of: for at least one characteristic frequency of the operation of the engine, measuring at least one synchronous vibration level value; for at least one module of the engine, estimating an out-of-balance value of the module in accordance with the one or more vibration level values measured and at least one sensitivity coefficient; estimating a balancing margin of the module in accordance with the out-of-balance value of said module and a maximum threshold; (d) estimating a remaining number of flights of the aircraft prior to balancing and/or a quality indicator of a preceding balancing operation in accordance with the one or more estimated balancing margins and data representing past balancing operations of the engine.

A method for monitoring an aircraft engine during flight, which includes the steps of: for at least one characteristic frequency of the operation of the engine, measuring at least one synchronous vibration level value; for at least one module of the engine, estimating an out-of-balance value of the module in accordance with the one or more vibration level values measured and at least one sensitivity coefficient; estimating a balancing margin of the module in accordance with the out-of-balance value of said module and a maximum threshold; (d) estimating a remaining number of flights of the aircraft prior to balancing and/or a quality indicator of a preceding balancing operation in accordance with the one or more estimated balancing margins and data representing past balancing operations of the engine.

The present invention relates to a wind turbine rotor balancing method which compensates imbalances between the centers of gravity of the wind turbine blades, in both magnitude and position along said blades, so that the amount of mass needed to carry out this balancing method is minimized, while reducing the loads and vibrations associated with a position of the center of gravity of the rotor not aligned with the axis of rotation thereof, wherein the invention further relates to the wind turbine rotor balancing system and the wind turbine balanced with the above method.

The subject matter of the present invention relates to a system for the optical determination of correction planes in rotating elements, used in the process of balancing, in particular in diagnostic devices equipped with a system which has at least one video camera (K), at least one line projector (RL), a monitor screen (M) and a computer (P) which controls individual component elements of the system, wherein the video camera (K) cooperates with the line projector (RL) while projecting a view of the rotating element (EW) on the monitor screen (M) together with an image of a line (L) projected by means of the line projector (RL). The subject matter of the present invention also relates a method for determining correction planes which consists in that an area of measurement space is defined on the basis of a virtual rotating element (EW) before placing a rotating element (EW) on the shaft of a diagnostic device (PM) onto which line (L) is projected by means of line projector (RL), and subsequently a view of the rotating element (EW) is transmitted by means of the video camera (K) to the monitor screen (M) together with an image of the projected line (L), and thus the run of the line is obtained which maps a change in the value of the radius r.sub.n from the axis of the shaft of the diagnostic device (PM) and the value of distance D.sub.n of the rotating element (EW) from the diagnostic device (PM) in the defined area of measurement space.

The subject matter of the present invention relates to a system for the optical determination of correction planes in rotating elements, used in the process of balancing, in particular in diagnostic devices equipped with a system which has at least one video camera (K), at least one line projector (RL), a monitor screen (M) and a computer (P) which controls individual component elements of the system, wherein the video camera (K) cooperates with the line projector (RL) while projecting a view of the rotating element (EW) on the monitor screen (M) together with an image of a line (L) projected by means of the line projector (RL). The subject matter of the present invention also relates a method for determining correction planes which consists in that an area of measurement space is defined on the basis of a virtual rotating element (EW) before placing a rotating element (EW) on the shaft of a diagnostic device (PM) onto which line (L) is projected by means of line projector (RL), and subsequently a view of the rotating element (EW) is transmitted by means of the video camera (K) to the monitor screen (M) together with an image of the projected line (L), and thus the run of the line is obtained which maps a change in the value of the radius r.sub.n from the axis of the shaft of the diagnostic device (PM) and the value of distance D.sub.n of the rotating element (EW) from the diagnostic device (PM) in the defined area of measurement space.

Embodiments are directed to obtaining data from at least one sensor, the data pertaining to rotor loads and motion, processing, by a device comprising a processor, the data to obtain an estimate of at least one of gross weight (GW) and center of gravity (CG) for a rotorcraft, and outputting the estimate.

A system for monitoring parameters of a vehicle wheel assembly includes a wheel speed sensor configured to produce a wheel speed signal, and a wheel assembly monitoring module operatively connected to the wheel speed sensor. The wheel assembly monitoring module determines a dynamic response of the wheel speed signal at one or more wheel speeds. A wheel assembly health module provides one of a visual output, an audible output, and a haptic output indicating that the wheel assembly has exceeded a selected wheel assembly parameter threshold based on the dynamic response of the wheel speed signal.

A vehicle computer is described that includes a processor and memory storing instructions executable by the processor. The instructions may include, to: determine a vehicle speed; determine, for a first wheel, a first vibration profile; determine, for a second wheel, a second vibration profile that includes a roadway disturbance input; and using the speed and the two profiles, determine a wheel imbalance at the first wheel.