A compact load cell that simultaneously measures normal and shear forces in a load plane offset from a sensor plane by a distance h. The compact load cell comprises at least three force sensing elements (preferably four) arranged in the sensor plane about a point and spaced a distance d from the point. All force sensing elements may be spaced by the same distance or the distance may be different for one or more force sensing elements. Each force sensing element comprises a pressure sensor encased in a force transmission medium. A load plate is in contact with the force transmission medium and a load beam is connected at one end to the load plate above the point of the sensor plane and extends to the load plane. Forces acting in the load plane are transmitted to the sensor plane by the load beam and load plate. The forces are resolved to determine the normal and shear forces acting at the load plane. The compact load cell may be applied to determine forces acting on, for example, an unmanned aerial vehicle.

An integrated wireless data system and method for avionic performance indication for measuring, monitoring and displaying in-use, real-world engine-out characteristics on a propeller driven aircraft for the purposes of health monitoring, performance optimization, and regulatory compliance is provided. Engine-out characteristics may be measured either at the propeller extension hub mounted between the engine and propeller, on the crankshaft flange, or on the propeller itself, and include, but are not limited to, the engine output torque, thrust, vibration, bending loads and temperature. Data may be transmitted wirelessly to a base unit located inside the cockpit and user selected parameters are updated on a display in real-time. The system may also store all collected data, for later download and analysis. The system may also have a software interface that can be used to download, view and analyze all recorded data, as well as to configure the system settings and alerts.

A system and method of non-intrusive thrust measurement of a gas turbine engine. The system comprises a transmitter disposed at a boundary of fluid flow and at least one receiver adapted to receive transmissions from the transmitter. A processor is coupled to the receivers to determine a parameter from a characteristic of the transmission at the receiver suite and adapted to determine a thrust parameter from the parameter. A method for non-intrusively measuring engine thrust includes transmitting a wave across the exhaust plume, receiving the transmitted wave and determining a measurement parameter of the exhaust plume based on a characteristic of the received wave, and comparing the measurement parameter to a reference parameter and determining the thrust based on the comparison.

Embodiments of the invention relate to a thrust stand and a method of measuring thrust. Embodiments of the invention pertain to a method of calibrating a thrust stand. Embodiments of the subject thrust stand can incorporate a passive eddy current based damper. Specific embodiments of the passive eddy current based damper can function without contact with the balance arm. Further specific embodiments of the passive eddy current based damper can be used in a vacuum. Embodiments can utilize signal analysis techniques to identify and reduce noise. A logarithmic decrement method can be used to calibrate the thrust stand. Force measurements can be made with embodiments of the subject thrust stand for a standard macroscale dielectric barrier discharge (DBD) plasma actuator and/or other thrust producing devices.

A method determines a thrust force of an aircraft engine that is attached to an aircraft by a force transferring element having a strain gauge for determining its strain state and a temperature sensor for measuring a surface temperature of the force transferring element adjacent to the strain gauge. The method includes: determining the surface temperature; determining a strain of the force transferring element; determining the strain state of the force transferring element based on the determined strain and compensating for temperature effects by taking into account the surface temperature, the compensation of the temperature effects taking into account both static and transient influences; and calculating the thrust force of the aircraft engine from the determined strain state.

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

A method for measuring a thrust margin of a turbomachine, in which data are acquired including the thrust margin which is determined as a function of a specified thrust and a measured thrust, the measured thrust being determined on a measuring bench which includes a bench equipment and on which the turbomachine is, wherein a time evolution of the thrust margin is modelled by at least one linear or affine function which is calculated for at least one determined time interval of the thrust margin, at least one bias of the bench equipment is calculated relative to at least one linear or affine function having been calculated, the thrust margin is corrected by subtracting from it at least one bias of the bench equipment in at least one determined time interval.

Disclosed is A load cell assembly for transferring a load to a transducer, the load cell assembly comprising a contact plate adapted to contact an object generating the load; a transducer adapted to generate an electrical signal proportionate to the load; and a ball component adapted to transfer the load from the contact plate to the transducer; wherein the contact plate, ball component, and transducer are arranged so that the contact plate and transducer are simultaneously in contact with the ball component.

A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from a central axis extending through the propeller and a propeller drive shaft, is provided. The method comprises: obtaining measurements representative of strain in the propeller drive shaft using multiple primary strain sensors, each primary strain sensor providing respective measurements representative of strain; wherein the primary strain sensors are located around a circumference of the drive shaft of the propeller; and wherein each strain sensor is located such that it crosses a plane defined by the radial direction of a blade and the central axis, the plane being bounded by the central axis. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.