A ball mount for measuring tongue weight of a trailer is disclosed. The ball mount can include a ball portion having a hitch ball configured to couple with a tongue of a trailer. The ball mount can also include a hitch portion for interfacing with a hitch receiver associated with a vehicle. In addition, the ball mount can include a load measurement device associated with the ball portion to determine a magnitude of a downward force on the hitch ball. The load measurement device can include a reservoir having a fluid and a piston disposed therein, and a pressure sensor in fluid communication with the reservoir. The hitch ball can be configured to exert a force on the piston, thereby affecting a pressure of the fluid in response to the downward force on the hitch ball.

The invention provides a sensor assembly for force sensing, the sensor assembly comprising: a first portion having a first and a second through hole, a second portion having a third and fourth through hole, and a first pin and a second pin coupling the first portion to the second portion. At least one out of the first and the second pin comprises a magnetoelastic based sensor for outputting a signal corresponding to a stress-induced magnetic flux emanating from a magnetically polarized region of the pin. The magnetoelastic based sensor comprises at least one direction sensitive magnetic field sensor in an at least partially hollow portion of the pin, which field sensor is configured for determination of a shear force in at least one direction. The invention further provides a tow coupling comprising the sensor assembly. The invention further provides a method for detecting a load.

Tractor Draft Control Testing Device has the capability of testing the draft control of hydraulic system of all types of tractors on the production line and final control of tractor-manufacturing companies.

Systems and methods for magnetoelastic hitch receiver force detection are disclosed. An example vehicle includes a chassis, a trailer hitch receiver configured to receive a trailer hitch arm along an axis, a first pin having a first magnetic field, the first pin disposed above and perpendicular to the axis, a second pin, the first pin and the second pin coupling the trailer hitch receiver to the chassis and a first sensor configured to detect changes in the first magnetic field.

Systems and methods for operating a rotorcraft engine are described herein. Measurements indicative of at least one of current temperature and current pressure at an inlet of the engine are obtained from at least one sensor while the rotorcraft is in flight. At least one current inlet loss is determined from the measurements. Current available engine power of the rotorcraft engine is determined based on the at least one current inlet losses. A visual indication of the current available engine power is produced via a flight display.

The present disclosure relates to a measuring device (42, 43) for measuring forces and/or torques between a motorized vehicle (1) and a trailer or attachment which is towed or pushed thereby, wherein the measuring device (42, 43) has at least three sensor elements (22, 34) which are arranged on a carrier (20, 31), transversely with respect to a virtual longitudinal axis of the motorized vehicle (1) and spaced apart from one another, wherein the measuring device (42, 43) is arranged in a coupling region between the motorized vehicle (1) and the pulled or pushed trailer or attachment, and wherein, in order to transmit their measured values, the sensor elements (22, 34) are connected to an evaluation device (40), which is configured to convert these measured values into signals for force displays and/or torque displays according to magnitude and direction.

A measuring device (60) is configured for measuring forces or torques between a motorized vehicle (1) and a trailer or attachment which is towed or pushed thereby. The measuring device (60) has at least three sensor elements (79, 80) arranged on a carrier (71), transversely with respect to a virtual longitudinal axis of the motorized vehicle (1) and spaced apart from one another. The measuring device (60) is arranged in a coupling region between the motorized vehicle (1) and the pulled or pushed trailer or attachment. In order to transmit their measured values, the sensor elements (79, 80) are connected to an evaluation device (40), which is configured to convert these measured values into signals for force displays and/or torque displays according to magnitude and direction.

A trailer hitch system may include a scale ball mount for supporting a hitch ball as part of a trailer hitch system, and for measuring the tongue weight of a trailer. The scale ball mount may comprise a trailer hitch ball mount. In an embodiment, the scale ball mount may include a biasing component disposed below a hitch ball and a gauge for displaying downward force applied at the hitch ball. The biasing component may be a urethane spring. An indicator may be disposed between the biasing component and the hitch ball, and the indicator may be viewable through an opening in the gauge.

A ball assembly for attachment to a ball mount is described. The ball assembly can include a ball post that is securable to a ball mount. A hitch ball is slidably coupled to the ball post at a ball end of the ball post. A load gauge is disposed at the gauge end of the ball post. A load transfer element is operably associated with both the hitch ball and the load gauge so as to cause a load measurement to display on the load gauge based upon a load applied to the hitch ball.

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 includes 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. The primary strain sensors are located around a circumference of the drive shaft of the propeller, and 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.