A method for determining stability of a vehicle having a load suspended from the vehicle is provided. The method can include obtaining measurements from a plurality of sensors positioned on the vehicle, obtaining a measurement from a vehicle accelerometer operative to determine an inclination of the vehicle, determining a position of the load suspended from the vehicle, determining a slung load of the load suspended from the vehicle, using the determined slung load and the determined position of the load suspended from the vehicle, determining tipping moments acting on the vehicle, determining righting moments acting on the vehicle and determining a tipping stability based on the determined tipping moments and determined righting moments.

A method for determining stability of a vehicle having a load suspended from the vehicle is provided. The method can include obtaining measurements from a plurality of sensors positioned on the vehicle, obtaining a measurement from a vehicle accelerometer operative to determine an inclination of the vehicle, determining a position of the load suspended from the vehicle, determining a slung load of the load suspended from the vehicle, using the determined slung load and the determined position of the load suspended from the vehicle, determining tipping moments acting on the vehicle, determining righting moments acting on the vehicle and determining a tipping stability based on the determined tipping moments and determined righting moments.

A touch panel that includes a film having piezoelectric properties, the film having a first principal plane and a second principal plane. A divided electrode is on the first principal plane, and a uniform ground electrode is on the second principal plane and arranged opposite to the divided electrode on the first principal plane.

A sensor including a layer having viscoelastic properties, the layer comprising a void, the void filled with a fluid; and optionally, a more rigid sensing element embedded within the layer. When a force is applied to a surface of the sensor, the shape of the void changes, causing the electrical resistance of the fluid in the void to change. When included, the more rigid sensing element can bear upon the void to cause the electrical resistance of the fluid in the void to change. A direction and intensity of the force can be determined by measuring the change of the electrical resistance of different voids positioned about the sensing element. The layer can be an elastomer, preferably silicone rubber. The fluid can be a conductive liquid, preferably Eutectic Gallium Indium. The sensing element can be plastic and can have a “Joystick” shape. The voids can take the form of channels or microchannels having a predefined pattern and/or shape.

A system for calculating forces exerted into an aircraft component includes a test hinge assembly and a monitoring system. In at least one embodiment, the test hinge assembly is a triangular shaped assembly, and includes at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system is configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

In one aspect, a transducer body includes a support having clevis halves. The sensor body includes a generally rigid peripheral member disposed about a spaced-apart central hub joined to each of the clevis halves. At least three flexure components couple the peripheral member to the hub. The flexure components are spaced-apart from each other at generally equal angle intervals about the hub; the sensor body further including a flexure assembly for some flexure components joining the flexure component to at least one of the hub and the peripheral member, the flexure assembly being compliant for forces in a radial direction from the hub to the peripheral member. Each flexure assembly is configured such that forces transferred concentrate strain at a midpoint along the length of each corresponding flexure component.

A load transducer is disclosed herein. The load transducer includes a body portion having a plurality of sides, the plurality of sides of the body portion including a first side; a plurality of beam portions including a first beam portion and a second beam portion, the first beam portion being coupled to the body portion, the second beam portion being coupled to the first beam portion, and the second beam portion extending along the first side of the body portion; and at least one load cell disposed on one or more of the plurality of beam portions, the at least one load cell configured to measure at least one force or moment component of a load applied to the load transducer. A force measurement assembly including a plurality of load transducers with first and second beam portions is also disclosed herein.

A resonant sensor comprises a proof body subjected to a torque of forces produced by an external mechanical structure, the body comprising: a first and a second interface that can each come into contact with the structure; at least two sensitive zones arranged between these two interfaces; a sensitive zone formed by a plate embedded in a frame secured mechanically to the interfaces, the plate able to resonate under the effect of local mechanical excitations produced at particular points by excitation transducers bearing the plate at several resonant frequencies, sensors picking up the resonant signals produced at the particular points, measurement means measuring the resonant frequency shifts of signals which are linear combinations of the resonant signals picked up, the shifts being a function of mechanical stresses induced by the forces and transmitted to the plate by the frame, the components of the torque of forces being determined from the resonant frequency shifts measured on the plates of the sensitive zones.

The present invention relates to a method and an arrangement for measuring a force and/or moment on a machine element extending along an axis, using the inverse magnetostrictive effect. The machine element has a magnetization region for magnetization, this region fully encompassing the axis. The arrangement includes at least one first magnetic sensor and one second magnetic sensor, each being designed to measure individually a first and a second direction component of a magnetic field that is caused by the magnetization and by the force and/or the moment. The direction components that can be measured using the first magnetic sensor have differing orientations. Likewise, the direction components that can be measured using the second magnetic sensor have differing orientations. The first magnetic sensor and the second magnetic sensor are arranged around the axis at different peripheral positions.

A plate-like supporting body (200) is arranged below a plate-like force receiving body (100) and a deformation body (300) is connected between them. The deformation body (300) is provided with an elastically deformed portion (310) arranged along a connection channel (R1) which connects a first force receiving point (P1) with a second force receiving point (P2), a first base portion (320) and a second base portion (330) which support the elastically deformed portion (310) from below. The upper end of the first base portion (320) supports the vicinity of a first relay point (m1) on the connection channel (R1) so as to sway freely, and the upper end of the second base portion (330) supports the vicinity of a second relay point (m2) on the connection channel (R1) so as to sway freely. An arm-like member (312) which couples a pair of relay points (m1, m2) is used to lower the detection sensitivity of moment around an origin (O) which is exerted on the force receiving body (100), thereby easily adjusting the balance of detection sensitivity between moment and force.