An example device includes an inner element, an outer surrounding element, and a plurality of connecting flexural elements coupled between the inner element and the outer surrounding element. The inner element has a plurality of reflective surface areas that are configured to reflect light to a sensor. The outer surrounding element surrounds the inner element. The plurality of connecting flexural elements allow the inner element to move relative to the outer surrounding element.

An example device includes an inner element, an outer surrounding element, and a plurality of connecting flexural elements coupled between the inner element and the outer surrounding element. The inner element has a plurality of reflective surface areas that are configured to reflect light to a sensor. The outer surrounding element surrounds the inner element. The plurality of connecting flexural elements allow the inner element to move relative to the outer surrounding element.

An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine includes a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit, a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit, and a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine includes a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit, a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit, and a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

The invention relates to a twisting torque sensor, comprising a transmission shaft (12) subjected to the torque to be measured, a reference shaft (14), and a device for measuring an angular deformation representing the torque to be measured between the two shafts. The torque sensor is characterised in that the transmission shaft (12) comprises a bore (24) extending from one end of the transmission shaft (12), referred to as input (28) of the shaft, to an opposite end, and in that the torque sensor comprises an enclosure (22) for confining the temperature of the two shafts, and a fluid circulation circuit including a portion made up of said bore (24), an injector (32) for injecting the fluid into the bore (24) at said input (28) of the shaft, and a fluid temperature sensor (34) in the fluid circulation circuit, the measured temperature being intended for correcting the torque measurement.

A force sensor includes a first member, a second member, an intermediate member, a first elastic structure that couples the first member and the intermediate member, a second elastic structure that couples the second member and the intermediate member, and a displacement detector that measures displacements of the first member and the second member. It is possible to provide a force sensor that has high detection precision and that is compact.

A force sensor includes a first member, a second member, an intermediate member, a first elastic structure that couples the first member and the intermediate member, a second elastic structure that couples the second member and the intermediate member, and a displacement detector that measures displacements of the first member and the second member. It is possible to provide a force sensor that has high detection precision and that is compact.

A turbomachine with at least one rotatable shaft and at least one device for measuring a rotational movement of a rotatable structural component), in particular of the shaft, is provided. The device has a receiver and a first pattern carrier that has at least one pattern site. Here, the device comprises a second pattern carrier with at least one pattern site, wherein the pattern carriers are respectively connectable or connected to the rotatable structural component, so that they are rotatable together with the same about a rotational axis with respect to the receiver, namely in such a manner that the pattern site of the first pattern carrier is positioned in congruence with the pattern site of the second pattern carrier, and wherein the receiver is embodied and configured for detecting whether or not the pattern sites are positioned in congruence with one another.