Methods and systems for assisting the piloting of an aircraft are provided. The system includes at least one avionics type system and at least one non-avionics type system. The method includes steps involving receiving avionics type data associated with a flying context of the aircraft; forwarding the avionics type data to a non-avionics type system or computer; determining, in the non-avionics computer, one or more adjustment recommendations for equipment based on the received flying context and/or on predetermined data; displaying one or more recommendations. Various developments are described, in particular the conditions for requesting and/or computing recommendations (e.g. ongoing adjustment of the avionics, similar previous configuration, etc.), the selection and the categorization of recommendations, the handling of adjustment data for the avionics, etc. Software aspects are described.

Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

The invention relates to a mechanical actuator for a high-lift system of an aircraft, wherein the actuator is provided with an internal gearing between an input and an output shaft and comprises an internal sensor for torque measurement, wherein the sensor comprises at least two sensing elements for detecting the input and output torque at separate measuring points, and a common evaluation unit for the at least two sensing elements.

The invention relates to a mechanical actuator for a high-lift system of an aircraft, wherein the actuator is provided with an internal gearing between an input and an output shaft and comprises an internal sensor for torque measurement, wherein the sensor comprises at least two sensing elements for detecting the input and output torque at separate measuring points, and a common evaluation unit for the at least two sensing elements.

A system for distributed control of an aircraft. The system includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components. The aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, and command the flight component to produce a response command.

A system for distributed control of an aircraft. The system includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components. The aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, and command the flight component to produce a response command.

An aircraft wing configuration for a vertical or a short take-off and landing aircraft having a plurality of propeller-blown wings mounted at different longitudinal locations along a fuselage of the vertical take-off and landing aircraft, producing two or more lifting surfaces, fixed at a predetermined acute wing angle greater than 0° and substantially less than 90° relative to a horizontal plane, and having a plurality of flaps disposed behind the wings. The configuration has a plurality of propellers distributed in front of the plurality of wings producing two or more lifting surfaces and mounted such that the wings are externally blown by forced airstreams from the propellers. The propellers produce distributed thrust components, and the plurality of flaps are in the forced airstreams of the propellers when one or more of the flaps is in an extended position.

An aircraft wing configuration for a vertical or a short take-off and landing aircraft having a plurality of propeller-blown wings mounted at different longitudinal locations along a fuselage of the vertical take-off and landing aircraft, producing two or more lifting surfaces, fixed at a predetermined acute wing angle greater than 0° and substantially less than 90° relative to a horizontal plane, and having a plurality of flaps disposed behind the wings. The configuration has a plurality of propellers distributed in front of the plurality of wings producing two or more lifting surfaces and mounted such that the wings are externally blown by forced airstreams from the propellers. The propellers produce distributed thrust components, and the plurality of flaps are in the forced airstreams of the propellers when one or more of the flaps is in an extended position.

Disclosed herein is a monobloc and removable pedal module for an aircraft rudder bar. The pedal module, which is intended for a rudder bar, includes a pedal, at least one integrated adjustment system, and a connection device which enables a removable connection of the pedal module to be produced. The pedal module is a monobloc component in order to simplify and facilitate its replacement via the removable connection obtained by the connection device.