A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

A compressor variable angle measurement system for guiding the positioning variable vanes supported on a penny of a compressor of a gas turbine engine. The system comprising a gauge assembly that is connectable to a computing device. the gauge assembly comprises a base plate and a clamp arm. The gauge assembly is configured to removably grip a variable vane between three vane contact portions of the baseplate and the vane contact portion of the clamp arm and on the leading edge vane engaging portion and the trailing edge vane engaging portion of the base plate, the stagger angle of the variable vane with respect to the radial setting pin being determined by the computing device from measurements made by an inertial measurement unit.

Method for managing the energy in a system for verifying the inflation pressure of the tires of an aircraft, consisting in measuring, by a pressure sensor, at least one inflation pressure of each of the tires, obtaining a unique identification data relating to each of the tires, and sending via the wireless communication link the measurements and data thus collected to a processing unit disposed in or out of the aircraft for them to be available to a pilot or a maintenance operator, the step of sending the measurements and data being carried out in an acyclic manner as a function of a trigger signal given by a motion detector that detects the motion of the wheels of the aircraft as long as the speed is lower than a predetermined maximum speed.

A method is for detecting a blockage of a wind vane (12) of an aircraft, with the wind vane (12) including a support (20), a paddle (22) mounted rotating relative to the support (20) along an axis (A), a motor (28) able to exert a rotational torque on the paddle (22) along the axis (A), the motor (28) being connected to a processing unit (18). The method includes applying a predetermined blockage detection torque on the paddle (22) by the motor (28); measuring at least one piece of information representative of a resistance of the paddle (22) to the predetermined detection torque; and generating, via the processing unit (18), a blocking information signal, if a predetermined condition based on the representative information is verified.

A method and system for determining an estimation of an anemometric parameter of an aircraft. The anemometric parameter including an angle of attack, a sideslip angle and a calibrated airspeed. The method including obtaining an indication of a secondary surface state of the aircraft; obtaining a position indication of a horizontal primary surface; obtaining a load applied estimation on a corresponding actuator using the position indication of the horizontal primary surface and the position of the corresponding actuator; accessing a lookup table with the indication of the secondary surface state of the aircraft, the load estimation applied on the corresponding actuator, and the position of the corresponding actuator; obtaining an estimation of the anemometric parameter associated with the horizontal primary surface; providing the estimation of the anemometric parameter associated with the horizontal primary surface and wherein the lookup table is generated during a learning phase.

A landing aid method and device for an aircraft including a unit for calculating automatically in a repetitive manner, during a final approach of the aircraft with a view to landing on a landing runway, using at least a ground speed of the aircraft, a height of the aircraft in relation to the ground, and a target vertical speed representing a vertical speed required on contact with the landing runway, a slope angle of a flight path allowing the aircraft to perform a flare, checking at least the target vertical speed on contact with the landing runway, and a unit for displaying automatically, on at least one screen of the flight deck of the aircraft, a first symbol illustrating the current slope angle of the aircraft and a second symbol illustrating the calculated slope angle.

A vehicle control system may include a vehicle frame, a mount secured to the vehicle frame and configured for rigidly securing a smartphone therein such that motions experienced by the vehicle frame are correspondingly experienced by the smartphone, and system electronics arranged on the frame and in communication with the smartphone and vehicle controllers, the system electronics configured to receive signals from the smartphone and control directional devices of the vehicle based on the signals via the vehicle controllers. A system for preparing signals for transmission to the vehicle to control navigation may also be provided.

A device for monitoring and estimating parameters relating to the flight of an aircraft includes an estimation module 4 for determining an estimation of the values of the parameters relating to the flight of the aircraft and for generating residues, a detection module for determining the statuses associated with each of said sensors C1, C2, . . . , CN and with a parameter P1 corresponding to the weight of the aircraft, a transmission module for transmitting the statuses associated with each of said sensors C1, C2, . . . , CN to a user device and, on the next iteration, to the estimation module.

An apparatus in which electric power is generated for an electrical load from differentials in electric field strengths within a vicinity of powerlines includes: a plurality of electrodes separated and electrically insulated from one another for enabling differentials in voltage resulting from differentials in electric field strength experienced there at; and electrical components electrically connected therewith and configurable to establish one or more electric circuits whereby voltage differentials cause a current to flow through the established electric circuit for powering the electrical load. Preferably, the apparatus includes a control assembly having one or more voltage-detector components configured to detect relative voltages of the electrodes; and a processor enabled to configure—based on the detected voltages and based on voltage and electric current specifications for powering the electrical load—one or more of the electrical components to establish an electric circuit for powering the electrical load.

An apparatus and method for performing optical caliper measurements remotely, including an unmanned aerial vehicle, a camera attached to the unmanned aerial vehicle, and an optical caliper measurement tool attached to the unmanned aerial vehicle, where the optical caliper measurement tool includes a mount, a laser source attached to the mount, and a beam splitter attached to the mount, where the laser source is configured to direct a laser beam through the beam splitter to split the laser beam into two parallel laser beams separated by a fixed distance.