Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing, a lateral-control surface, and a mini-spoiler. The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing, a lateral-control surface, and a mini-spoiler. The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p−1 inputs, receiving as input distinct subsets of 2×p−1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p−1 inputs and delivering as output the two intermediate values.

A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p−1 inputs, receiving as input distinct subsets of 2×p−1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p−1 inputs and delivering as output the two intermediate values.

A method for initializing a device for performing acoustic speech recognition (ASR) using an ASR model, by a computer system including at least one processor and a system memory element. The method includes obtaining a plurality of voice data articulations of predetermined phrases, by the at least one processor via a user interface. The plurality of voice data articulations includes a first quantity of audio samples of actual articulated voice data, and each of the plurality of voice data articulations includes one of the audio samples including acoustic frequency components. The method further includes performing a plurality of augmentations to the plurality of voice data articulations of predetermined phrases, to generate a corpus audio data set that includes the first quantity of audio samples and a second quantity of audio samples including augmented versions of the first quantity of audio samples.

A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.

A drive for a harmonic gear assembly, comprising an input shaft having a shaft axis (A) and an epicyclic carrier unit removably mounted around, and coaxial with the input shaft, the epicyclic carrier unit comprising a carrier having an interior circumference designed to match the outer circumference of the shaft and further comprising a first roller assembly mounted at a first location around the circumference of the carrier unit and comprising a first roller shaft extending substantially parallel to the shaft axis and a first roller rotatably mounted around the first rotor shaft, and a second roller assembly mounted at a second location around the circumference of the carrier unit and comprising a second roller shaft extending substantially parallel to the shaft axis and a second roller rotatably mounted around the second rotor shaft, the first and second rollers extending radially outwards from the carrier to define a major axis between the radially outer surfaces of the first and second rollers, and wherein the outer surface of the carrier unit at locations other than the first and second locations defines a minor axis.

A drive for a harmonic gear assembly, comprising an input shaft having a shaft axis (A) and an epicyclic carrier unit removably mounted around, and coaxial with the input shaft, the epicyclic carrier unit comprising a carrier having an interior circumference designed to match the outer circumference of the shaft and further comprising a first roller assembly mounted at a first location around the circumference of the carrier unit and comprising a first roller shaft extending substantially parallel to the shaft axis and a first roller rotatably mounted around the first rotor shaft, and a second roller assembly mounted at a second location around the circumference of the carrier unit and comprising a second roller shaft extending substantially parallel to the shaft axis and a second roller rotatably mounted around the second rotor shaft, the first and second rollers extending radially outwards from the carrier to define a major axis between the radially outer surfaces of the first and second rollers, and wherein the outer surface of the carrier unit at locations other than the first and second locations defines a minor axis.

A force balance sensor including a mechanical strain amplification system including a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member, at least one strain sensor coupled to the sensor torsion member between the first and second ends, a first torsional stiffening member coupled to the first end of the sensor torsion member, and a second torsional stiffening member coupled to the second end of the sensor torsion member, wherein the first torsional stiffening member and the second torsional stiffening member are coupled to a torque member.

A force balance sensor including a mechanical strain amplification system including a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member, at least one strain sensor coupled to the sensor torsion member between the first and second ends, a first torsional stiffening member coupled to the first end of the sensor torsion member, and a second torsional stiffening member coupled to the second end of the sensor torsion member, wherein the first torsional stiffening member and the second torsional stiffening member are coupled to a torque member.