Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a collection engine to obtain first monitoring information corresponding to a first set of control surfaces of an aircraft, the first set including a first control surface on a first side of the aircraft and a second control surface on a second side of the aircraft, the second side opposite the first, and obtain second monitoring information corresponding to a second set of control surfaces of the aircraft, the second set including a third control surface on the first side and a fourth control surface on the second side. The example apparatus further includes a non-responsive component detector to determine if one of the control surfaces is non-responsive based on the first and the second monitoring information, and a command generator to deactivate the first set when the non-responsive component detector determines that the first control surface is non-responsive while the second set remains active.

Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap, an actuator, a first hydraulic module, and a second hydraulic module. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The actuator is to move the flap relative to the fixed trailing edge. The first hydraulic module is located at the actuator. The second hydraulic module is located remotely from the first hydraulic module and includes a local power unit. The actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module.

A monitoring system includes a movable surface of an aircraft, an actuation system for the movable surface of an aircraft including actuators, a first position sensor adapted to measure a position of a first actuator of the actuators and a second position sensor adapted to measure a position of a second actuator of the actuators. The monitoring system also includes a first force sensor adapted to measure forces passing through the first actuator of the actuators and a second force sensor of the at least two force sensors being adapted to measure forces passing through the second actuator of the actuators. The monitoring system also includes a calculator configured to detect skew of the movable surface and excess force passing through the first and/or second actuator from the position obtained by the at least two position sensors and the force measured by the at least two force sensors.

An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part. The sensor is configured to detect a first relative position of the first and second parts indicative of the wing structure supporting a load, and a second relative position of the first and second parts indicative of the wing structure being supported.

A proportional brake is provided and includes first and second bodies, a spring element, a coil and a booster coil. The first body includes brake plates and the second body includes thrust plates. The second body is disposed such that the thrust plates are interleaved with the brake plates and is rotatable and movable with respect to the first body. The spring element urges the second body to move toward the first body such that the thrust plates are urged toward braking engagements with the brake plates. The coil is provided at a first side of the brake plates and, when energized, generates a first flux moment on the second body in opposition to the spring element. The booster coil is provided at a second side of the brake plates and, when energized, generates a second flux moment on the second body in support of the spring element.

A proportional braking system is provided for use with a movable surface which is movable relative to a housing. The proportional braking system includes a variable displacement brake which is configured for displacement toward or away from braking engagement with the movable surface in proportion to an input command and a brake driver which is receptive of data reflective of movements of the movable surface relative to the housing and which issues the input command to the variable displacement brake in accordance with the data.

A proportional brake is provided and includes first and second bodies, a spring element, a coil and a booster coil. The first body includes brake plates and the second body includes thrust plates. The second body is disposed such that the thrust plates are interleaved with the brake plates and is rotatable and movable with respect to the first body. The spring element urges the second body to move toward the first body such that the thrust plates are urged toward braking engagements with the brake plates. The coil is provided at a first side of the brake plates and, when energized, generates a first flux moment on the second body in opposition to the spring element. The booster coil is provided at a second side of the brake plates and, when energized, generates a second flux moment on the second body in support of the spring element.

A flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.

Methods and systems for detecting skew in a wing slat of an aircraft are provided. At least one pair of sensors associated with the wing slat is excited via at least one first electronic device. In response to the exciting and at the at least one first electronic device, at least one pair of signals indicative of at least one pair of state-change counts for the at least one pair of sensors is obtained. The at least one pair of state-change counts is transmitted to at least one second electronic device communicatively coupled to the at least one first electronic device. At the at least one second electronic device, a skew level of the wing slat is determined based on the at least one pair of state-change counts.

A system and method for controlling one or more flaps of a wing of an aircraft include a first flap moveably secured to a first wing of the aircraft. The first flap is moveable between an extended position and a retracted position. First and second actuators are coupled to the first flap. A flap control unit is in communication with the first and second actuators. The flap control unit is configured to operate the first and second actuators to move the first flap between retracted and extended positions, monitor a first electrical signal provided to the first actuator, monitor a second electrical signal provided to the second actuator, and determine that the first and second actuators are synchronized by monitoring the first and second electrical signals.