A redundant load transmission includes an input shaft configured to receive a rotational torque from a primary drive, an output shaft configured to transmit the rotational torque to an actuator, and a coupling assembly configured to connect the input shaft to the output shaft to transmit the rotational torque. The input shaft is configured to receive the rotational torque from the primary drive and transmit the rotational torque through the coupling assembly when the coupling assembly is in a primary drive configuration. The coupling assembly is configured to be disconnected from the input shaft and transmit a rotational torque to the output shaft from a secondary drive when the coupling assembly is in a secondary drive configuration.

An electromechanical actuator (EMA) includes a plurality of modes and includes an electrical motor having a motor shaft extending along an axis (A) and that drives the shaft to rotate about the axis and a gear assembly mounted around, and in geared connection with the shaft, to rotate with the shaft. The EMA output is connected to the gear assembly such that rotation of the motor shaft causes rotation of the output via the gear assembly, the output rotating at a speed which is a predetermined fraction of the speed of rotation of the motor shaft based on the gear ratio of the gear assembly. The EMA also includes a synchroniser comprising a first conical portion connected to an end of the motor shaft, and a second conical portion connected to a ratchet. The synchroniser has an engaged position and a disengaged position.

An aircraft includes a plurality of control targets, avionics devices and a control switch unit. The control targets each includes a power line communication unit configured to perform communication via a power line. The avionics devices are respectively connected with the control targets via exclusive-use signal lines. The avionics devices are configured to control the control targets via the signal lines. The avionics devices each includes a PLC unit configured to perform communication via the power line. The control switch unit is configured to, when an abnormality occurs in any of the avionics devices, cause another one of the avionics devices to control the control target which has been controlled by the any of the avionics devices, via the power line.

Apparatus and methods for controlling unmanned systems (UMSs), such as unmanned aircraft, are provided. A UMS can include core systems, auxiliary systems, a payload, a physical computer, a network, and a power system. The network can enable the physical computer to communicate with the auxiliary systems using a second communications tier and with the payload using a third communications tier. The network and the physical computer can logically separate the second and third communications tiers. The power system can provide a first, second, and third power domains respectively for the core systems, the auxiliary systems, and for the payload. The power system can include circuitry that inhibits an overcurrent fault in the third power domain from causing an electrical fault in the first and second power domains and that inhibits an overcurrent fault in the second power domain from causing an electrical fault in the first power domain.

A system architecture for operation of aircraft flaps. The system architecture includes a first pair of motor drive units, the first pair comprising a first motor drive unit (MD1) and a second motor drive unit (MD3), and a second pair of motor drive units, the second pair comprising a third motor drive unit (MD2) and a fourth motor drive unit (MD4). The system further includes a first plurality of switches connected between the first motor drive unit (MD1) and the second motor drive unit (MD3), the first plurality of switches configured to operate a first electric motor and a second electric motor, and a second plurality of switches connected between the third motor drive unit (MD2) and the fourth motor drive unit (MD4), the second plurality of switches configured to operate a third electric motor and a fourth electric motor.

An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

A linear electromechanical actuator with a main screw-nut assembly driven by a main motion device and having a hollow screw with an abutting surface; an anti-jamming piston arranged coaxially within the screw and shiftable between an engaged position in which locking dogs interfere with the abutting surface and a disengaged position in which the piston is free to slide within the screw; and actuating elements configured to shift the piston from the engaged to the disengaged position upon electrical or mechanical failure of the actuator. The actuating elements include a key axially movable between the engaged and disengaged positions and having a locking section, configured to bias the locking dogs into interference with the abutting surface in the engaged position, and an unlocking section, configured to allow free sliding of the piston within the screw in the disengaged position. An anti-jamming device for operating a critical flight control surface.

Method for controlling and damping the motion of a hydraulic actuator in an electro hydrostatic actuator (EHA) system comprising an electric motor, a hydraulic pump and a hydraulic fluid circuit connecting the hydraulic pump and the hydraulic actuator includes comprising: energising the electric motor to drive the hydraulic pump to supply hydraulic fluid to the hydraulic actuator through the hydraulic fluid circuit in an active mode of operation; providing a flow path between the hydraulic actuator and the hydraulic pump in a damping mode of operation such that hydraulic fluid can flow via the flow path through the hydraulic pump when the hydraulic actuator is driven by an external force; and determining a desired amount of damping to be applied to the hydraulic actuator in the damping mode of operation and providing the electric motor with one or more energy consuming means configured to provide the desired amount of damping.

A first air data value is generated based on a first set of parameters. A second set of parameters that does not include any of the first set of parameters is processed through an artificial intelligence network to generate a second air data value. The second set of parameters is processed through a plurality of diagnostic artificial intelligence networks to generate a plurality of diagnostic air data values. Each of the plurality of diagnostic artificial intelligence networks excludes a different one of the second set of parameters. One of the second set of parameters is identified, based on the first air data value and the plurality of diagnostic air data values, as a fault source parameter that is associated with a fault condition.

A manual brake override system includes a gear system, an electric motor in operative communication with the input of the gear system, a holding brake in operative communication with the input of the gear system. The holding brake is configured to prevent movement within the gear system when engaged. A manual handwind is provided in operative communication with the input of the gear system and the manual handwind and holding brake are configured such that the input of the gear system can be driven, with the manual handwind, whilst the holding brake is engaged.