A triplex pneumatic architecture system is disclosed having first, second, and third pneumatic subsystems where triplex redundancy may be accomplished by measuring only one particular node in each system, such as a measured current of the servo valve. Each of the first, second, and third pneumatic subsystems are configured to control a separate redundant pneumatic actuation assembly. Each subsystem may comprise a current sensor to measure a control current from a servo driver to a servo valve that controls the pneumatic actuation assembly to output a measured current value, and a dump valve coupled to a relay. Each processor is configured to generate a termination signal to actuate the first relay to open the first dump valve. The triplex pneumatic architecture system further includes a communication bus to communicatively couple each of the first, second, and third pneumatic subsystems. Each processor is configured to generate the termination signal and to communicate the termination signal to one or more of the relays when one measured current value deviates from the two other measured current values by a predetermined error value.

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.

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.

An actuator for a rotor blade adjustment having an electromechanical drive unit may be connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

An actuator for a rotor blade adjustment having an electromechanical drive unit may be connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

A system for detecting mechanical failure of a connection between a variable differential transformer and a controlled element. The sensor system includes a variable differential transformer with a housing encapsulating a first coil, a bore in the housing, wherein the bore is adjacent to the first coil, a core disposed in the bore, a shaft connectible between the core, at a first end, and the controlled element, at a second end, and a biasing element connected to the shaft. Responsive to a break in the shaft, the biasing element moves the core to an out-of-range position detectable by at least the first coil.

A system for detecting mechanical failure of a connection between a variable differential transformer and a controlled element. The sensor system includes a variable differential transformer with a housing encapsulating a first coil, a bore in the housing, wherein the bore is adjacent to the first coil, a core disposed in the bore, a shaft connectible between the core, at a first end, and the controlled element, at a second end, and a biasing element connected to the shaft. Responsive to a break in the shaft, the biasing element moves the core to an out-of-range position detectable by at least the first coil.

In an example, a system includes a first controller for controlling a first-flight-control surface, a second controller for controlling a second-flight-control surface, and a first override system including a mechanical linkage between the first controller and the second controller. The first override system is configured such that: (i) while less than a first threshold amount of force is applied to the mechanical linkage, movement of the first controller causes a corresponding movement of the second controller and vice versa, and (ii) while greater than the first threshold amount of force is applied to the mechanical linkage, the first controller and the second controller move separately. The system also includes a second override system operable to permanently disconnect the mechanical linkage responsive to greater than a second threshold amount of force applied to the mechanical linkage. The second threshold amount of force is greater than the first threshold amount of force.

A sub-system 200 for an aircraft hydraulic system 20 that includes a first inlet 202 for receiving fluid from a supply 22 of hydraulic fluid, a system valve 210 for controlling fluid flow from the sub-system 200 to a hydraulically-operable system 24 of the aircraft hydraulic system 20, a check valve 220 for permitting fluid flow from the sub-system 200 and preventing or hindering fluid flow into the sub-system 200, a second inlet 240 for receiving fluid from a second supply 28 of hydraulic fluid, and a selector 230. The selector 230 configured to place the system valve 210 in fluid communication with the first inlet 202 when the selector 230 is in a first state, and to place the system valve 210 in fluid communication with the check valve 220 and the second inlet 240 when the selector 230 is in a second state different from the first state.

Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap and an actuator. 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 actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied by a hydraulic system of the aircraft. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied by a local power unit. The local power unit is selectively connectable to an electrical system of the aircraft. The electrical system is to power the local power unit to supply the second pressurized hydraulic fluid.