Distributed trailing edge wing flap systems

A wing flap system for an aircraft, the wing flap system comprising:

• first, second, third and fourth flaps movable between respective deployed positions and respective retracted positions, the first and second flaps being movable relative to a first fixed trailing edge of a first wing of the aircraft, the third and fourth flaps being movable relative to a second fixed trailing edge of a second wing of the aircraft;
• first, second, third, fourth, fifth, sixth, seventh and eighth actuators, the first and second actuators to move the first flap relative to the first fixed trailing edge, the third and fourth actuators to move the second flap relative to the first fixed trailing edge, the fifth and sixth actuators to move the third flap relative to the second fixed trailing edge, the seventh and eighth actuators to move the fourth flap relative to the second fixed trailing edge, respective ones of the first, second, fifth and sixth actuators being hydraulically drivable via first pressurized hydraulic fluid to be supplied by a first hydraulic system of the aircraft, respective ones of the third, fourth, seventh and eighth actuators being hydraulically drivable via second pressurized hydraulic fluid to be supplied by a second hydraulic system of the aircraft;
• and
• first, second, third and fourth local power units respectively located at the first, third, fifth, and seventh actuators, the first actuator being hydraulically drivable independently from the first pressurized hydraulic fluid via third pressurized hydraulic fluid to be supplied to the first actuator from a compensator of the first local power unit in response to a failure of the first hydraulic system, the third actuator being hydraulically drivable independently from the second pressurized hydraulic fluid via fourth pressurized hydraulic fluid to be supplied to the third actuator from a compensator of the second local power unit in response to a failure of the second hydraulic system, the fifth actuator being hydraulically drivable independently from the first pressurized hydraulic fluid via fifth pressurized hydraulic fluid to be supplied to the fifth actuator from a compensator of the third local power unit in response to the failure of the first hydraulic system, the seventh actuator being hydraulically drivable independently from the second pressurized hydraulic fluid via sixth pressurized hydraulic fluid to be supplied to the seventh actuator from a compensator of the fourth local power unit in response to the failure of the second hydraulic system.

A wing flap system for an aircraft, the wing flap system comprising:

• a flap movable between a deployed position and a retracted position, the flap being movable relative to a fixed trailing edge of a wing of the aircraft;
• first and second actuators to move the flap relative to the fixed trailing edge, the first and second actuators being commonly hydraulically drivable via first pressurized hydraulic fluid to be supplied by a hydraulic system of the aircraft;
• and
• a local power unit located at the first actuator, the first actuator being hydraulically drivable independently from the first pressurized hydraulic fluid via second pressurized hydraulic fluid to be supplied to the first actuator from a compensator of the local power unit in response to a failure of the hydraulic system.