Bombardier Inc.

Université De Sherbrooke

Short Brothers Plc

Learjet Inc.

Vlad Iliescu

Gustave Nfonguem

Marc Denninger

Patrick Chouinard

Jean-Sébastien Plante

Robert Young

Avraham Ardman

Waseem Wahba

Menas Salib

Jean - Sebastien Plante

An aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

Aircraft with distributed hydraulic system

An aircraft wing includes a groove extending along a length between a forward extremity and an aft extremity. A forward segment of the groove extends upwardly to the forward extremity. The forward extremity is a highest point of the groove. A flap carriage is mounted to the groove and displaceable therealong. A flap is pivotably attached to the flap carriage to define a flap pivot axis about which the flap is rotatable. The flap is displaceable with the flap carriage. An actuator has an arm being extendable between an extended position and a retracted position to displace the flap carriage along the groove. The flap carriage in the retracted position being disposed in the forward segment of the groove and the flap being rotated about the flap pivot axis to position the flap trailing edge in negative flap deployment.

Aircraft wing with deployable flap

Methods and apparatus for distributing electric power from a power source of an aircraft to a plurality of electrical loads of the aircraft during a limited power availability condition are disclosed. An exemplary method comprises: distributing electric power from the power source of the aircraft to the plurality of electrical loads; receiving one or more signals indicative of a demand for electric power by one or more of the plurality of electrical loads; and adjusting the power distribution to the plurality of electrical loads based on the demand for electric power by the one or more plurality of electrical loads. The power distribution is also adjusted to maintain an overall power consumption of the plurality of electrical loads at or below a threshold.

Apparatus and methods for distributing electric power on an aircraft during a limited power availability condition

Actuators and methods useful in the operation aircraft flight control surfaces are disclosed. Some of the actuators and methods disclosed may be useful in the operation flight control surfaces when a fault condition such as a jam associated with an actuator is detected. An exemplary electromechanical actuator disclosed comprises: a motor; a first screw configured for translation movement relative to a structure of the aircraft when driven by the motor; a second screw mounted in series with the first screw; and a fuse element coupling the first screw and the second screw together to permit translation movement of the second screw together with the first screw. The fuse element may permit at least partial disengagement of the second screw from the first screw to permit translation of the second screw relative to the first screw. The fuse element may also allow an active flutter damping of the flight control surface. The fuse element may comprise magneto-rheological fluid.

Actuators and methods for aircraft flight control surfaces

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.

Slat skew detection system and method

A selector lever includes a housing with front and rear ends and a lever with a shaft pivotally disposed on a cross-shaft. The shaft defines a shaft axis. The lever has a top that is disposed outside of the housing. A movable shaft moves substantially axially along the shaft axis. A pin, having first and second protrusions, is disposed adjacent to a bottom end of the movable shaft. A first detent plate is disposed on a first side of the movable shaft and includes at least a first slot that receives the first protrusion. A second detent plate is disposed on a second side of the moveable shaft and includes at least a second slot therein receiving the second protrusion. A first failure detection slot is associated with the first slot, permitting movement of the first protrusion therein in the absence of the second protrusion.

Growing community of inventors

Kirkland, Canada

Vlad Iliescu