Bombardier Inc.

Safran Landing Systems Canada Inc./safran Systemes D'atterrissage Canada Inc.

Learjet Inc.

Howard Ian Smith

Thomas Hanson

Dmitry Budnitsky

Iyad Akel

Marin Besliu

Chris Bryant

Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap along an elongated track member as the trailing edge flap moves toward the deployed position; guiding a forward portion of the trailing edge flap along the elongated track member as the trailing edge flap moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap relative to the elongated track member.

Assemblies and methods for deploying a trailing edge flap of an aircraft

Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

Methods and systems for deploying adjacent trailing edge flaps

Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap () along an elongated track member (C) as the trailing edge flap () moves toward the deployed position; guiding a forward portion of the trailing edge flap (28) along the elongated track member (C) as the trailing edge flap () moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap () relative to the elongated track member (C).

Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.

Growing community of inventors

Niagara Falls, Canada

Howard Ian Smith