Abstract: In an example, method for locking/unlocking a structure is described. The method includes attaching a first end of a pawl to a support assembly, wherein the pawl comprises a shape memory alloy (SMA) element configured to transition between a first configuration and a second configuration, and wherein the pawl is attached to the support assembly such that a second end of the pawl is movable between a locked position that prevents a rotatable shaft from rotating and an unlocked position that allows the rotatable shaft to rotate, activating the SMA element, thereby causing the SMA element to take on the first configuration and move the second end of the pawl to the locked position, and deactivating the SMA element, thereby causing the SMA element to take on the second configuration and move the second end of the pawl from the locked position to the unlocked position.

Abstract: In an example, method for locking/unlocking a structure is described. The method includes attaching a first end of a pawl to a support assembly, wherein the pawl comprises a shape memory alloy (SMA) element configured to transition between a first configuration and a second configuration, and wherein the pawl is attached to the support assembly such that a second end of the pawl is movable between a locked position that prevents a rotatable shaft from rotating and an unlocked position that allows the rotatable shaft to rotate, activating the SMA element, thereby causing the SMA element to take on the first configuration and move the second end of the pawl to the locked position, and deactivating the SMA element, thereby causing the SMA element to take on the second configuration and move the second end of the pawl from the locked position to the unlocked position.

Abstract: A method and apparatus for dampening a structure in an aircraft. The apparatus comprises a housing, a first compartment located along an axis extending centrally through the housing, a second compartment located adjacent to the first compartment on the axis extending centrally through the housing, a first piston, a rod, and a second piston. The housing has an elongate shape. The first piston is located within the first compartment of the housing. The first piston defines a first chamber and a second chamber of the first compartment as the first piston moves within the housing. The rod is associated with the first piston and extends centrally through the first compartment and the second compartment. The second piston is coaxial to the first piston and located within the second compartment. The second piston moves relative to the rod to accommodate a flow of a fluid into the second compartment.

Abstract: A method and apparatus for dampening a structure in an aircraft. The apparatus comprises a housing, a first compartment located along an axis extending centrally through the housing, a second compartment located adjacent to the first compartment on the axis extending centrally through the housing, a first piston, a rod, and a second piston. The housing has an elongate shape. The first piston is located within the first compartment of the housing. The first piston defines a first chamber and a second chamber of the first compartment as the first piston moves within the housing. The rod is associated with the first piston and extends centrally through the first compartment and the second compartment. The second piston is coaxial to the first piston and located within the second compartment. The second piston moves relative to the rod to accommodate a flow of a fluid into the second compartment.