A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line The first and second supply lines are connected to a source of hydraulic fluid At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface A flow control assembly is connected to the return line and to at least one of the first and second supply lines A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly It is emphasized that this abstract is provided to comply with the rules requiring an abstract It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims (37 CFR §172(b))

Aircraft control surface drive system and associated methods

The present invention relates to a variable camber wing mechanism. The mechanism includes a main wing, a slat member connected by swing arm members to the main wing, slots in the leading edge of the main wing for the swing arms to pass through, and a shutter member for sealing the slot around each swing arm member by means of a sliding movement parallel to the leading edge. This sealing of the slots prevents ingress of ice and water into the main wing.

Variable camber wing mechanism

The present invention is directed generally toward leading edge flap apparatuses and corresponding methods One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path

Leading Edge Flap Apparatuses and Associated Methods

Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.

Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods

Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly (120) that in turn includes a deployable leading edge panel (121) having a generally fixed-shape flow surface, a bullnose (123) coupled to the panel,, and a link mechanism (130) coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism includes a first support link (131), a second support link (132), and first (133), second (134), and third (135) positioning links. The positioning links are pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link so that the leading edge panel forms a gap (101) with the airfoil when in the deployed position. The positioning links are the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.

Link mechanisms for gapped rigid krueger flaps, and associated systems and methods

A deployment mechanism employing multiple, nonproportional, four-bar linkages for guiding the movement of an airfoil control surface. The linkages are connected at one of their ends to the airfoil control surface and at their other end to an airfoil. The connection points of each linkage to the airfoil define a set of lines which are skewed at progressively greater angles with respect to a reference line. The mechanism when activated guides the extension of the control surface into an overlapping position with the airfoil. The overlap forms a nozzle between the airfoil control surface and the airfoil surface. The amount of overlap at any point is a constant percentage of the airfoil chord length at that same point.

Bennett D

Papers

Control surface deployment mechanism