Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems (200) in accordance with some embodiments -include- a wing (210) having a trailing edge (211) , and a flap (220) positioned at least partially aft of the wing trailing edge (211) and being deployable relative to the wing (210) between a first flap position and a second flap position by operation of a first actuator. A spoiler (230) can be positioned at least proximate to the trailing edge (211) and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing (210) , a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator (231) can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap. independent of the motion of the flap.

Systems and methods for controlling aircraft flaps and spoilers

Trailing edge devices configured to carry out multiple functions, and associated methods of use and manufacture are disclosed An external fluid flow body (eg, an airfoil) configured in accordance with an embodiment of the invention includes a first portion and a second portion, at least a part of the second portion being positioned aft of the first portion, with the second portion being movable relative to the first portion between a neutral position, a plurality of upward positions, and a plurality of downward positions A guide structure can be coupled between the first and second portions, and an actuator can be operatively coupled between the first and second portions to move the second portion relative to the first portion In one embodiment, a flexible surface can track the motion of the second portion and can expose a gap at some positions In another embodiment, a controller can be coupled to the actuator and can be configured to direct the actuator to move the second portion to a high lift setting, a high drag setting, a roll setting, and a trim setting In yet another embodiment, trailing edge devices on an airfoil can have scaled, mechanically similar guide structures

Multi-function trailing edge devices and associated methods

A variable camber flap assembly having first and second operative positions. A rotatable drive arm powers first and second linkage subassemblies. The first linkage subassembly extends the flap panel in a downward and forward direction to its operative positions, and also rotates a hinged bullnose outwardly so as to foreshorten the distance between the leading and trailing edges of the flexible flap panel, increasing the camber of the flap. The second linkage subassembly cooperates with the first to angularly orientate the flap panel in its operative positions, and also positions the trailing edge of the panel relative to the leading edge of the airfoil. In the first operative position the trailing edge of the panel is spaced forwardly from the leading edge of the airfoil so as to form an aerodynamic slot; in the second operative position the flap panel is drawn rearwardly so that its trailing edge forms an aerodynamic seal with the airfoil.

Three-position variable camber krueger leading edge flap

Aircraft control surface operating systems and apparatuses, and associated methods of use. In one embodiment, an aircraft system includes an actuator operably coupled to a control surface in one-to-one correspondence. The actuator can include at least a first fluid port and a second fluid port. A first fluid circuit can be configured to provide pressurized working fluid from a fluid source to the first fluid port on the actuator to retract the actuator. A second fluid circuit can be configured to similarly provide pressurized working fluid from the fluid source to the second fluid port on the actuator to extend the actuator. The aircraft system can further include an accumulator configured to store pressurized working fluid for actuator operation in the event of a pressure drop in the fluid source.

Systems, apparatuses, and methods for moving aircraft control surfaces

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

An aircraft wing incorporates a leading edge flap which is retractable into an opening provided in the bottom surface of the wing. The flap is actuated by compact linkage which allows room for auxiliary equipment in the leading edge portion of the wing forward of the forwardmost main spar. The flap includes a surface panel having a rigid rear section which when retracted into the wing forms a part of the bottom airfoil surface of the wing and a flexible central section which when extended is curved to form a portion of the flap airfoil surface and when retracted is partially straightened out to conform to the contour of the bottom airfoil surface of the wing. A bullnose is pivotally mounted on rigid structure forming a part of the flap. When the flap is extended, the bullnose forms a downward and rearward extension of the flap airfoil surface. Upon retraction of the flap, the bullnose is folded inwardly to a tucked position above the flap and inside the wing. A link, interconnecting the bullnose and the central section of the flap surface panel, causes the central section to flex between its extended position and its retracted position responsive to movement of the bullnose.

Varnell L James

Papers

Leading edge flap