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

A wing leading edge high-lift generating device in the form of a spanwise slat segment having both an upper and a lower surface, faired into an airfoil configured leading edge of a relatively stationary portion of the wing therebehind and movable with respect thereto by a downwardly extending hinge arm pivotally related to a downwardly extending hinge bracket from the wing within a fairing structure which also includes an actuator between the hinge arm and bracket for biasing the hinge arm connected to the leading edge device away from and downwardly with respect to the hinge bracket of the wing about the pivotal connection therewith. Further, the wing leading edge slat device has a large cavity formed between the upper and lower surfaces thereof, which cavity is readily adaptable for the insertion of a large duct for blowing pressurized air through a nozzle and an aerodynamic slot formed between the leading edge slat and the relatively stationary airfoil configured leading edge of the wing therebehind when the leading edge slat is moved outwardly and downwardly. In another embodiment the leading edge slat has its movement guided by an extendable track.

Wing leading edge high lift device

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

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

A leading edge device (referred to as a foreflap) is formed by passing a curved parting line through an airfoil in such a manner as to allow the front part of the airfoil to rotate about a pivot which is close to the wing external contour. When the foreflap is thus extended, the resulting airfoil contour has a large bulbous nose which is formed mainly by the parting line. The exact contour of the resulting nose may be shaped to optimum aerodynamic contour for high lift operation without adversely affecting high speed performance, since the parting surface is inside of the clean airfoil when the foreflap is retracted. The foreflap may be operated by any conventional means, e.g., a simple hinge located at the pivot outside of the airfoil contour.

A Robertson

Papers

Airfoil with extendible and retractable leading edge