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 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

Methods and apparatuses for controlling airflow with a leading edge device having a flexible flow surface. In one embodiment, the airfoil includes a first portion having a first flow surface and a second flow surface facing opposite from the first flow surface. The second portion of the airfoil has a leading edge and is movably coupled to the first position. The second portion can move between a first position and a second position offset from the first position by an angle of from about 45° to about 90° or more. The second portion includes a flexible flow surface having a first shape when the second portion is in the first position and a second shape different than the first shape when the second portion is in the second position. A guide structure can be coupled between the first portion and the second portion. In another embodiment, the airfoil can have inbound and outbound leading edge portions with an inbound guide structure having a first mechanical arrangement and an outbound guide structure having a second mechanical arrangement different than the first.

Method and apparatus for controlling airflow with a leading edge device having a flexible flow surface

A slot forming segment is inserted between two portions of a wing, which are adjacent along a longitudinal axis of wing, into a cove of a carved trailing edge of a leading portion of the adjacent portions and pivotal relatively to both adjacent portions of the wing between which it is inserted. The slot forming segment has such a shape and a position of its axis of rotation that by deflecting it downwardly relatively to the leading portion, it is formed a slot inside the wing's structure of large inlet cross section and high convergence ratio for the control of the boundary layer over an upper surface of the wing behind the slot forming segment for the need of extra lift production. Simultaneously, it is increased both a camber and an aerodynamic surface area of a following portion of the adjacent portions whereby additionally increasing the extra lift production on the wing. A slot changing spoiler is inserted directly in front of and above the slot forming segment and has such a shape of its undersurface and a position of its axis of rotation that a camber of an upper surface of the wing and the convergence ratio of the slot is changed by the simultaneous rotation of the slot changing spoiler and the slot forming segment in the opposite direction whereby increasing the rate of change of lift on the wing for the efficient maneuver of an aircraft at low speeds of flight.

Slot forming segments and slot changing spoilers

An airfoil is specified with a double slotted leading edge flap having two members and adapted to be used together with a multislotted trailing edge flap. The leading edge flap uses two slots for landing and one or no slots for take off. The rear leading edge member defines a slot substantially downstream of the cruise leading edge. Ahead of the trailing edge flap slot, there is provided a special slot across the wing''s surface in special cooperation with a spoiler. The airfoil surface between the downstream slot of the leading edge flap and the special slot near the trailing edge flap is short and with negligible camber. Special consideration is given to wing torsion, fuel volume, number of slots, and effect of varying airfoil thickness on flap geometric and aerodynamic parameters.

Alberto Alvarez Calderon

Papers

Variable camber multi-slotted flaps