The Boeing Company

Martin F Stephenson

Seiya Sakurai

Kevin W Beyer

James E Finnila

A hinged panel operation system is provided having a mechanical linkage assembly coupled between a fixed structure and a trailing edge device. The mechanical linkage assembly has a first link operatively coupled to the trailing edge device, a second link pivotably connected at a first end to the first link and pivotably connected at a second end to a third link, and an eccentric attachment connecting the second link to the third link. The hinged panel operation system further has a hinged panel positioned forward of the trailing edge device and being operatively coupled to the mechanical linkage assembly. The hinged panel is movable by the mechanical linkage assembly between a stowed position and a drooped position. The mechanical linkage assembly provides a load path to the hinged panel.

Hinged panel operation systems and methods

Flow body systems and associated methods, including aerospace vehicle control surface systems are disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. The at least one self-aligning mechanism can be positioned to allow the second flow body to rotate about the hinge line and the hinge axis.

Aerospace vehicle flow body systems and associated methods

Actuation and support mechanisms for wing trailing edge flap systems wherein each flap system has a streamwise or chordwise pair of geometrically similar flap support assemblies. Each of the flap support assemblies has a chordwise aligned cantilever support beam fixedly attached to wing structure. The beam incorporates multiple cam tracks for providing guidance and support to a movable dual carriage assembly upon which a wing trailing edge flap assembly is mounted. The dual carriage assembly comprises a fore-carriage which is articulatably connected to an aft-carriage. The wing trailing edge flap assembly is mounted upon the aft-carriage. Both the fore-carriage and the aft-carriage are individually supported by rollers constantly engaging a separate cam track for each of said carriages. For actuation of the dual carriage assembly and the wing trailing edge assembly mounted thereon, a ball screw drive mechanism is incorporated between the cantilever beam and the dual carriage assembly.

Wing trailing edge flap mechanism

A carrier unit for chordwise extending and rotatably positioning an auxiliary airfoil mounted adjacent to the trailing edge of a relatively fixed main airfoil of an airplane. When the auxiliary airfoil is in a fully retracted and stowed position, the actuation and positioning linkage mechanism of the carrier unit is completely housed within the combined auxiliary and main airfoil envelope with no external protrusions or fairings. For auxiliary airfoil extension, to increase the overall chord plane by approximately eight percent, a first set of four-bar linkages is utilized comprising: a beam member supported at a forward portion by a pair of approximately parallel links pivoted to wing structure and swingable chordwise in a generally parallel relationship for translatably shifting the auxiliary airfoil which is pivoted to a rearward portion of the beam member. For changing the auxiliary airfoil angle-of-incidence relative to the main airfoil, one or more sets of four-bar linkages are integrated with the first set for a unified rotation programming and extension drive that functions to produce an aerodynamic slot opening when the auxiliary airfoil is extended to takeoff and landing positions whereat it is deflected up to approximately forty degrees relative to the main airfoil reference chord plane. For an aerodynamic braking action during landing roll-out, the geometrical relationship of the sets of four-bar linkages functions to deflect the auxiliary airfoil chord plane greater than forty degrees, to approximately ninety degrees or more relative to the main airfoil reference chord plane.

Growing community of inventors

Sammamish, WA, United States of America

Martin F Stephenson