Abstract: A pair of vortex generators are attached to the exterior surface of an aircraft and located forwardly of a flush inlet so as to effectively remove or reduce the thickness of a slower-moving boundary layer airflow ajdacent to the exterior aircraft surface and increase the mass airflow into the flush inlet. The pair of vortex generators induce higher mean total pressure airflow into the area between the vortex generators and downstream thereof and in front of to the flush inlet, thereby resulting in an increase in mass airflow into the flush inlet for a given inlet area.

Abstract: A folding chair assembly for dual use as a wheelchair or a flight attendant's seat onboard a commercial passenger airplane. The folding chair assembly can be manipulated into any of the following modes: (1) fully retracted into a compact assembly that can be stowably secured by a plurality of catches against a vertical wall in the passenger compartment of an aircraft; (2) with the chair assembly still secured to the wall, the seat pan is pulled down against a seat return spring and is usable as a flight attendant's seat; and (3) the folded chair assembly is completely detached from the plurality of retaining catches and fully extended to function as a wheelchair that is usable down the aisles of commercial passenger aircraft.

Abstract: Design and construction of a composite material airplane having a high aspect-ratio wing and a horizontal double-lobe fuselage cross-section for cargo and/or passenger accommodations. The fuselage comprises a double-lobe shell of contoured honeycomb core composite panels and an interior vertical plane centerline web forming a divider between the lobes. Piano-hinge type joints are utilized for multi-panel junctures to provide uniform load distribution across the junctures. The piano-hinge juncture utilizes hinge lugs which are dimensioned to interface sequentially along the hinge axis, and the hinge lugs are interconnected by a tubular hinge pin.

Abstract: An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics combined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aerodynamic control surfaces; and wherein, the redundancy is implemented through the division of the total aerodynamic surface area to be actuated into multi-segments, with each control segment having its own channel in the avionic control system. The avionic control system is effective in minimizing the effects of power actuated control loads reacting through aircraft structure by the incorporation of an electronic gain control power module which is positioned between the power output side of an actuator (e.g., an electro-mechanical or electro-hydraulic device) and the aerodynamic control surface or segment being actuated.

Abstract: A folding chair assembly for dual use as a wheelchair or a flight attendant's seat onboard a commercial passenger airplane. The folding chair assembly can be manipulated into any of the following modes: (1) fully retracted into a compact assembly that can be stowably secured by a plurality of catches against a vertical wall in the passenger compartment of an aircraft; (2) with the chair assembly still secured to the wall, the seat pan is pulled down against a seat return spring and is usable as a flight attendant's seat; and (3) the folded chair assembly is completely detached from the plurality of retaining catches and fully extended to function as a wheelchair that is usable down the aisles of commercial passenger aircraft.

Abstract: A wheelchair for transporting a physically handicapped person down the narrow aisle of a commercial passenger airplane. The wheelchair comprises a fixed back frame structure having a pair of rear caster wheels mounted to the lower end thereof and a pair of front wheels mounted on an extendable front wheel frame assembly which includes a foot rest member at the front end thereof. The rear caster wheels provide directional control.

Abstract: 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.

Abstract: An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics combined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aerodynamic control surfaces; and wherein, the redundancy is implemented through the division of the total aerodynamic surface area to be actuated into multi-segments, with each control segment having its own channel in the avionic control system. The avionic control system is effective in minimizing the effects of power actuated control loads reacting through aircraft structure by the incorporation of an electronic gain control power module which is positioned between the power output side of an actuator (e.g., an electro-mechanical or electro-hydraulic device) and the aerodynamic control surface or segment being actuated.

Abstract: A floor mounted power drive unit for moving containerized cargo or pallets within a cargo airplane; and the cargo drive unit generally comprises, a rotatable wheel or roller which is both steerable and retractable, and which is of modular construction for ease of insertion into a mounting opening in the floor of the cargo compartment with the only interface being a torque reaction means and an electrical connection.

Abstract: An inboard wing trailing edge flap of an aircraft has a flap carriage mechanism located within the fuselage or a fuselage/wing fairing structure, and the flap is attached to the carriage by a torque tube which penetrates the side of the fuselage. A slot is required in the fuselage through which the torque tube can travel as the flap is extended and retracted. The slot is covered when the flap is fully retracted, but when the flap is fully extended, airflow through the slot toward the upper surface of the flap causes the flap to lose lift. Therefore, airflow blocker doors are provided for closure of the slot when the flap is fully extended. The doors are held in a closed position by a pressure differential across the slot and by spring-loaded hinges; and the doors are adapted to be opened by engagement of a ramp cam member mounted to the flap torque tube, as the flap is retracted.

Abstract: A method for forming turbulators on scale model airplanes used in wind tunnel testing for accurately simulating a transition point on the model surface equivalent to that produced on the full scale airplane. The transition point is where the boundary layer airflow goes from a laminar airflow condition to a turbulent airflow condition. The method relates to applying a perforated tape mask (14) to the model surface (12) at a predetermined location and filling the perforations (15) with a fast cure epoxy (17). After the epoxy has cure hardened, the tape mask (14) is peeled off in the direction of the arrow (16), leaving a series of in situ formed disk turbulators (10) which function to produce the transition point on the model surface.

Abstract: An actuation and extension mechanism for aerodynamically high-lift devices such as a wing leading edge slat or a wing trailing edge flap; wherein an aerodynamic panel is connected to one end of an extendible track member that is supported and guided by its other end through rollers fixedly mounted to wing rib structure. The track member incorporates a separate rack gear segment internally thereof as part of the extension or retraction mechanism and this combination of track and gear segment provides the primary support and drive means to the high-lift device, without compromising the structural strength, safety, or operational reliability of said combination.

Abstract: An actuation and extension mechanism for aerodynamic high-lift devices such as a wing leading edge slat or a wing trailing edge flap; wherein an aerodynamic panel is connected to one end of an extendible track member that is supported and guided by its other end through rollers fixedly mounted to wing rib structure. The track member incorporates a cable and drum arrangement as part of the extension or retraction mechanism; and this combination of track, cable and drum provides the primary support and drive means for the high-lift device without compromising the structural strength or the stress safety of said combination.

Abstract: A wing leading edge slat actuation and positioning system, wherein a slat panel is connected to one end of an extensible track member which is supported and guided at its other end, by rollers mounted to fixed structure in the leading edge section of the wing. The actuation and positioning system comprises a unified drive and a programming mechanism which is connected to the slat panel and functions to combine an aerodynamic slot opening or closure operation with a slat extension drive mechanism. The unified drive and programming mechanism comprises a contoured camtrack somewhat in the shape of an S-camtrack and having a roller follower which is connected to a link and drive arm; and this combination allows synchronization of slat actuation with programming control of slat angle-of-deflection and aerodynamic slot opening or closure.

Abstract: A hinge mechanism for a door on an overhead baggage compartment which is generally located in the passenger section of an airliner and utilized by passengers for the stowage of carry-on luggage. The door hinge mechanism comprises, an unequal length four-bar linkage mechanism which produces a compound motion to the door for swinging it into the standing room area of the passenger section when it is moved to the open position. An ordinary four-bar linkage mechanism would have two pairs of equal length links and their operation would be designed around two fixed pivot points. However, in this disclosure there is only one fixed pivot point and the other of the generally fixed pivots, is a walking pivot which is guided by a cam device to profile the travel of the door.

Abstract: A hinge mechanism for an overhead baggage compartment which is generally located in the passenger section of an airliner. The hinge mechanism comprises, a dual-cam guided four-bar linkage mechanism which produces a compound motion to the door for retraction through a relatively narrow horizontal opening into an area above the baggage compartment. Ordinarily, a four-bar linkage mechanism would have its operation designed around two fixed pivot points; however, in this disclosure there is only one fixed pivot point and the other of said pivots is a walking pivot which is guided by a dual-cam device for profiling the travel of the door.

Abstract: An airfoil having a trailing edge flap assembly comprising a flap member which in its stowed position is located above a fixed mounting structure. There is a rear pivot link connected at its lower end to the mounting structure and by its upper end to an aft portion of the flap. There is a forward slideway by which the forward part of the flap is mounted for longitudinal slide motion relative to the fixed mounting structure. The flap has a stowed position in the rear portion of the wing, and is movable rearwardly with substantial Fowler motion to an intermediate position for take-off, and movable further rearwardly to a fully extended position where the flap extends rearwardly and downwardly for take-off.