Abstract: A high-speed transport aircraft. In one embodiment, the aircraft includes a fuselage, delta wings, and integrated engine nacelles. The fuselage is configured to carry a payload and has a forward portion and an aft portion. The aft portion defines a generally constant-width planform and includes first, second, third, and fourth passenger seat sections, with each of the seat sections having at least two passenger seats positioned abreast at least generally normal to a longitudinal axis of the fuselage. In one aspect of this embodiment, the wings extend from the fuselage adjacent to the aft portion, and the fuselage further includes first and second rows of windows above the wings. The first row of windows are positioned in the fuselage directly adjacent the first seat section and the second row of windows are positioned in the fuselage directly adjacent the fourth seat section.

Abstract: A deployable receptacle includes a tray for supporting an object thereon and being movable between a storing position and a deploying position. The tray stores an object thereon when the tray is disposed in the storing position and deploys the object therefrom when the tray is disposed in the deploying position. A lever is coupled to the tray for moving the tray between the storing position and the deploying position.

Abstract: One advantageous embodiment of the present invention is an integrated transport system (14) for moving an object (20) in an aircraft (10) between a main cabin (16) and an overhead cabin (18) via a shaft (24) in connection therebetween. This integrated transport system (14) includes a single-unit gantry-lift device (42) with an object carrier (32) for receiving the object (20). This object carrier (32) has one or more restraint members (34, 38) for securing the object (20) in the object carrier (32) and preventing the object (20) from inadvertently tipping or falling out of the object carrier (32). In this embodiment, the single-unit gantry-lift device (42) further includes a lift device (46) for moving the object carrier (32) generally along a longitudinal axis (22) of the shaft (24) and a gantry device (44) for moving the object carrier (32) generally along a first axis (26) of the overhead cabin (18) and/or a second axis (28), which is disposed generally perpendicular to the first axis (26).

Abstract: One advantageous embodiment of the present invention is an integrated transport system (14) for moving an object (20) in an aircraft (10) between a main cabin (16) and an overhead cabin (18) via a shaft (24) in connection therebetween. This integrated transport system (14) includes a single-unit gantry-lift device (42) with an object carrier (32) for receiving the object (20). This object carrier (32) has one or more restraint members (34, 38) for securing the object (20) in the object carrier (32) and preventing the object (20) from inadvertently tipping or falling out of the object carrier (32). In this embodiment, the single-unit gantry-lift device (42) further includes a lift device (46) for moving the object carrier (32) generally along a longitudinal axis (22) of the shaft (24) and a gantry device (44) for moving the object carrier (32) generally along a first axis (26) of the overhead cabin (18) and/or a second axis (28), which is disposed generally perpendicular to the first axis (26).

Abstract: Derivative aircraft and methods for their manufacture. In one embodiment, a derivative aircraft having a derivative wing is derived from a baseline aircraft having a baseline wing. In one aspect of this embodiment, the baseline wing can include an outboard wing portion and an inboard wing portion, the inboard wing portion having a forward inboard wing portion and an aft inboard wing portion. In a further aspect of this embodiment, the derivative wing can include a wing insert having a spanwise wing insert portion and a chordwise wing insert portion, the chordwise wing insert portion of the wing insert being interposed between the forward inboard wing portion and the aft inboard wing portion of the baseline wing, and the spanwise wing insert portion being interposed between the outboard wing portion and the forward and aft inboard wing portions of the baseline wing.

Abstract: Derivative aircraft and methods for their manufacture. In one embodiment, a derivative aircraft having a derivative wing is derived from a baseline aircraft having a baseline wing. In one aspect of this embodiment, the baseline wing can include an outboard wing portion and an inboard wing portion, the inboard wing portion having a forward inboard wing portion and an aft inboard wing portion. In a further aspect of this embodiment, the derivative wing can include a wing insert having a spanwise wing insert portion and a chordwise wing insert portion, the chordwise wing insert portion of the wing insert being interposed between the forward inboard wing portion and the aft inboard wing portion of the baseline wing, and the spanwise wing insert portion being interposed between the outboard wing portion and the forward and aft inboard wing portions of the baseline wing.

Abstract: A turbofan jet engine having a housing and an engine core disposed in the housing. The engine core includes at least a compressor, turbine, and a drive shaft. The drive shaft defines a drive shaft axis. A plurality of fans are disposed in the housing and each is rotatable about a separate fan axis. Each of the fan axes are axially offset from the drive shaft axis. The turbofan jet engine further includes a drive system operably interconnecting the engine core and fans so as to rotatably drive the fans and selectively disengage select fans from the engine core.

Abstract: Derivative aircraft and methods for their manufacture. In one embodiment, a derivative aircraft having a derivative wing is derived from a baseline aircraft having a baseline wing. In one aspect of this embodiment, the baseline wing can include an outboard wing portion and an inboard wing portion, the inboard wing portion having a forward inboard wing portion and an aft inboard wing portion. In a further aspect of this embodiment, the derivative wing can include a wing insert having a spanwise wing insert portion and a chordwise wing insert portion, the chordwise wing insert portion of the wing insert being interposed between the forward inboard wing portion and the aft inboard wing portion of the baseline wing, and the spanwise wing insert portion being interposed between the outboard wing portion and the forward and aft inboard wing portions of the baseline wing.

Abstract: A turbofan jet engine having a housing and an engine core disposed in the housing. The engine core includes at least a compressor, turbine, and a drive shaft. The drive shaft defines a drive shaft axis. A plurality of fans are disposed in the housing and each is rotatable about a separate fan axis. Each of the fan axes are axially offset from the drive shaft axis. The turbofan jet engine further includes a drive system operably interconnecting the engine core and fans so as to rotatably drive the fans and selectively disengage select fans from the engine core.

Abstract: Derivative aircraft and methods for their manufacture. In one embodiment, a derivative aircraft having a derivative wing is derived from a baseline aircraft having a baseline wing. In one aspect of this embodiment, the baseline wing can include an outboard wing portion and an inboard wing portion, the inboard wing portion having a forward inboard wing portion and an aft inboard wing portion. In a further aspect of this embodiment, the derivative wing can include a wing insert having a spanwise wing insert portion and a chordwise wing insert portion, the chordwise wing insert portion of the wing insert being interposed between the forward inboard wing portion and the aft inboard wing portion of the baseline wing, and the spanwise wing insert portion being interposed between the outboard wing portion and the forward and aft inboard wing portions of the baseline wing.

Abstract: A high-speed transport aircraft. In one embodiment, the aircraft includes a fuselage, delta wings, and integrated engine nacelles. The fuselage is configured to carry a payload and has a forward portion and an aft portion. The aft portion defines a generally constant-width planform and includes first, second, third, and fourth passenger seat sections, with each of the seat sections having at least two passenger seats positioned abreast at least generally normal to a longitudinal axis of the fuselage. In one aspect of this embodiment, the wings extend from the fuselage adjacent to the aft portion, and the fuselage further includes first and second rows of windows above the wings. The first row of windows are positioned in the fuselage directly adjacent the first seat section and the second row of windows are positioned in the fuselage directly adjacent the fourth seat section.