Abstract: A vertical takeoff and landing aircraft includes a pair of ducted lift/thrust fans that are rotatably movable between a first vertical lift position and a second horizontal thrust position. The lift/thrust fans are disposed within curvilinear fan recesses formed within leading edge portions of the aircraft's wings. A downwardly exhausting, ducted lift fan is disposed within the aircraft's fuselage, aft of the aircraft's pitch axis. A power plant, disposed within the fuselage, is coupled with the lift/thrust fans and the lift fan by a transmission system. The lift/thrust fans and lift fan are positioned with respect to one another to be triangulated about the aircraft's center of gravity and the aircraft's center of lift.

Abstract: A vertical takeoff and landing aircraft includes a pair of ducted lift/thrust fans that are rotatably movable between a first vertical lift position and a second horizontal thrust position. The lift/thrust fans are disposed within curvilinear fan recesses formed within leading edge portions of the aircraft's wings. A downwardly exhausting, ducted lift fan is disposed within the aircraft's fuselage, aft of the aircraft's pitch axis. A power plant, disposed within the fuselage, is coupled with the lift/thrust fans and the lift fan by a transmission system. The lift/thrust fans and lift fan are positioned with respect to one another to be triangulated about the aircraft's center of gravity and the aircraft's center of lift.

Abstract: The invention relates to systems and methods for manufacturing composite parts for aircraft. In one innovative aspect, a system and method for adjusting a location of a center of gravity of an aircraft relative to a center of lift of a wing of the aircraft is disclosed, wherein a modular spar tunnel mold is provided and configured to be detachably fixed at a plurality of selected locations within a main mold for a fuselage portion of the aircraft. In another innovative aspect, a movable detail or mold is used for manufacturing complex composite parts for an aircraft. In yet another innovative aspect, a movable detail is used to fabricate a common feature for a plurality of different parts for one or more aircraft or a family of aircraft of similar design.

Abstract: A hybrid composite-metal energy absorbing seat is described. According to one embodiment, an aircraft seat includes a seat base assembly and a seat back assembly. The seat base assembly includes multiple rigid metal seat base side frame elements joined by a lower seat pan, an energy absorbing element placed on the lower seat pan to deform and absorb downward energy in a crash, and a contoured seat pan whose sides extend past the seat base side frame elements and deform to absorb downward energy in a crash. The seat back assembly is attached to the seat base assembly and includes multiple rigid metal seat back side frame elements joined by a contoured composite seat back. The rigid metal seat back side frame elements absorb forward crash load energy by permanently deforming during a severe forward crash load. The contoured composite seat back provides design/aesthetic flexibility.

Abstract: A hybrid composite-metal energy absorbing seat is described. According to one embodiment, an aircraft seat includes a seat base assembly and a seat back assembly. The seat base assembly includes multiple rigid metal seat base side frame elements joined by a lower seat pan, an energy absorbing element placed on the lower seat pan to deform and absorb downward energy in a crash, and a contoured seat pan whose sides extend past the seat base side frame elements and deform to absorb downward energy in a crash. The seat back assembly is attached to the seat base assembly and includes multiple rigid metal seat back side frame elements joined by a contoured composite seat back. The rigid metal seat back side frame elements absorb forward crash load energy by permanently deforming during a severe forward crash load. The contoured composite seat back provides design/aesthetic flexibility.

Abstract: A system and method for adjusting a location of a center of gravity of an aircraft relative to a center of lift of a wing of the aircraft. In one innovative aspect, a modular spar tunnel mold is provided and configured to be detachably fixed at a selected location within a main mold for a fuselage portion of the aircraft.

Abstract: A system and method for adjusting a location of a center of gravity of an aircraft relative to a center of lift of awing of the aircraft. In one innovative aspect, a modular spar tunnel mold is provided and configured to be detachably fixed at a selected location within a main for a fuselage portion of the aircraft.