Abstract: An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing. The aircraft includes leading edge root extensions mounted to the fixed wing and the fuselage at a leading edge of the fixed wing, at least one dynamic slat mounted to a leading edge of the wing structure, and a chine formed in the fuselage along lateral sides thereof at a nose of the aircraft.

Abstract: An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing. The aircraft includes leading edge root extensions mounted to the fixed wing and the fuselage at a leading edge of the fixed wing, at least one dynamic slat mounted to a leading edge of the wing structure, and a chine formed in the fuselage along lateral sides thereof at a nose of the aircraft.

Abstract: An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing.

Abstract: Some apparatus embodiments include an aircraft having a hybrid parallel electric propulsion system including two internal combustion engines and an electric propulsion system including two electric motors electrically connected to an electric power module. The electric power module is optionally configured for attachment to a bottom side of a fuselage. Each of the electric motors attaches to an aircraft wing outboard of the nearest internal combustion engine. The electric motors and internal combustion engines are operable independently of one another, providing for propulsion by the electric motors during flight and ground operations when the internal combustion engines may operate inefficiently. Some embodiments are implemented as a hybrid parallel electric propulsion retrofit package for adding an electric propulsion system to an aircraft previously equipped only with internal combustion engines.

Abstract: An aircraft fuselage includes a stretched-quadrant fuselage segment having from to four stretched-quadrant fuselage projections spaced at intervals around the fuselage. The stretched-quadrant fuselage segment enables an aircraft to be configured for three-across seating rows and for carrying an LD-3 unit load device inside the fuselage with the seats removed.

Abstract: An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing.

Abstract: Some apparatus embodiments include an aircraft having a hybrid parallel electric propulsion system including two internal combustion engines and an electric propulsion system including two electric motors electrically connected to an electric power module. The electric power module is optionally configured for attachment to a bottom side of a fuselage. Each of the electric motors attaches to an aircraft wing outboard of the nearest internal combustion engine. The electric motors and internal combustion engines are operable independently of one another, providing for propulsion by the electric motors during flight and ground operations when the internal combustion engines may operate inefficiently. Some embodiments are implemented as a hybrid parallel electric propulsion retrofit package for adding an electric propulsion system to an aircraft previously equipped only with internal combustion engines.

Abstract: An aircraft fuselage includes a stretched-quadrant fuselage segment having from to four stretched-quadrant fuselage projections spaced at intervals around the fuselage. The stretched-quadrant fuselage segment enables an aircraft to be configured for three-across seating rows and for carrying an LD-3 unit load device inside the fuselage with the seats removed.

Abstract: An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing. The aircraft includes leading edge root extensions mounted to the fixed wing and the fuselage at a leading edge of the fixed wing, at least one dynamic slat mounted to a leading edge of the wing structure, and a chine formed in the fuselage along lateral sides thereof at a nose of the aircraft.