US 12,735,168 B2 · Aircraft design and technology

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.

Claims19

Dependent claims

A method of operating an aircraft, comprising:

providing an aircraft having a fuselage, a swept wing extending laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage, at least one vertical tail surface extending upward from the fuselage, a dynamic slat attached to a leading edge of the wing, and first and second turbine engines mounted to the fuselage at locations positioned vertically below the wing, the aircraft having a maximum take-off weight, and the turbine engines providing a maximum continuous thrust;
operating the aircraft with:
a maximum continuous thrust to maximum take-off weight ratio in the range of 0.5 to 0.6;
sustained turns in the range of about 6.5 G to about 7.5 G;
and
angle of attack of at least 25°;
and
providing leading edge root extensions mounted to the wing and the fuselage at the leading edge of the wing, the leading edge root extensions having a planform area ratio relative to a planform area of the wing in the range of about 0.1% to about 5%.

5 more elements

A method of operating an aircraft, comprising:

providing an aircraft having a fuselage, a swept wing extending laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage, at least one vertical tail surface extending upward from the fuselage, a dynamic slat attached to a leading edge of the wing, first and second turbine engines mounted to the fuselage at locations positioned vertically below the wing, and leading edge root extensions mounted to the wing and the fuselage at the leading edge of the wing, the aircraft having a maximum take-off weight, the turbine engines providing a maximum continuous thrust, the leading edge root extensions having a planform area ratio relative to a planform area of the wing in the range of about 0.1% to about 5%;
creating lifting vortex flow with the leading-edge root extensions at angles of attack of at least about 25°;
and
operating the aircraft with:
a maximum continuous thrust to maximum take-off weight ratio in the range of 0.5 to 0.6;
sustained turns in the range of about 6.5 G to about 7.5 G;
and
angle of attack of at least 25°.

5 more elements

A method of operating an aircraft, comprising:

providing an aircraft having a fuselage, a swept wing extending laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage, at least one vertical tail surface extending upward from the fuselage, a dynamic slat attached to a leading edge of the wing, first and second turbine engines mounted to the fuselage at locations positioned vertically below the wing, leading edge root extensions mounted to the wing and the fuselage at the leading edge of the wing, a nose chine formed in the fuselage along lateral sides thereof at a nose of the aircraft, the nose chine extending at least partially forward of a canopy and terminating forward of the wing, the turbine engines providing a maximum continuous thrust, the leading edge root extensions having a planform area ratio relative to a planform area of the wing in the range of about 0.1% to about 5%, the turbine engines each generate maximum continuous thrust in the range of about 3,200 lbf to about 4,000 lbf., and the aircraft has an empty weight in the range of about 9,000 lbs. to about 10,000 lbs. and a maximum loaded weight in the range of about 12,000 lbs. to about 14,000 lbs.;
creating lifting vortex flow with the leading-edge root extensions at angles of attack of at least about 25°;
moving the dynamic slat between a retracted position and at least one extended position to facilitate operating the aircraft at an angle of attack of at least 25°, the dynamic slat exposing a gap between the leading edge of the wing and a fixed portion of the wing in the at least one extended position;
shedding air vortices with the nose chine at angles of attack of at least about 25° to increase yaw stability of the aircraft;
operating the aircraft with:
a maximum continuous thrust to maximum take-off weight ratio in the range of 0.5 to 0.6;
sustained turns in the range of about 6.5 G to about 7.5 G;
and
the angle of attack of at least 25°.

6 more elements

Dependencies are inferred from the claim text.

Aircraft design and technology

Life of this patent

Aircraft design and technology

Life of this patent

Abstract

Claims19