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US 12,576,966 B1Granted
Supersonic aircraft
AssigneePivotal Supersonic Inc.
InventorSteven S. Ogg
Life of this patent
Estimating the term…
Abstract
A supersonic aircraft is disclosed herein. The supersonic aircraft comprises one or more fuselages, one or more wings, at least one wing-mounted engine, at least one inlet mounted on the upper surface of or above the wing, an upper wing surface propulsion system fairing, and a lower wing surface propulsion system fairing or lower wing surface modification to account for the presence of the engine.
Claims15
An aircraft capable of level supersonic flight comprising:
- a wing;
- and
- a lower wing surface propulsion system fairing;
- and
- a wing-mounted propulsion system comprising an inlet, and an engine comprising a plurality of rotating turbomachinery components;
- and
- wherein the inlet is configured to obtain a majority of its air from above the wing at all flight conditions, and the inlet is located aft of a leading edge of the wing at the range of spanwise locations encompassing those of the wing-mounted propulsion system;
- and
- wherein the rotating turbomachinery comprises a component with a maximum diameter, and
- wherein with the aircraft configured to be self-supporting with the landing gear down on a horizontal surface, the maximum diameter component is located vertically (Z-axis) such that the lowest point of the maximum diameter component or most forward maximum diameter component if there is more than one component with the maximum diameter, is located below a line that is a linear interpolation between a plurality of points on an upper surface of the wing that are immediately inboard and immediately outboard of the wing-mounted propulsion system excluding any wing-to-nacelle fillets at the most forward body station (X-axis) of the maximum diameter turbomachinery component and at the spanwise location (Y-axis) of the lowest point on the maximum diameter turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter, by an amount no less than 14.0% of the diameter of the maximum diameter turbomachinery component;
- and
- wherein the underwing propulsion system fairing extends forward of the largest diameter rotating turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter by an amount greater than 50% of the diameter of the maximum diameter turbomachinery component.
9 more elements
An aircraft capable of level supersonic flight comprising:
- a wing capable of variable sweep;
- and
- a lower wing surface propulsion system fairing;
- and
- a wing-mounted propulsion system comprising an inlet, and an engine comprising a plurality of rotating turbomachinery components;
- and
- wherein the inlet is configured to obtain a majority of its air from above the wing at all flight conditions, and the inlet is located aft of a leading edge of the wing at the range of spanwise locations encompassing those of the wing-mounted propulsion system;
- and
- wherein the rotating turbomachinery comprises a component with a maximum diameter, and
- wherein with the aircraft configured to be self-supporting with the landing gear down on a horizontal surface, the maximum diameter component is located vertically (Z-axis) such that the lowest point of the maximum diameter component or most forward maximum diameter component if there is more than one component with the maximum diameter, is located below a line that is a linear interpolation between a plurality of points on an upper surface of the wing that are immediately inboard and immediately outboard of the wing-mounted propulsion system excluding any wing-to-nacelle fillets at the most forward body station (X-axis) of the maximum diameter turbomachinery component and at the spanwise location (Y-axis) of the lowest point on the maximum diameter turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter, by an amount no less than 14.0% of the diameter of the maximum diameter turbomachinery component;
- and
- wherein the underwing propulsion system fairing extends forward of the largest diameter rotating turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter by an amount greater than 50% of the diameter of the maximum diameter turbomachinery component.
9 more elements
An aircraft capable of level supersonic flight comprising:
- a wing;
- and
- a lower wing surface propulsion system fairing;
- and
- a wing-mounted propulsion system comprising an inlet, and an engine comprising a plurality of rotating turbomachinery components;
- and
- wherein the inlet is configured to obtain a majority of its air from above the wing at all flight conditions, and the inlet is located aft of a leading edge of the wing at the range of spanwise locations encompassing those of the wing-mounted propulsion system;
- and
- wherein the rotating turbomachinery comprises a component with a maximum diameter, and
- wherein with the aircraft configured to be self-supporting with the landing gear down on a horizontal surface, the maximum diameter component is located vertically (Z-axis) such that the lowest point of the maximum diameter component or most forward maximum diameter component if there is more than one component with the maximum diameter, is located below a line that is a linear interpolation between a plurality of points on an upper surface of the wing that are immediately inboard and immediately outboard of the wing-mounted propulsion system excluding any wing-to-nacelle fillets at the most forward body station (X-axis) of the maximum diameter turbomachinery component and at the spanwise location (Y-axis) of the lowest point on the maximum diameter turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter, by an amount no less than 14.0% of the diameter of the maximum diameter turbomachinery component;
- and
- wherein the underwing propulsion system fairing extends forward of the most forward rotating turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter by an amount greater than 50% of the diameter of the maximum diameter turbomachinery component;
- and
- wherein the ratio of the cross-sectional area of the wing covered by the fan to the fan total frontal area at the body station of the largest diameter turbomachinery component, Aratio, is greater than 8.0%.
11 more elements
An aircraft capable of level supersonic flight comprising:
- a wing capable of variable sweep;
- and
- a lower wing surface propulsion system fairing;
- and
- a wing-mounted propulsion system comprising an inlet, and an engine comprising a plurality of rotating turbomachinery components;
- and
- wherein the inlet is configured to obtain a majority of its air from above the wing at all flight conditions, and the inlet is located aft of a leading edge of the wing at the range of spanwise locations encompassing those of the wing-mounted propulsion system;
- and
- wherein the rotating turbomachinery comprises a component with a maximum diameter, and
- wherein with the aircraft configured to be self-supporting with the landing gear down on a horizontal surface, the maximum diameter component is located vertically (Z-axis) such that the lowest point of the maximum diameter turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter, is located below a line that is a linear interpolation between a plurality of points on an upper surface of the wing that are immediately inboard and immediately outboard of the wing-mounted propulsion system excluding any wing-to-nacelle fillets at the most forward body station (X-axis) of the maximum diameter turbomachinery component and at the spanwise location (Y-axis) of the lowest point on the maximum diameter turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter, by an amount no less than 14.0% of the diameter of the maximum diameter turbomachinery component;
- and
- wherein the underwing propulsion system fairing extends forward of the largest diameter rotating turbomachinery component or most forward maximum diameter component if there is more than one component with the maximum diameter by an amount greater than 50% of the diameter of the maximum diameter turbomachinery component;
- and
- wherein the ratio of the cross-sectional area of the wing covered by the fan to the fan total frontal area at the body station of the largest diameter turbomachinery component, Aratio, is greater than 8.0%.
11 more elements
Dependencies are inferred from the claim text.