An aircraft configuration that may reduce the level of roaring jet exhaust noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. The aircraft's nacelles are mounted to the aircraft higher than the wings, with substantially vertical stab
An aircraft configuration that may reduce the level of roaring jet exhaust noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. The aircraft's nacelles are mounted to the aircraft higher than the wings, with substantially vertical stabilizers outboard of the outermost engine. Noise shifting means are provided such as, for each nacelle, primary chevrons at the core nozzle, secondary chevrons at the fan nozzle, a partial bypass mixer, a long duct full flow mixer, or a combination thereof to provide a shift in spectrum distribution of jet exhaust noise from lower to higher frequency. Variable geometry chevrons may be used with increased immersion to provide such a shift just during noise-restricted portions of an aircraft flight profile. The aircraft aerodynamic structural surfaces serve as noise shielding barriers that more effectively block or redirect the frequency shifted noise up and away from communities.
대표청구항▼
1. A non-blended wing body aircraft comprising: a tubular fuselage;two wings with two wing strakes mounted to the tubular fuselage, the wings and strakes in a substantially delta wing configuration and each including a leading edge and a top surface, the wings each including a trailing edge;a plural
1. A non-blended wing body aircraft comprising: a tubular fuselage;two wings with two wing strakes mounted to the tubular fuselage, the wings and strakes in a substantially delta wing configuration and each including a leading edge and a top surface, the wings each including a trailing edge;a plurality of nacelles mounted to the fuselage and having a leading end, a top, a bottom, and a longitudinal axis, each nacelle including a turbofan engine, a fan nozzle having a diameter, and a core nozzle, wherein each nacelle is completely and directly above the respective wing, strake, or a combination thereof;a substantially vertical stabilizer mounted on each wing outboard of each respective outermost nacelle at a mounting location;a split aft deck including a trailing edge and a multi-element upwardly rotatable pitch control surface including a trailing edge at the trailing edge of the deck, andnoise shifting means associated with the core nozzle, the fan nozzle, or a combination thereof, of each nacelle,wherein the mounting location of each substantially vertical stabilizer to the respective wing is lower than the bottom of the respective outermost nacelle and each substantially vertical stabilizer extends at least as high as the top of the respective outermost nacelle,wherein the leading edge of each strake or wing, as applicable, extends forward of the respective nacelle leading end along the longitudinal axis of that nacelle at least a distance as great as the distance from the top surface of the respective wing to the top of the respective nacelle,wherein the trailing edge of the aft deck extends aft of the respective nacelle fan nozzle along the longitudinal axis of that nacelle at least a distance as great as the distance from the top surface of the respective wing to the top of the respective nacelle,wherein the fuselage extends between the nacelles and there is no central vertical stabilizer between the nacelles. 2. The aircraft of claim 1, wherein the noise shifting means includes variable geometry chevrons as primary chevrons at the core nozzle, variable geometry chevrons as secondary chevrons at the fan nozzle, or a combination thereof, wherein the variable geometry chevrons each include a free end with a tip, and wherein the tips of the variable geometry chevrons have a fully immersed position towards the longitudinal axis of the nacelle of between approximately 1.5 inches to approximately 2 inches from the fan nozzle. 3. The aircraft of claim 1, wherein the noise shifting means comprises chevrons mounted to or integrated with the core nozzle. 4. The aircraft of claim 1, wherein the noise shifting means comprises a partial bypass mixer at the core nozzle. 5. The aircraft of claim 1, wherein the noise shifting means comprises a long duct full flow mixer at the core nozzle. 6. The aircraft of claim 1, wherein the distance from the fan nozzle to the trailing end of the upwardly rotatable pitch control surface, when the upwardly rotatable pitch control surface is in the same plane as the aft deck, is greater than approximately two fan nozzle diameters. 7. The aircraft of claim 1, wherein the noise shifting means comprise primary chevrons at the core nozzle and secondary chevrons at the fan nozzle, wherein the angular orientation of the primary chevrons and the secondary chevrons is such that the tips of more than one primary chevron are aligned with the tips of more than one secondary chevron, and the valleys of more than one primary chevron are aligned with the valleys of more than one secondary chevron. 8. The aircraft of claim 1, wherein the noise shifting means comprise a lobed mixer at the core nozzle and secondary chevrons at the fan nozzle, wherein the angular orientation of the lobes of the mixer and the secondary chevrons is such that the tips of more than one lobe are aligned with the tips of more than one secondary chevron, and the valleys of more than one primary chevron are aligned with the valleys of more than one secondary chevron. 9. The aircraft of claim 1, wherein the substantially vertical stabilizers are canted outboard by approximately 5 degrees to approximately 10 degrees off of a plane perpendicular with the top surface of the aft deck. 10. The aircraft of claim 1, wherein the noise shifting means comprises secondary chevrons mounted to or integrated with the fan nozzle. 11. The aircraft of claim 10, wherein the secondary chevrons are un-actuated, fixed position chevrons. 12. The aircraft of claim 10, wherein the secondary chevrons are variable geometry chevrons. 13. The aircraft of claim 1, wherein the noise shifting means includes variable geometry chevrons as primary chevrons at the core nozzle, variable geometry chevrons as secondary chevrons at the fan nozzle, or a combination thereof, wherein the variable geometry chevrons each include a free end with a tip, and wherein the tips of the variable geometry chevrons have a fully immersed position towards the longitudinal axis of the nacelle of up to approximately 2 inches from the fan nozzle. 14. The aircraft of claim 13, wherein the deepest immersion of variable geometry chevrons towards the longitudinal axis occurs at approximately 4,000 feet altitude or lower. 15. The aircraft of claim 13, wherein the immersion is eliminated gradually from take-off to when the aircraft is approximately 10,000 feet above nearest ground. 16. The aircraft of claim 1, wherein the distance from the fan nozzle to the trailing end of the upwardly rotatable pitch control surface, when the upwardly rotatable pitch control surface is in the same plane as the aft deck, is between approximately two and a half and approximately three and a half fan nozzle diameters. 17. The aircraft of claim 16, wherein shielding of noise emitted towards the ground from the aircraft in flight for frequency bands 33 and higher results in approximately 10 db or more attenuation. 18. A method of making a non-blended wing body aircraft with reduced aircraft noise, infrared radiation, or sonic boom, or a combination thereof, emitted towards the ground from the aircraft in flight, the method comprising: providing a tubular fuselage;mounting two wings with two wing strakes to the fuselage, the wings and strakes in a substantially delta wing configuration and each including a leading edge and a top surface, the wings each including a trailing edge;mounting a plurality of nacelles to the fuselage and having a leading end, a top, a bottom, and a longitudinal axis, each nacelle including a turbofan engine, a fan nozzle having a diameter, and a core nozzle, wherein each nacelle is completely and directly above the respective wing, strake, or a combination thereof;mounting a substantially vertical stabilizer on each wing outboard of each respective outermost nacelle at a mounting location;providing a split aft deck including a trailing edge and a multi-element upwardly rotatable pitch control surface including a trailing edge at the trailing edge of the deck, andproviding noise shifting means for each nacelle primary comprising one or more of chevrons at the core nozzle, secondary chevrons at the fan nozzle, a partial bypass mixer at the core nozzle, a long duct full flow mixer at the core nozzle, or a combination thereof,wherein the mounting location of each substantially vertical stabilizer to the respective wing is lower than the bottom of the respective outermost nacelle and each substantially vertical stabilizer extends at least as high as the top of the respective outermost nacelle,wherein the leading edge of each strake or wing, as applicable, extends forward of the respective nacelle leading end along the longitudinal axis of that nacelle at least a distance as great as the distance from the top surface of the respective wing to the top of the respective nacelle,wherein the trailing edge of the aft deck extends aft of the respective nacelle fan nozzle along the longitudinal axis of that nacelle at least a distance as great as the distance from the top surface of the respective wing to the top of the respective nacelle,wherein the fuselage extends between the nacelles and there is no central vertical stabilizer between the nacelles. 19. A method of shielding noise emitted toward the ground from a non-blended wing body aircraft in flight by nacelles, each nacelle having a longitudinal axis and including a turbofan engine, a fan nozzle having a diameter, and a core nozzle, the aircraft including aerodynamic structural surfaces, the method comprising: using noise shifting means associated with the fan nozzle, the core nozzle, or a combination thereof, to cause an increase in high frequency noise and a decrease in low frequency noise; andusing the aerodynamic structural surfaces as a noise shielding barrier between the nacelles and the ground, wherein the barrier has a trailing end that extends aft of the fan nozzle between approximately two and approximately four fan nozzle diameters from the fan nozzle along the nacelle longitudinal axis. 20. The method of claim 19, wherein the barrier trailing end extends aft of the fan nozzle between approximately 2.5 and approximately 3.5 fan nozzle diameters to result in, beneath the aircraft, sound attenuation for frequency bands 33 and higher of at least approximately 10 dB.
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