Method and apparatus for reducing aircraft noise
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0946341
(2010-11-15)
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등록번호 |
US-8393567
(2013-03-12)
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발명자
/ 주소 |
- Moore, Matthew D.
- Boren, Kelly L.
- Lan, Justin
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
3 인용 특허 :
6 |
초록
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An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is locate
An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is located longitudinally between the rear spar and the wing trailing edge. The propulsor may also be mounted such that a lowest point of the rotor diameter is located vertically above the wing upper surface.
대표청구항
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1. An arrangement for an aircraft, comprising: a fuselage;a wing having a wing upper surface, a rear spar and a wing trailing edge; anda propulsor including at least one rotor having a rotor diameter and a rotor axis, the propulsor being mounted such that the at least one rotor is located according
1. An arrangement for an aircraft, comprising: a fuselage;a wing having a wing upper surface, a rear spar and a wing trailing edge; anda propulsor including at least one rotor having a rotor diameter and a rotor axis, the propulsor being mounted such that the at least one rotor is located according to the following:longitudinally between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis; andvertically such that a lowest point of the rotor diameter is above the wing upper surface. 2. The arrangement of claim 1 wherein the rotor is located: laterally such that the shortest distance from the rotor diameter to the fuselage is approximately no greater than two rotor diameters. 3. The arrangement of claim 1 wherein the wing includes a wing tip, the wing being configured such that the rotor is located: longitudinally between a forward most point and an aftmost point of the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g. 4. The arrangement of claim 3 wherein: the wing trailing edge has a sweep angle in the range of approximately −5 to −10 degrees. 5. The arrangement of claim 3 wherein the propulsor being mounted such that the rotor is located according to the following: longitudinally aft of the trailing edge;vertically such that a lowest point of the rotor diameter is no lower than a horizontal plane passing through a terminus of the wing chord line at the trailing edge. 6. The arrangement of claim 1 wherein: the wing has a dihedral angle of up to approximately 10 degrees. 7. The arrangement of claim 1 wherein the wing includes a wing tip, the rotor being located: vertically such that a highest point of the rotor diameter is vertically lower than the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g. 8. The arrangement of claim 1 wherein: the rotor axis has a local angle of attack no greater than 0 degrees relative to a local flow over the wing upper surface. 9. The arrangement of claim 8 wherein: the local angle of attack is between approximately 0 degrees and −4 degrees. 10. The arrangement of claim 1 wherein the fuselage has a cabin including passenger seating; the rotor being located: longitudinally such that the rotor is generally non-aligned with the passenger seating. 11. The arrangement of claim 1 wherein: the propulsor is configured as a turbofan having a nacelle and an inlet having an inlet axis and a hilite defining a hilite plane;the turbofan being mounted according to the following: longitudinally such that the hilite plane is between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the inlet axis; andvertically such that a lowest point of the hilite is above the wing upper surface. 12. The arrangement of claim 11 wherein the nacelle terminates at a secondary flow exit, the turbofan being mounted according to the following: longitudinally such that the secondary flow exit is aft of the wing leading edge; andvertically such that a lowest point of the nacelle is above the wing upper surface. 13. An arrangement for acoustic shielding of an open fan aircraft, comprising: a generally tubular fuselage;a wing having a wing tip, a wing upper surface, a rear spar and a wing trailing edge; anda propulsor having counter-rotating forward and aft rotors defining a rotor diameter and a rotor axis and including a plurality of rotor blades each having a blade pitch axis, the blade pitch axes of the forward and aft rotors defining a mid-point therebetween, the propulsor being mounted such that the forward and aft rotors are located according to the following: longitudinally such that the mid-point is between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis;longitudinally such that the mid-point is between a forward most point and an aftmost point of the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g; andvertically such that a lowest point of the rotor diameter is vertically above the wing upper surface. 14. A method of attenuating noise produced by a propulsor of an aircraft, the propulsor including at least one rotor having a rotor diameter and a rotor axis, the aircraft including a wing having a wing upper surface, a rear spar and a wing trailing edge, comprising the steps of: locating the rotor longitudinally between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis; andlocating the rotor vertically such that a lowest point of the rotor diameter is above the wing upper surface. 15. The method of claim 14 wherein the step of locating the propulsor longitudinally further comprises: locating the rotor longitudinally such that the rotor is between a forward most point and an aftmost point of the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g. 16. The method of claim 14 further comprising the step of: providing the wing with a dihedral angle of up to approximately 10 degrees. 17. The method of claim 14 wherein the wing includes a wing tip, the step of locating the propulsor vertically further comprises: locating the rotor diameter vertically below the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g. 18. The method of claim 14 wherein the steps of locating the propulsor comprises: locating the rotor longitudinally aft of the trailing edge; andlocating the rotor vertically such that a lowest point of the rotor diameter is no lower than a horizontal plane passing through a terminus of the wing chord line at the trailing edge. 19. The method of claim 14 further comprising the step of: orienting the propulsor such that the rotor axis has a negative local angle of attack relative to a local flow over the wing upper surface. 20. The method of claim 14 wherein the propulsor includes forward and aft rotors including a plurality of rotor blades each having a blade pitch axis, the blade pitch axes of the forward and aft rotors defining a mid-point therebetween, the step of locating the rotor longitudinally comprising: locating the mid-point between a forward most point and an aftmost point of the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g. 21. A method of attenuating noise produced by a propulsor of an aircraft, the propulsor having counter-rotating forward and aft rotors defining a rotor diameter and a rotor axis and including a plurality of rotor blades each having a blade pitch axis, the blade pitch axes of the forward and aft rotors defining a mid-point therebetween, the aircraft including a wing having a wing tip, a rear spar and a wing trailing edge, the method comprising the steps of: locating the mid-point longitudinally between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis;locating the mid-point longitudinally between a forward most point and an aftmost point of the wing tip when the wing is deflected upwardly under a wing loading of approximately 1-g;locating the forward and aft rotors vertically such that a lowest point of the rotor diameter is above the wing upper surface; andlocating the forward and aft rotors vertically such that a highest point of the rotor diameter is below the wing tip when the wing is deflected upwardly under the approximate 1-g wing loading.
이 특허에 인용된 특허 (6)
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Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C., Aircraft.
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Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C., Aircraft configuration.
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Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C., Airplane configuration.
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Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C., Airplane configuration.
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Guo,Yueping, Apparatus and method for reducing aircraft noise and acoustic fatigue.
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Sankrithi, Mithra M. K. V.; Paisley, David J.; Moore, Matthew D., Noise-shielding wing configuration.
이 특허를 인용한 특허 (3)
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Golshany, Sina S.; Huntly, David Miles; Blom, Adriana W.; Erickson, Todd W.; Tretow, Paul R., Contra-rotating open fan propulsion system.
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Yao, Jixian; Breeze-Stringfellow, Andrew, Stabilizer assembly for an aircraft AFT engine.
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Lan, Justin Honshune; Vogel, Stuart William; Cohen, Robert L., Systems and methods for acoustic resonance mitigation.
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