IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0481854
(2009-06-10)
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등록번호 |
US-8186617
(2012-05-29)
|
우선권정보 |
ES-200900951 (2009-04-07) |
발명자
/ 주소 |
- Llamas Sandin, Raul Carlos
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
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인용정보 |
피인용 횟수 :
4 인용 특허 :
4 |
초록
▼
An aircraft having a lambda-box wing configuration includes, a fuselage, a propulsion system, a first pair of swept-back airfoils, connected to the top forward portion of the fuselage, a second pair of swept-forward airfoils, connected to the lower rear portion of the fuselage at a point of the said
An aircraft having a lambda-box wing configuration includes, a fuselage, a propulsion system, a first pair of swept-back airfoils, connected to the top forward portion of the fuselage, a second pair of swept-forward airfoils, connected to the lower rear portion of the fuselage at a point of the said fuselage aft of the connection of the swept-back airfoils, and a third pair of substantially vertical airfoils, the tips of the swept-forward airfoils being connected to the lower side of the swept-back airfoils at an intermediate point of the span of the said swept-back airfoils, by the substantially vertical airfoils, the swept-back airfoils having a higher aspect ratio than that of the swept-forward airfoils, which makes the swept-back airfoils have a reduced induced drag without penalizing their weight.
대표청구항
▼
1. An aircraft comprising: a fuselage,a propulsion system,a pair of swept-back airfoils, connected to a top forward portion of the fuselage,a pair of swept-forward airfoils connected to a lower rear portion of the fuselage at a point of the fuselage aft of a connection of the swept-back airfoils,a p
1. An aircraft comprising: a fuselage,a propulsion system,a pair of swept-back airfoils, connected to a top forward portion of the fuselage,a pair of swept-forward airfoils connected to a lower rear portion of the fuselage at a point of the fuselage aft of a connection of the swept-back airfoils,a pair of substantially vertical airfoils,wherein the tips of the swept-forward airfoils are connected to a lower side of the swept-back airfoils at an intermediate point of a span of the swept-back airfoils by the substantially vertical airfoils, the swept-back airfoils having a higher aspect ratio than that of the swept-forward airfoils, which makes the swept-back airfoils have a reduced induced drag without penalizing their weight, as their maximum bending moment is reduced because of structural support that the swept-forward airfoils provide to the swept-back airfoils through the vertical airfoils, anda landing gear system comprising at least one leg connected to a lower portion of the forward fuselage, and two legs connected to a lower side of the swept-forward airfoils, the at least two legs of the lower side of the swept-forward airfoils and the propulsion system being connected to a same structural spar of the swept-forward airfoils, so that the inertial loads introduced by the propulsion system in cases of landing with high vertical accelerations are transmitted to the landing gear legs through a shortest possible load path within an airframe as allowed by landing gear legs separation and engine installation requirements. 2. The aircraft according to claim 1, wherein the swept-back airfoils and the swept-forward airfoils have sweep angles providing a horizontal separation between said swept-back airfoils and swept-forward airfoils, this separation reducing compressible drag of the aircraft flight at high speeds due to aerodynamic interaction of the swept-back airfoils and swept-forward airfoils. 3. The aircraft according to claim 1 or 2, wherein horizontal stagger of the swept-back airfoils and swept-forward airfoils provides sufficient longitudinal stability and control to the aircraft without the need of a horizontal stabilizer. 4. The aircraft according to claim 1, wherein a center of lift of the swept-back airfoils is located forward of a center of gravity of the aircraft, the center of lift of the swept-forward airfoils being located behind the center of gravity of the aircraft, this configuration helping to provide static stability to the aircraft. 5. The aircraft according to claim 1, wherein the propulsion system is located on an upper side of the swept-forward airfoils such that noise radiated downwards by exhaust gases of the propulsion system intercepts the swept-forward airfoils, which act as noise shields reducing perceived noise between the engines and the ground during aircraft flight. 6. The aircraft according to claim 5, wherein the noise radiated by the exhaust gases of the propulsion system and emitted downwards at an angle between 30° and 70°, this angle being measured from an axis of symmetry of an exhaust jet, intersects the upper side of the swept-forward airfoils which thereby act as noise shields. 7. The aircraft according to claim 1, wherein the propulsion system comprises at least two engines of turbojet, turbofan, turboprop or unducted fan type. 8. The aircraft according to claim 1, wherein the swept-back airfoils comprise control surfaces located at an inboard portion of said swept-back airfoils and adjacent to the fuselage such that these control surfaces are able to deflect downwards in order to produce a pitch-up moment during a take-off run to assist aircraft rotation for lift-off. 9. The aircraft according to claim 1, wherein the swept-forward airfoils comprise control surfaces located at an inboard portion of the swept-forward airfoils adjacent to the fuselage, these control surfaces being able to deflect upwards in order to produce a pitch-up moment during a take-off run to assist aircraft rotation for lift-off. 10. The aircraft according to claim 1, wherein the swept-forward airfoils provide aerodynamic forces in an upwards direction during a cruise portion of flight of the aircraft. 11. The aircraft according to claim 1, wherein the swept-back airfoils comprise trailing edge control surfaces that provide roll control to the aircraft. 12. The aircraft according to claim 1, further comprising: a retractable passenger staircase located at a rear lower portion of the fuselage to allow access to an interior of the aircraft without aid of ground equipment. 13. The aircraft according to claim 1, further comprising: a pair of airfoils connected to a rear portion of the fuselage, the airfoils providing additional static longitudinal stability and also longitudinal control to the aircraft by being able to rotate around an axis perpendicular to a plane of symmetry of the aircraft. 14. The aircraft according to claim 1, further comprising: a pair of airfoils connected to a forward portion of the fuselage, the airfoils providing additional static longitudinal stability and also longitudinal control to the aircraft by being able to rotate around an axis perpendicular to a plane of symmetry of the aircraft.
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