IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0782456
(2007-07-24)
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등록번호 |
US-7789343
(2010-09-27)
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발명자
/ 주소 |
- Sarh, Branko
- File, David J.
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출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
21 인용 특허 :
8 |
초록
▼
A morphing aircraft includes a lifting body and a telescopic lifting or control surface, such as a wing, coupled to the lifting body. The lifting surface is deployable between extended and retracted positions relative to the lifting body and configured such that, when disposed in the extended positi
A morphing aircraft includes a lifting body and a telescopic lifting or control surface, such as a wing, coupled to the lifting body. The lifting surface is deployable between extended and retracted positions relative to the lifting body and configured such that, when disposed in the extended position, the flight characteristics of the aircraft correspond to those of a low-speed, high-lift aircraft, and when disposed in the retracted position, the flight characteristics of the air-craft correspond to those of a high-speed, low-lift aircraft, the lifting surface is disposed entirely within the lifting body, and an outboard end surface of the lifting surface blends continuously into an outer mold line surface of the lifting body.
대표청구항
▼
What is claimed is: 1. An aircraft, comprising: a lifting body; a telescopic wing coupled to the lifting body, the wing being deployable between extended and retracted positions relative to the lifting body and configured such that, when disposed in the extended position, the flight characteristics
What is claimed is: 1. An aircraft, comprising: a lifting body; a telescopic wing coupled to the lifting body, the wing being deployable between extended and retracted positions relative to the lifting body and configured such that, when disposed in the extended position, the flight characteristics of the aircraft correspond to those of a low-speed, high-lift aircraft, and when disposed in the retracted position, the flight characteristics of the aircraft correspond to those of a high-speed, low-lift aircraft, the wing is disposed entirely within the lifting body, and an outboard end element of the wing blends continuously into an outer mold line of the lifting body; and a mechanism for pivoting the wing about an axis perpendicular to the wing and located at a root end thereof such that a portion of the wing outboard of the axis is sweepable between forward and aft positions. 2. The aircraft of claim 1, wherein the wing comprises a canard to provide lift to the aircraft. 3. The aircraft of claim 1, further comprising a telescopic vertical fin, stabilizer or ruddevator. 4. The aircraft of claim 1, wherein the lifting body comprises a blended wing body (BWB) or a body having a delta shape. 5. The aircraft of claim 1, wherein the wing comprises a plurality of segments having opposite inboard and outboard ends that nest concentrically within one another when the wing is disposed in the retracted position. 6. The aircraft of claim 5, wherein each segment comprises: an outer skin; a rib disposed inside the skin at the inboard end of the segment; a pair of fore and aft spar segments extending laterally between the inboard and outboard ends; and, a mechanism disposed adjacent to at least one of the inboard and outboard ends for slidably supporting the at least one end relative to an adjacent segment. 7. The aircraft of claim 6, wherein respective ones of the fore and aft spar segments nest concentrically within each other when the wing is disposed in the retracted position. 8. The aircraft of claim 6, wherein both the fore and aft spar segments of each wing segment are either rotatable about a lateral axis of the wing segment, or are fixed relative to the wing segment. 9. The aircraft of claim 8, wherein the wing segments containing the rotatable spar segments alternate with the wing segments containing the fixed spar segments. 10. The aircraft of claim 9, further comprising a mechanism for rotating respective pairs of the rotatable fore and aft spar segments such that the fixed pair of the fore and aft spar segments of an adjacent wing segment are urged coaxially toward or away from the adjacent pair of rotatable spar segments. 11. The aircraft of claim 6, wherein the sliding support mechanism comprises a sliding block having an inner end fixedly coupled to the rib of the wing segment and an outer end configured to slide in a laterally extending, inwardly opening, C-shaped channel contained in the skin of an adjacent wing segment. 12. The aircraft of claim 6, wherein the sliding support mechanism comprises a sliding block having an outer end fixed at the outer end of the skin of the wing segment and an inner end configured to slide in a laterally extending, outwardly opening, C-shaped channel contained in the skin of an adjacent wing segment.
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