IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0428468
(2012-03-23)
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등록번호 |
US-8376281
(2013-02-19)
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발명자
/ 주소 |
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출원인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
11 |
초록
▼
An apparatus and method for improving the fuel range of an aircraft are provided. The aircraft includes a fuselage with a front windshield, and an external skin providing a top cover for a cockpit of the aircraft. The apparatus includes an aerodynamic fairing secured adjacent the windshield and encl
An apparatus and method for improving the fuel range of an aircraft are provided. The aircraft includes a fuselage with a front windshield, and an external skin providing a top cover for a cockpit of the aircraft. The apparatus includes an aerodynamic fairing secured adjacent the windshield and enclosing the external skin covering the cockpit for a reduction in an abrupt change in area encountered by air flowing along the length of the fuselage. An enclosure is formed between the aerodynamic fairing and the external skin in which a fuel bladder, configured with a reticulated polyurethane foam insert, may be disposed for added fuel capacity of the aircraft. The method includes steps of providing an aerodynamic fairing configured to balance the flow of fluid over the aircraft during flight, and securing the aerodynamic fairing atop the aircraft and adjacent the front windshield.
대표청구항
▼
1. An aircraft having a wing and further comprising: a fuselage providing a front windshield, and an external skin adjacent the windshield and covering a cockpit; andan aerodynamic fairing formed from material selected from a group consisting of aluminum, carbon fiber composite, fiberglass composite
1. An aircraft having a wing and further comprising: a fuselage providing a front windshield, and an external skin adjacent the windshield and covering a cockpit; andan aerodynamic fairing formed from material selected from a group consisting of aluminum, carbon fiber composite, fiberglass composite, and metal matrix composites, and secured atop said external skin and adjacent said front windshield, wherein said aerodynamic fairing in cooperation with said external skin covering said cockpit of said aircraft form an enclosed volume there between, wherein said aerodynamic fairing forms no portion of said wing, and further wherein at least a portion of the front windshield extends beneath the fairing, and in which the external skin covering the cockpit blocks at least a portion of a field of view above the head of a pilot flying the aircraft, and wherein said wing is attached to a side of said fuselage and not to a top of said fuselage. 2. The aircraft of claim 1, in which said aerodynamic fairing is configured to mitigate an abrupt change in area encountered by air flowing along a length of a fuselage of the aircraft during flight, thereby reducing drag encountered by said aircraft during flight. 3. The aircraft of claim 2, further comprising a fuel bladder disposed between said aerodynamic fairing and said external skin covering the cockpit. 4. The aircraft of claim 3, further comprising a fuel port supported by the aerodynamic fairing and communicating with an interior of the fuel bladder, wherein said fuel port provides access to the fuel bladder, and mitigates escapement of a fuel from said fuel bladder. 5. The aircraft of claim 4, further comprising a reticulated polyurethane foam insert enveloped by said fuel bladder, the reticulated polyurethane foam insert for explosion suppression of said fuel. 6. The aircraft of claim 1, in which said fuselage further providing a condensate relief channel disposed between said aerodynamic fairing and said external skin for relief of condensate formed between said aerodynamic fairing and said external skin. 7. The aircraft of claim 6, in which the aerodynamic fairing is formed from aluminum. 8. The aircraft of claim 6, in which the aerodynamic fairing is formed from a carbon fiber composite. 9. The aircraft of claim 6, in which the aerodynamic fairing is formed from a fiberglass composite. 10. The aircraft of claim 1, further comprising a fuel bladder disposed between said aerodynamic fairing and said external skin covering the cockpit. 11. The aircraft of claim 10, further comprising a fuel port supported by the aerodynamic fairing and communicating with an interior of the fuel bladder, wherein said fuel port provides access to the fuel bladder, and mitigates escapement of a fuel from said fuel bladder. 12. The aircraft of claim 11, further comprising a reticulated polyurethane foam insert enveloped by said fuel bladder, the reticulated polyurethane foam insert for explosion suppression of said fuel. 13. A combination comprising: an aircraft having a wing;a fuselage secured to the wing and providing a front windshield, and an external skin adjacent the windshield and covering a cockpit; andan aerodynamic fairing formed from material selected from a group consisting of aluminum, carbon fiber composite, fiberglass composite, and metal matrix composites, and secured atop said external skin and adjacent said front windshield, wherein said aerodynamic fairing in cooperation with said external skin covering said cockpit of said aircraft form an enclosed volume there between, wherein said aerodynamic fairing forms no portion of said wing, and further wherein at least a portion of the front windshield extends beneath the fairing, and in which the external skin covering the cockpit blocks at least a portion of a field of view above the head of a pilot flying the aircraft; andsteps for improving fuel range of the aircraft, and wherein said wing is attached to a side of said fuselage and not to a top of said fuselage. 14. The combination of claim 13, in which the steps for improving fuel range of the aircraft comprising: providing said aerodynamic fairing configured to reduce an abrupt change in area encountered a flow of fluid over a length of said fuselage of the aircraft during flight, thereby reducing drag encountered by said aircraft during flight; andsecuring said aerodynamic fairing atop said aircraft and adjacent a front windshield, wherein said aerodynamic fairing in cooperation with an external skin covering a cockpit of said aircraft form an enclosed volume there between. 15. The combination of claim 14, by steps further comprising: forming a condensate relief channel disposed between said aerodynamic fairing and said external skin for relief of condensate formed between said aerodynamic fairing and said external skin;incorporating a fuel port in a top portion of said aerodynamic fairing;mounting a fuel bladder within said enclosed volume and engaging an interior of the fuel bladder with said fuel port, wherein said fuel port provides access to the fuel bladder for supply of a fuel, and mitigates escapement of the fuel from said fuel bladder; anddisposing a reticulated polyurethane foam insert within said fuel bladder, said reticulated polyurethane foam insert for explosion suppression of said fuel. 16. The combination of claim 14, by a step further comprising, forming a condensate relief channel disposed between said aerodynamic fairing and said external skin for relief of condensate formed between said aerodynamic fairing and said external skin. 17. The combination of claim 16, by a step further comprising, incorporating a fuel port in a top portion of said aerodynamic fairing. 18. The combination of claim 17, by a step further comprising, mounting a fuel bladder within said enclosed volume, wherein an interior of the fuel bladder is fitted to said fuel port such that said fuel port provides access to the fuel bladder for supply of a fuel and mitigates escapement of the fuel from said fuel bladder. 19. The combination of claim 18, by a step further comprising, disposing a reticulated polyurethane foam insert within said fuel bladder, said reticulated polyurethane foam insert for explosion suppression of said fuel. 20. An aircraft having a wing and further comprising: a fuselage providing a front windshield, and an external skin adjacent the windshield and covering a cockpit;an aerodynamic fairing secured atop said external skin and adjacent said front windshield, wherein said aerodynamic fairing in cooperation with said external skin covering said cockpit of said aircraft form an enclosed volume there between, wherein said aerodynamic fairing forms no portion of said wing, and further wherein at least a portion of the front windshield extends beneath the fairing, and in which the external skin covering the cockpit blocks at least a portion of a field of view above the head of a pilot flying the aircraft, in which said aerodynamic fairing is configured to mitigate an abrupt change in area encountered by air flowing along a length of a fuselage of the aircraft during flight, thereby reducing drag encountered by said aircraft during flight;a fuel bladder disposed between said aerodynamic fairing and said external skin covering the cockpit;a fuel port supported by the aerodynamic fairing and communicating with an interior of the fuel bladder, wherein said fuel port provides access to the fuel bladder, and mitigates escapement of a fuel from said fuel bladder; anda reticulated polyurethane foam insert enveloped by said fuel bladder, the reticulated polyurethane foam insert for explosion suppression of said fuel.
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