Ventral fairing for an aircraft
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0727362
(2007-03-26)
|
등록번호 |
US-8128029
(2012-03-06)
|
우선권정보 |
ES-200602769 (2006-10-31) |
발명자
/ 주소 |
- Jiménez Del Lago, Mario
- Pérez Serrano, Julián
|
출원인 / 주소 |
|
대리인 / 주소 |
Wenderoth, Lind & Ponack, L.L.P.
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
6 |
초록
▼
Ventral fairing for an aircraft provided between a left wing and a right wing, which comprises a lower central section of convex transverse cross-section located between the left lower surface of the left wing and the right lower surface of the right wing, and with an angle between the cross-section
Ventral fairing for an aircraft provided between a left wing and a right wing, which comprises a lower central section of convex transverse cross-section located between the left lower surface of the left wing and the right lower surface of the right wing, and with an angle between the cross-section of the fairing and the line of cross-section corresponding to the lower surface of each wing of less than 90 degrees, separate left and right lower lateral sections of concave transverse cross-section which are respectively extended between the lower surface of each wing and the central section; separate first lines of inflection between the lower surface of each wing and the corresponding lateral section; separate second lines of inflection between the lateral sections and the central section.
대표청구항
▼
1. A ventral fairing for an aircraft locatable between a left wing with a left lower surface and a right wing of the aircraft with a right lower surface, the ventral fairing comprising: a lower central section of convex transverse cross-section locatable between said left lower surface and said righ
1. A ventral fairing for an aircraft locatable between a left wing with a left lower surface and a right wing of the aircraft with a right lower surface, the ventral fairing comprising: a lower central section of convex transverse cross-section locatable between said left lower surface and said right lower surface;an angle of less than 90 degrees between the cross-section of the fairing and the line of cross-section corresponding to the lower surface of each wing;a left lateral section of concave transverse cross-section which is extended between at least part of said left lower surface and said central section, and a right lateral section of concave transverse cross-section which is extended between at least part of said right lower surface and said central section;separate first lines of inflection between the lower surface of each wing and the corresponding lateral section;separate second lines of inflection between the lateral sections and the central section;a forward part in which are arranged said left and right lateral sections and the first lines of inflection;a rear part of convex transverse cross-section which does not include said left and right lateral sections nor the first lines of inflection; andseparate transition sections in which the configuration of the transverse cross-section of the forward part is progressively adapted to the configuration of the transverse cross-section of the rear part. 2. The ventral fairing according to claim 1, wherein the angle between the cross-section of the fairing and the line of cross-section corresponding to the lower surface of each wing is from 10° to 45°. 3. The ventral fairing according to claim 1, wherein the angle between the cross-section of the fairing and the line of cross-section corresponding to the lower surface of each wing is from 10° to 30°. 4. The ventral fairing according to claim 1, wherein the angle between the cross-section of the fairing and the line of cross-section corresponding to the lower surface of each wing is from 10° to 15°. 5. The ventral fairing arrangement according to claim 1, wherein the separate transition sections progressively reduce the left lateral concave cross-section and the right lateral concave cross-section in size in a direction away from said forward part toward said rear part such that the left lateral concave transverse cross-section and the right lateral concave transverse cross-section are eliminated at said rear part. 6. A ventral fairing arrangement comprising: a left wing having a left lower surface;a right wing having a right lower surface; anda ventral fairing havinga central convex transverse cross-section located between the left lower surface and the right lower surface,a left lateral concave transverse cross-section located between at least part of the left lower surface and the central convex transverse cross-section, anda right lateral concave transverse cross-section which is located between at least part of the right lower surface and the central convex transverse cross-section,wherein the angle between the ventral fairing and the left lower surface is less than 90° and the angle between the ventral fairing and the right lower surface is less than 90°,wherein a first left point of inflection is formed between the left lower surface and the left lateral concave transverse cross-section and a first right point of inflection is formed between the right lower surface and the right lateral concave transverse cross-section,wherein a second left point of inflection is formed between the left lateral concave transverse cross-section and the central convex transverse cross-section and a second right point of inflection is formed between the right lateral concave transverse cross-section and the central convex transverse cross-section,wherein the ventral fairing further has a forward section, and a rear section, andwherein the left lateral concave cross-section and the right lateral concave cross-section are progressively reduced in size in a direction away from the forward section toward the rear section such that the left lateral concave transverse cross-section and the right lateral concave transverse cross-section are eliminated at the rear section. 7. A ventral fairing for use attached between a left lower wing surface and a right lower wing surface, the ventral fairing having: a central convex transverse cross-section;a left lateral concave transverse cross-section; anda right lateral concave transverse cross-section,wherein the left lateral concave transverse cross-section is configured such that, when the ventral fairing is attached between the left lower wing surface and the right lower wing surface, an angle of less than 90° is formed between the ventral fairing and the left lower wing surface,wherein the right lateral concave transverse cross-section is configured such that, when the ventral fairing is attached between the left lower wing surface and the right lower wing surface, an angle of less than 90° is formed between the ventral fairing and the right lower wing surface,wherein the left lateral concave transverse cross-section is configured such that, when the ventral fairing is attached between the left lower wing surface and the right lower wing surface, a first left point of inflection is formed between the left lower wing surface and the left lateral concave transverse cross-section,wherein the right lateral concave transverse cross-section is configured such that, when the ventral fairing is attached between the left lower wing surface and the right lower wing surface, a first right point of inflection is formed between the right lower wing surface and the right lateral concave transverse cross-section,wherein a second left point of inflection is formed between the left lateral concave transverse cross-section and the central convex transverse cross-section and a second right point of inflection is formed between the right lateral concave transverse cross-section and the central convex transverse cross-section,wherein the ventral fairing further has a forward section, and a rear section, andwherein the left lateral concave cross-section and the right lateral concave cross-section are progressively reduced in size in a direction away from the forward section toward the rear section such that the left lateral concave transverse cross-section and the right lateral concave transverse cross-section are eliminated at the rear section.
이 특허에 인용된 특허 (6)
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Carter Glenn T. (Fort Worth TX) Paniszczyn Thomas F. (Fort Worth TX), Aircraft having improved performance with beaver-tail afterbody configuration.
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Maury, Jean-Pierre; Milhau, Alain; Pauly, Bernard, Aircraft with ventral fairing and seal for such an aircraft.
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Pauly, Bernard, Aircraft with ventral fairing and seal for such an aircraft.
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Halter Harold P., Boat bottom hull design.
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Gruensfelder Cynthia Ann ; Wille Robert Henry ; Ellis James Richard ; Diller Joseph Brice, Expandable aircraft cargo bay and method.
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Ellis James R. ; Diller Joseph B., Expandable aircraft section.
이 특허를 인용한 특허 (1)
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Mueller, Rainer; Huebner, Robert; Busch, Heinz-Peter; Wawrzyniec, Marie-Laure, Aircraft fuselage having burnthrough resistant components.
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