IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0178704
(2008-07-24)
|
등록번호 |
US-8152095
(2012-04-10)
|
우선권정보 |
FR-07 05466 (2007-07-26) |
발명자
/ 주소 |
- Cazals, Olivier
- Koch, Alexander
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
13 |
초록
▼
An aircraft, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fusel
An aircraft, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following: air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.
대표청구항
▼
1. An aircraft, having: a fuselage, a wing structure fixed to the fuselage, at least one horizontal stabilizer rearward of the wing, at least two vertical stabilizers, substantially vertical, fixed to the fuselage rearward of the wing, and at least two propulsion jet engines, wherein: the fuselage h
1. An aircraft, having: a fuselage, a wing structure fixed to the fuselage, at least one horizontal stabilizer rearward of the wing, at least two vertical stabilizers, substantially vertical, fixed to the fuselage rearward of the wing, and at least two propulsion jet engines, wherein: the fuselage has a cylindrical fuselage section followed rearward by a fuselage section, the cross section of which is progressively flattened to have a low thickness fuselage rear end and the width of which is substantially those of the cylindrical section;the wing is fixed to the fuselage on the top of said fuselage;the at least two propulsion jet engines are mounted side by side on top of the fuselage, rearward of the wing, inside a cowling structure extended longitudinally above the fuselage between, in front, air inlet openings located above the fuselage at the location of wing root chords, and, on the rear, exhaust nozzle outlets located above the fuselage and forwardly of the fuselage rear end, the width of said fuselage being at least the width of said cowling structure;the cowling structure has lateral walls, substantially vertical, one on each outer side of the cowling structure, which are substantially in aerodynamic continuity with two vertical stabilizers of the at least two vertical stabilizers, and has a substantially flat horizontal wall joining the lateral walls extending longitudinally between the air inlet openings and the exhaust nozzle outlets, said exhaust nozzle outlets being located between said two vertical stabilizers and located forward of the trailing edges of said two vertical stabilizers and aft of the leading edges of said two vertical stabilizers. 2. An aircraft according to claim 1, wherein said at least two propulsion engines are suspended under a fixed part of the cowling structure. 3. An aircraft according to claim 1, wherein each of the air intake openings is inclined rearward, wherewith an upper lip of said opening is disposed aftwardly of a lip in the base portion of said opening. 4. An aircraft according to claim 1, wherein the at least two propulsion engines are installed in a sunken position, such that 10% to 30% of the diameter of each propulsion engine is disposed below the upper delimiting surface of the fuselage. 5. An aircraft according to claim 1, wherein interior surfaces of the cowling structure of the propulsive package, which interior surfaces extend inside air inlets and exhaust nozzles of said propulsive package, have treatment to absorb acoustic waves. 6. An aircraft according to claim 1, wherein the at least one horizontal stabilizer has a substantially horizontal aerodynamic surface which is fixed to an upper portion of the two vertical stabilizers. 7. An aircraft according to claim 1, wherein the at least two propulsion engines are disposed at a locus with respect to the longitudinal axis of the fuselage, such that zones of ejection of scraps from propulsion engines will not involve zones of the wing structure or of the stabilizers where organs which are important for the safety of the aircraft are disposed. 8. An aircraft according to claim 1, wherein said at least two propulsion engines are suspended under a fixed part of the cowling structure above maintenance shafts which traverse an aft portion of the fuselage, which shafts generally extend vertically with respect to said propulsion engines.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.