IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0946579
(2007-11-28)
|
등록번호 |
US-8128023
(2012-03-06)
|
우선권정보 |
FR-06 55199 (2006-11-30) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
7 |
초록
▼
When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface b
When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft.
대표청구항
▼
1. An aircraft comprising: a fuselage having front and rear portions;a wing connected to the fuselage; anda rear tail unit situated behind the wing at the rear of the aircraft, said rear tail unit having at least one horizontal stablilizer;at least one jet engine fixed to the at least one horizontal
1. An aircraft comprising: a fuselage having front and rear portions;a wing connected to the fuselage; anda rear tail unit situated behind the wing at the rear of the aircraft, said rear tail unit having at least one horizontal stablilizer;at least one jet engine fixed to the at least one horizontal stabilizer of the rear tail unit and located under the horizontal stabilizer by means of an attachment mast disposed between the horizontal stabilizer and the at least one jet engine; said attachment mast and said horizontal stabilizer being arranged such that said at least one engine hangs vertically adjacent to said fuselage and substantially proximal to the ground, or hangs vertically above a non structural part of said fuselage and substantially proximal to the top to the fuselage, thereby allowing easy installation and/or removal of said engine. 2. The aircraft according to claim 1, wherein the at least one horizontal stabilizer is fixed to the fuselage. 3. The aircraft according to claim 1, wherein the rear tail unit further comprises a vertical stabilizer and wherein the at least one horizontal stabilizer is fixed to said vertical stabilizer above the fuselage. 4. The aircraft according to claim 1, wherein the vertical stabilizer further comprises two substantially vertical aerodynamic surfaces, and wherein the at least one horizontal stabilizer is fixed to said vertical aerodynamic surfaces above the fuselage and extends laterally beyond said vertical aerodynamic surfaces. 5. The aircraft according to claim 4, wherein the two substantially vertical aerodynamic surfaces form an angle. 6. The aircraft according to claim 4, comprising at least two jet engines fixed to the at least one horizontal stabilizer arranged symmetrically with respect to a vertical axial plane of the aircraft. 7. The aircraft according to claim 1, wherein the at least one horizontal stabilizer comprises end elements forming essentially vertical aerodynamic surfaces extending vertically above and/or below the horizontal stabliizer. 8. The aircraft according to claim 1, wherein the at least one horizontal stabilizer comprises an upper horizontal aerodynamic surface that is raised with respect to the fuselage by at least two substantially vertical aerodynamic surfaces fixed to the ends of said upper horizontal aerodynamic surface. 9. The aircraft according to claim 8, wherein the vertical aerodynamic surfaces are fixed to the fuselage of the aircraft. 10. The aircraft according to claim 8, wherein the at least one horizontal stabilizer further comprises a lower horizontal aerodynamic surface fixed to the fuselage of the aircraft and the vertical aerodynamic surfaces are fixed between the lower horizontal aerodynamic surface and the upper horizontal aerodynamic surface. 11. Aircraft according to claim 10, characterized in that the geometric shapes and the arrangements of the lower horizontal surface (72), of the upper horizontal surface (73), of the vertical surfaces (62, 63), of the rear horizontal tail unit, and of the attachment masts (9a, 9b) allow, for at least one engine (8a, 8b) fixed to the upper horizontal surface (73) of the rear horizontal tail unit, the installation and/or the removal by moving said engine with a vertical movement without there being any interference between said engine and structural elements of the aircraft (1). 12. Aircraft according to claim 11, characterized in that the lower horizontal surface (72) of the rear horizontal tail unit comprises a leading edge (721) with a concave shape in plan view. 13. Aircraft according to claim 11, characterized in that the vertical surfaces (62, 63) are inclined forwards such that one end of the upper horizontal surface (73) of the rear horizontal tail unit is forward with respect to an end of the lower horizontal surface (72) of the rear horizontal tail unit. 14. Aircraft according to claim 8, characterized in that the fuselage (2) comprises non-structural parts (22, 23) able to allow, for at least one engine (8), the installation or the removal of said engine by moving said engine with a vertical movement without there being any interference between said engine and structural parts (21) of the aircraft (1). 15. Aircraft according to claim 14, characterized in that the fuselage (2) comprises in its structural parts (21), a well (23, 25) whose dimensions make it possible to move the engine (8) with a vertical movement of said engine. 16. Aircraft according to claim 15, characterized in that a wall (231) of the well (23) corresponds to a sealed wall of the fuselage (2) when said fuselage comprises a sealed rear end. 17. Aircraft according to claim 14, characterized in that the fuselage (2) comprises a tail cone (22) that can be moved to make it possible to move the engine (8) with a vertical movement of said engine. 18. Aircraft according to claim 17, characterized in that the tail cone (22) is removable, in order to be separated from the structural part (21) of the fuselage (2). 19. Aircraft according to claim 17, characterized in that the tail cone (22) is articulated on the structural part (21) of the fuselage (2). 20. The aircraft according to claim 8, wherein the at least one engine is fixed to the upper horizontal aerodynamic surface of the horizontal stabilizer in the vertical axial plane of the aircraft. 21. The aircraft according to claim 8, further comprising at least two engines fixed to the upper horizontal aerodynamic surface of the horizontal stabilizer and arranged symmetrically with respect to the vertical axial plane of the aircraft. 22. The aircraft according to claim 21, further comprising an engine fixed to the upper horizontal aerodynamic surface substantially in the vertical axial plane of the aircraft. 23. The aircraft according to claim 20, wherein the engine is in a position offset in a direction parallel to the longitudinal axis of the aircraft. 24. The aircraft according to claim 8, further comprising at least one additional vertical surface between the upper horizontal aerodynamic surface and the substantially horizontal lower surface and/or between the upper horizontal aerodynamic surface and the fuselage, said at least one additional vertical surface being situated between two engines fixed to the upper horizontal aerodynamic surface. 25. The aircraft according to claim 24, wherein the at least one additional vertical surface comprises means of shielding against projections of engine debris. 26. The aircraft according to claim 1, further comprising at least two engines fixed to the wing of the aircraft and arranged substantially symmetrically with respect to a vertical axial plane of the aircraft.
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