Device to handle and lock a cover of an aircraft nacelle
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-027/00
B64D-027/16
B64D-027/18
출원번호
US-0435655
(2009-05-05)
등록번호
US-8128022
(2012-03-06)
우선권정보
FR-08 02469 (2008-05-05)
발명자
/ 주소
Bulin, Guillaume
출원인 / 주소
Airbus Operations SAS
대리인 / 주소
Young & Thompson
인용정보
피인용 횟수 :
2인용 특허 :
2
초록▼
The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe (56) that empties out toward the front at an air intake (58), and, on the outside, an aerodynamic wall that extends from the air intake (58) up to the rear end of the nacelle, and a hood (62) that compri
The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe (56) that empties out toward the front at an air intake (58), and, on the outside, an aerodynamic wall that extends from the air intake (58) up to the rear end of the nacelle, and a hood (62) that comprises said air intake (58) as well as a cylindrical wall (64) that forms at least one portion of the aerodynamic surface of the outside of the nacelle, whereby said hood (62) can move translationally relative to a stationary part of the nacelle toward the front along slides (72), each slide (72) comprising a guide element (74) that is connected to the hood (or to the stationary part of the nacelle), whereby said guide element (74) can slide into a pipe (78) that is connected to the stationary part of the nacelle (or to a hood) and has a section that is above the section of the guide element (74) so as to allow the hood (62) to rotate in order to immobilize it in the closed position.
대표청구항▼
1. An aircraft nacelle, comprising: aerodynamic surface of an outside of the nacelle;an air intake (58);on an inside of the nacelle, an inside pipe (56) emptying out toward a front at the air intake (58);on an outside of the nacelle, an aerodynamic wall extending from the air intake (58) up to a rea
1. An aircraft nacelle, comprising: aerodynamic surface of an outside of the nacelle;an air intake (58);on an inside of the nacelle, an inside pipe (56) emptying out toward a front at the air intake (58);on an outside of the nacelle, an aerodynamic wall extending from the air intake (58) up to a rear end of the nacelle; anda hood (62) comprised of said air intake (58) and a cylindrical wall (64) that forms at least one portion of the aerodynamic surface of the outside of the nacelle;a stationary part;slides (72), each slide (72) comprising a guide element (74) connected by a connecting part (82) to the hood and a conduct (78) connected to the stationary part,said guide element (74) having a rectilinear bar shape with a cylindrical section that can slide into the conduct (78) of the sliding element (76) that is connected to the stationary part;wherein said hood (62) is movable translationally, relative to the stationary part, toward a front of the nacelle along the slides (72),wherein the conduct (78) has an oblong section with a width essentially equal to a diameter of the bar and a length allowing a rotation of the hood (62) to immobilize the hood in the closed state,wherein the sliding element (76) has a slot (80) extending parallel to the guide element (74), said slot (80) being positioned so as not to allow passage of the connecting part (82) and the translation of the hood (62) when the hood (62) is in the closed state,wherein the connecting part (82) is arranged to the right of the slot when the hood has pivoted and allows the translational movement of said hood, said slot (80) having a width suited to the connecting part (82) so as not to allow the rotation of the hood (62) when the hood is not in the closed state. 2. The aircraft nacelle according to claim 1, wherein the connecting part (82) comprises at least two crosspieces (84) arranged close to each end of the guide element (74),wherein the crosspieces (84) are separated by a distance greater than or equal to the length of the sliding element (76), and at least one end of said sliding element (76) rests against at least one of the crosspieces (84) in the closed state. 3. The aircraft nacelle according to claim 1, wherein the front edge (86) of the inside pipe (56) comprises alignment pieces (92) arranged in a plane perpendicular to the longitudinal direction (70) of the nacelle in a tangential direction and distributed over the circumference of the front edge (86), each alignment piece (92) able to work with a housing (94) arranged in plane that contains the longitudinal axis, the housings being integral with a rear frame (66) of the hood (62) adjacent of the edge (86) of the inside pipe (56) in the closed state. 4. The aircraft nacelle according to claim 3, wherein the rear frame (66) of the hood (62) comprises guide rails (96) distributed over the circumference, each guide rail comprising a plate with an edge suitable for guiding the inside pipe (56) and a housing (94) that can accommodate an alignment piece (92). 5. The aircraft nacelle according to claim 1, wherein the front edge (86) of the inside pipe (56) comprises a circumferential shape (88) that projects along the longitudinal direction of the nacelle and arranged to work with a circumferential rib (90) provided at a rear frame (66) of the hood (62) adjacent of the edge (86) of the inside pipe (56) in the closed state. 6. The aircraft nacelle according to claim 1, wherein the hood (62) is eccentric relative to the stationary part so that the center of gravity of the hood is arranged at the base and under the longitudinal axis (70) in the closed state. 7. The aircraft nacelle according to claim 1, further comprising locking/unlocking means occupying two states defined by i) a first locked state in which the locking/unlocking means immobilize the hood in the closed state after pivoting, and ii) a second unlocked state in which the locking/unlocking means allow the hood to rotate. 8. The aircraft nacelle according to claim 6, wherein the locking/unlocking means comprise a handle (110) that can pivot relative to the hood and a stop (112) integral with the stationary part, andwherein said handle occupies i) a first locked state in which the handle cannot pivot and rests against said stop (112) and ii) a second unlocked state in which the handle can pivot and allows the hood (62) to rotate. 9. The aircraft nacelle according to claim 1, further comprising rear hooking means interposed between a rear frame (100) provided at the rear edge of the inside pipe (56) and a collar (102) that connected to the inside face of the hood (62). 10. The aircraft nacelle according to claim 1, wherein the hood comprises a cutaway (69) in a U shape allowing the passage of a mast (52), at least one stationary hook (126) at one of the branches of the U, and at least one hook (128) that is controlled by at least one handle (130) at another branch of the U. 11. An aircraft nacelle, comprising: an air intake;on an inside of the nacelle, an inside pipe (56) emptying out toward a front at the air intake (58),on the outside of the nacelle, an aerodynamic wall that extends from the air intake (58) up to a rear end of the nacelle,a hood (62) comprised of said air intake (58) and a cylindrical wall (64) forming at least one portion of an aerodynamic surface of the outside of the nacelle,wherein said hood (62) is movable translationally relative to a stationary part of the nacelle toward the front along slides (72), each slide (72) comprising a guide element (74) connected by connecting means (82) to the stationary part of the nacelle,wherein said guide element (74) has a rectilinear bar shape with a cylindrical section and is slideable into a conduct (78) of a sliding element (76) s connected to the hood,wherein the conduct (78) has an oblong section with a width essentially equal to a diameter of the bar and a length allowing a rotation of the hood (62) to immobilize the hood in the closed state,wherein the sliding element (78) has a slot (80) that extends parallel to the guide element (74), said slot (80) being positioned so as not to allow the passage of the connecting means (82) and the translation of the hood (62) when the hood (62) is in the closed state,wherein the connecting means (82) is arranged to the right of the slot when the hood has pivoted to permit the translational movement of said hood, said slot (80) having a width relative the connecting means (82) so as not to allow the rotation of the hood (62) when the hood is not in the closed state. 12. The aircraft nacelle according to claim 11, wherein the connecting means (82) comprise at least two crosspieces (84) arranged close to each end of the guide element (74),wherein the crosspieces (84) are separated by a distance that is greater than or equal to the length of the sliding element (76), andwherein at least one end of said sliding element (76) rests against at least one of the crosspieces (84) in the closed state. 13. The aircraft nacelle according to claim 11, wherein the front edge (86) of the inside pipe (56) comprises alignment pieces (92) arranged in a plane perpendicular to the longitudinal direction (70) of the nacelle in a tangential direction and distributed over the circumference of the front edge (86), each alignment piece (92) able to work with a housing (94) arranged in plane that contains the longitudinal axis, the housings being integral with a rear frame (66) of the hood (62) adjacent of the edge (86) of the inside pipe (56) in the closed state. 14. An aircraft nacelle according to claim 13, wherein the rear frame (66) of the hood (62) comprises guide rails (96) distributed over the circumference, each guide rail comprising a plate with an edge suitable for guiding the inside pipe (56) and a housing (94) that can accommodate an alignment piece (92). 15. An aircraft nacelle according to claim 11, wherein the front edge (86) of the inside pipe (56) comprises a circumferential shape (88) that projects along the longitudinal direction of the nacelle and arranged to work with a circumferential rib (90) provided at a rear frame (66) of the hood (62) adjacent of the edge (86) of the inside pipe (56) in the closed state. 16. An aircraft nacelle according to claim 11, wherein the hood (62) is eccentric relative to the stationary part of the nacelle so that the center of gravity of the hood is arranged at the base and under the longitudinal axis (70) in the closed state. 17. An aircraft nacelle according to claim 11, further comprising locking/unlocking means having two states defined by i) a first locked state in which the locking/unlocking means immobilize the hood in the closed state after pivoting, and ii) a second unlocked state in which the locking/unlocking means allow the hood to rotate. 18. An aircraft nacelle according to claim 17, wherein the locking/unlocking means comprise a handle (110) that is pivotable relative to the hood and a stop (112) integral with the stationary part,wherein said handle is able to occupy a first locked state in which the handle cannot pivot and rests against said stop (112) and a second unlocked state in which the handle can pivot and allows the hood (62) to rotate. 19. An aircraft nacelle according to claim 11, further comprising rear hooking means interposed between a rear frame (100) provided at the rear edge of the inside pipe (56) and a collar (102) connected to the inside face of the hood (62). 20. An aircraft nacelle according to claim 11, wherein the hood comprises a cutaway (69) in a U shape for allowing the passage of a mast (52), andfurther comprising at least one stationary hook (126) at one branch of the U, and at least one hook (128) controlled, by at least one handle (130), at another branch of the U.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (2)
Hersen, Rene M. J.; Soulter, Pascal-Marie P. M., Movable aircraft engine cowling.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.