IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0050916
(2002-01-22)
|
우선권정보 |
FR-2001-001000 (2001-01-25) |
발명자
/ 주소 |
- Dazet, Francis
- Rouyre, Franç
- ois
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
15 인용 특허 :
8 |
초록
▼
Articulation device for an aircraft door panel and an aircraft door integrating such a device.An aircraft door panel is articulated on the jamb by a device ( 20 ) that defines an approximately elliptical opening and closing trajectory, in which the major axis is approximately perpendicular to the pa
Articulation device for an aircraft door panel and an aircraft door integrating such a device.An aircraft door panel is articulated on the jamb by a device ( 20 ) that defines an approximately elliptical opening and closing trajectory, in which the major axis is approximately perpendicular to the panel. The device ( 20 ) comprises in particular a main arm ( 30 ), a secondary arm ( 32 ) articulated at the end of the main arm and a control lever ( 34 ) connecting the secondary arm ( 32 ) to the jamb, by articulation axes (A 4, A 5 ) close to the articulation axes of the main arm ( 30 ) on the jamb and the secondary arm ( 32 ) on the main arm. This arrangement makes it possible to fit a more voluminous emergency exit chute into the door panel.
대표청구항
▼
1. Articulation device for a panel of an aircraft door on a jamb of the said door, the said device comprising a mechanism connecting the jamb to the panel, to define a trajectory followed by the said panel, outside the aircraft, when the panel is opened and closed, and orientation means capable of m
1. Articulation device for a panel of an aircraft door on a jamb of the said door, the said device comprising a mechanism connecting the jamb to the panel, to define a trajectory followed by the said panel, outside the aircraft, when the panel is opened and closed, and orientation means capable of maintaining an approximately constant orientation of the panel when it is displaced along the said trajectory, in which the said mechanism defines a trajectory with a variable curvature comprising mainly a first part with a relatively large radius of curvature, said first part of the trajectory being approximately perpendicular to the panel, including a closed state of the said panel, and a second part of the trajectory with a relatively small radius of curvature, said second part being approximately parallel to the said panel and including a fully open state of the panel; in which the said mechanism comprises a main arm that can be articulated on the jamb by a first axis, at least one secondary arm articulated on the main arm by a second axis and that can be articulated on the panel by a third axis, and at least one control lever that can be articulated on the jamb by a fourth axis located close to the first axis and articulated on the secondary arm by a fifth axis located close to the second axis; and, in which the fourth axis is offset towards the outside of the aircraft with respect to the first axis and the fourth axis is offset towards the outside of the aircraft and towards the first axis with respect to the second axis. 2. Device according to claim 1, in which the said mechanism defines an approximately elliptical trajectory, a major axis of the trajectory being approximately perpendicular to the panel. 3. Device according to claim 1, in which the offsets between the first and the fourth axes and between the second and fifth axes are approximately equal. 4. Device according to claim 3, in which the length of the control lever is less than the length of the main arm by a value approximately equal to the offsets between the first and fourth axes and between the second and fifth axes. 5. Aircraft door comprising a jamb connected to the fuselage of the aircraft and a panel articulated on the jamb by an articulation device according to claim 1. 6. Aircraft door according to claim 5, in which the panel and the jamb comprise complementary stops that come into mutual contact when the panel is in its closed state, the said door comprising locking means that control the downwards movement of the panel in order to offset the stops on the panel downwards with respect to the stops on the jamb when the locking means are released, before the panel is opened along the said trajectory, and vice versa. 7. Articulation device for a panel of an aircraft door on a jamb of the said door, the said device comprising a mechanism connecting the jamb to the panel, to define a trajectory followed by the said panel, outside the aircraft, when the panel is opened and closed, and orientation means capable of maintaining an approximately constant orientation of the panel when it is displaced along the said trajectory, in which the said mechanism defines a trajectory with a variable curvature comprising mainly a first part with a relatively large radius of curvature, said first part of the trajectory being approximately perpendicular to the panel, including a closed state of the said panel, and a second part of the trajectory with a relatively small radius of curvature, said second part being approximately parallel to the said panel and including a fully open state of the panel; in which the said mechanism comprises a main arm that can be articulated on the jamb by a first axis, at least one secondary arm articulated on the main arm by a second axis and that can be articulated on the panel by a third axis, and at least one control lever that can be articulated on the jamb by a fourth axis located close to the first axis and articulated on the secondary arm by a fifth axis located close to the second axis; and, in which the orientation means comprise at least one first connecting rod the end of which is fixed to a first hinge pin supporting the main arm about the first axis, and the other end of which can be articulated on the jamb, at least one second connecting rod, one end of which is fixed to a second hinge pin installed free to rotate on the secondary arm about the third axis and the other end of which can be articulated on the panel, and synchronous connecting means inserted between the first hinge pin and the second hinge pin to keep the angular orientation of the second hinge pin constant. 8. Device according to claim 7, in which the synchronous connecting means comprise at least one first endless belt supported by the main arm and passing between pulleys fixed in rotation to the first hinge pin and to a third hinge pin free to rotate about the second axis respectively, and at least a second endless belt supported by the secondary arm and passing between pulleys fixed in rotation to the third hinge pin and the second hinge pin, respectively. 9. Device according to claim 8, in which the main arm is cranked towards the inside of the aircraft and supports a fourth hinge pin rotating in its cranked part, at least two first endless belts passing between the pulleys supported by the first and the fourth hinge pins respectively, and between the pulleys supported by the fourth and and third hinge pins respectively. 10. Device according to claim 7, in which the said mechanism defines an approximately elliptical trajectory, a major axis of said trajectory being approximately perpendicular to the panel. 11. Aircraft door comprising a jamb connected to the fuselage of the aircraft and a panel articulated on the jamb by an articulation device according to claim 7.
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