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1. 发明公开

EP4403460A1 LIFTING ASSEMBLY FOR AN AIRCRAFT DOOR 审中-公开
公开(公告)号：EP4403460A1
公开(公告)日：2024-07-24
申请号：EP24152937.9
申请日：2024-01-19
申请人： Rohr, Inc.
发明人： BUCHET, Damien
IPC分类号： B64C1/14
CPC分类号： B64C1/1407 , B64C1/143 , B64C1/1423
摘要： A door assembly (26) for an aircraft (20) includes a door (28), a door handle (34), a door hinge (32), a support assembly (50), and a lifting assembly (58). The door handle (34) is rotatable between an unlatched position and a latched position. The support assembly (50) rotatably mounts the door hinge (32) to the door (28). The lifting assembly (58) includes a latch cam (120), a lift track (123), and a latch idler (122). The latch cam (120) is mounted to the door handle (34), rotatable with the door handle (34) about the door handle rotational axis (124), and forms an eccentric roller path (126) extending about the door handle rotational axis (124). The latch idler (122) includes a first roller (146) and a second roller (148). The first roller (146) is disposed on a lift track (123) of the support assembly (50) and configured to roll along the lift track (123). The second roller (148) is disposed within the eccentric roller path (126). The latch idler (122) is configured to lift the door (28) as the door handle (34) rotates from the latched position to the unlatched position.

2. 发明公开

EP4403459A1 SUPPORT ASSEMBLY FOR AN AIRCRAFT DOOR 审中-公开
公开(公告)号：EP4403459A1
公开(公告)日：2024-07-24
申请号：EP24152899.1
申请日：2024-01-19
申请人： Rohr, Inc.
发明人： BUCHET, Damien
IPC分类号： B64C1/14
CPC分类号： B64C1/1407 , B64C1/143
摘要： A door assembly (26) for an aircraft (20) includes a door (28), a door hinge (32), and a support assembly (50) rotatably mounting the door hinge (32) to the door (28). The support assembly (50) includes a forearm (52) and at least one link. The forearm (52) is rotatably mounted to the door hinge (32) along a first rotational axis (74) and extends along the first rotational axis (74) between an upper end (72) and a lower end (70). The at least one link extends between an inner end (96) and an outer end (98) and is rotatably mounted to the forearm (52) at the inner end (96). The at least one link is rotatable relative to the forearm (52) about a second rotational axis (74) and rotatably mounted to the door (28) at the outer end (98). The at least one link is rotatable about the second rotational axis (74) between a lowered position of the door (28) and a raised position of the door (28).

3. 发明公开

EP4403462A1 CLUTCH ASSEMBLY FOR AN AIRCRAFT DOOR 审中-公开
公开(公告)号：EP4403462A1
公开(公告)日：2024-07-24
申请号：EP24152978.3
申请日：2024-01-19
申请人： Rohr, Inc.
发明人： BUCHET, Damien
IPC分类号： B64C1/14
CPC分类号： B64C1/1407
摘要： A door assembly (26) for an aircraft (20) includes a door (28), an interior door handle (34) and an exterior door handle (36), and a clutch assembly (40). The interior door handle (34) and the exterior door handle (36) are rotatable about a door handle rotational axis (70). The clutch assembly (40) includes a shaft (52), an exterior coupling body (56), an exterior handle body (80), and a clutch lever (66). The shaft (52) includes an interface portion (74). The interface portion (74) includes a handle tooth (76). The exterior coupling body (56) includes a fixed body portion (88) disposed adjacent the interface portion (74). The exterior handle body (80) is rotatably mounted to the exterior coupling body (56) and is rotatable between an engaged position and a disengaged position. The clutch lever (66) is rotatably mounted to the exterior coupling body (56). The clutch lever (66) is pivotable between and to an engaged pivot position and a disengaged pivot position. In the engaged pivot position, the handle tooth (76) is positioned circumferentially between the clutch lever (66) and the fixed body portion.

4. 发明公开

EP4403461A1 INTERLOCK ASSEMBLY FOR AN AIRCRAFT DOOR 审中-公开
公开(公告)号：EP4403461A1
公开(公告)日：2024-07-24
申请号：EP24152943.7
申请日：2024-01-19
申请人： Rohr, Inc.
发明人： BUCHET, Damien
IPC分类号： B64C1/14
CPC分类号： B64C1/1407 , B64C1/14 , B64C1/1423 , B64D25/00
摘要： An interlock assembly (52) for an aircraft door (28) includes a shaft (54), an interlock first portion (56), and an auto-disarm second portion (58). The shaft (54) is rotatable about a second rotational axis (60) between an armed position and a disarmed position. The shaft (54) includes an interlock cam (64) and an auto-disarm cam (66). In a first interlock position, the interlock first portion (56) permits rotation of the shaft (54) between the armed position and the disarmed position. In a second interlock position, the interlock first portion (56) prevents rotation of the shaft (54) from the disarmed position to the armed position. In a first auto-disarm position, the auto-disarm second portion (58) permits rotation of the shaft (54) between the armed position and the disarmed position. In a second auto-disarm position, the auto-disarm second portion (58) prevents rotation of the shaft (54) from the disarmed position to the armed position.

5. 发明公开

EP4331997A1 LONG THROW LATCH 审中-公开
公开(公告)号：EP4331997A1
公开(公告)日：2024-03-06
申请号：EP22306311.6
申请日：2022-09-05
申请人： Rohr, Inc.
发明人： BUCHET, Damien
IPC分类号： B64D29/06 , E05B41/00 , E05C19/14 , F02K1/76
摘要： There is provided a latch mechanism (200) for joining two portions (110, 120) of a gas turbine engine, the latch mechanism being moveable between an open and a closed position. The latch mechanism comprises a first member (210) configured to be attachable to a first portion (110) of a gas turbine engine; a second member (220) pivotally attached to the first member (210), wherein the first member (210) is attached to the second member (220) at a first position (221); a handle (240) pivotally attached to the second member (220), wherein the handle (240) is attached to the second member (220) at a second position (222); and a third member (230) pivotally attached to the second member (220). The third member (230) is attached to the second member (220) at a third position (223), the third position (223) being between the first position (221) and the second position (222), and wherein the third member (230) comprises securing means (231) for securing the third member (230) to a second portion (120) of a gas turbine engine. The latch mechanism further comprises a locking device comprising retaining means (251) configured to retain the latch mechanism (200) in its closed position.

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