Method for arming/disarming an aircraft door evacuation slide and implementation mechanism

Patent metadata

Field	Value
Publication number	US-9783311-B2
Application number	US-201414897330-A
Country	US
Kind code	B2
Filing date	Jun 13, 2014
Priority date	Jun 14, 2013
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

The objective of the invention is to replace the rope bar of the door evacuation slide with individual connections. According to a preferred embodiment, the mechanism for arming/disarming an aircraft door evacuation slide ( 1, 15, 16 ) includes two releasable connectors ( 21 ) disposed to either side of the base of the door and each includes two half connectors ( 21 s, 21 i ), a so-called upper half connector ( 21 s, 41, 4 a, 42 ) rigidly connected to the door ( 1 ) and having an attachment device ( 33 ) for attachment to the slide, and a so-called lower half connector ( 21 i ) fixed to the cabin floor ( 6 ). Each upper half connector ( 21 s ) includes a movable inner part controlled by a ring ( 43 ) and housed in the corresponding lower half-connector ( 21 i ). The mechanism can also include an electric motor coupled to two rods ( 31 ), each rod ( 31 ) being capable of rotating the control ring ( 43 ) of each upper half connector ( 21 s ) between two angular positions: an armed position and a disarmed position.

First claim

The invention claimed is:

1. A method for arming mode and disarming mode of an evacuation slide ( 3 ) of an aircraft door ( 1 ) connected to a cabin floor ( 6 ) of the aircraft, the method comprising:
activating the arming mode (ARM) for lowering the aircraft door ( 1 ) into a closed position to engage half connectors ( 21 s , 21 i ; 22 s , 22 i ) forming at least two releasable connections ( 21 , 22 ) coaxial with an axis perpendicular to the cabin floor ( 6 );
rigidly connecting the half connectors ( 21 s , 21 i ; 22 s , 22 i ) of each connection ( 21 , 22 ) to the door ( 1 ) and to the cabin floor ( 6 ), respectively;
locking the connections ( 21 , 22 ) by driving, using a locking motion (T 1 , R 1 ) triggered by a control ( 51 ) of an energy source ( 23 );
wherein said locking step includes driving in rotation (R 2 ) about the axis of each connection ( 21 , 22 ) induced by driving in translation (T 2 ) by coupling with the energy source ( 23 ) until a configuration is reached locking the connections ( 21 , 22 );
wherein in the event of an emergency evacuation, unfurling and inflating the evacuation slide ( 3 ) attached only to each connection ( 21 , 22 ), and the disarming mode (DISARM) unlocking said connections by a mechanically driven reverse motion (T 2 , R 2 ) and then raising the door ( 1 ) to decouple the connections ( 21 , 22 ) before opening the door.

2. The method as claimed in claim 1 , wherein the connecting parts ( 21 i , 22 i ) are rigidly connected to the cabin floor ( 6 ) form extensions emerging from the floor ( 6 ).

3. The method as claimed in claim 1 , wherein the connecting parts ( 21 s , 21 i ; 22 s , 22 i ) are aligned during the lowering of the door ( 1 ) by fixing the connecting parts ( 21 s , 22 s ) rigidly connected to the door ( 1 ) via an elastic joint ( 45 ).

4. The method as claimed in claim 1 , wherein the driving in rotation (R 1 , R 2 ) causes pivoting of a mobile subassembly ( 72 ) of one of the parts ( 21 s , 22 s ) of each connection ( 21 , 22 ) between two angular positions (Ad, Aa), a locking position in which the subassembly ( 72 ) is arranged in a housing ( 10 ) of the other part ( 21 i , 22 i ) in accordance with a locking configuration and a releasable position in which the subassembly ( 72 ) and the housing ( 10 ) have complementary configurations.

5. A mechanism for at least one of arming and disarming an evacuation slide ( 3 ) of an aircraft door ( 1 ) connected to a cabin floor ( 6 ) of the aircraft comprising:
two releasable connectors ( 21 , 22 ) disposed on respective opposite sides of a bottom ( 1 i ) of the aircraft door ( 1 ) and each releasable connector including an upper half-connectors ( 21 s, 22 s ) and a lower half connector ( 21 i , 22 ), the upper half connector and the lower half connector are coaxial with an axis perpendicular to the cabin floor, the upper half-connector ( 21 s , 22 s ) is rigidly connected to the door ( 1 ) and includes an attachment device ( 33 ) to attach to the evacuation slide ( 3 ), the lower half-connector ( 21 i , 22 i ) is fixed to the cabin floor ( 6 ) and to a latch ( 7 ) for locking and unlocking the upper half-connector ( 21 s , 22 s ) and the lower half-connector ( 21 i , 22 i ), each latch ( 7 ) includes a part mobile ( 72 ) in rotation about the axis of the half-connectors ( 21 s , 22 s ; 21 i , 22 i ) and is adapted house in the corresponding lower half-connector ( 21 i , 22 i ), and
wherein the mechanism ( 2 ) further includes:
an energy source ( 23 ) coupled to two links ( 31 , 32 ), each link ( 31 , 32 ) adapted to move in translation parallel to the floor by the energy source ( 23 ) to drive the mobile part ( 72 ) of a latch ( 7 ) in rotation (R 1 , R 2 ) between two angular positions:
an angular position (Aa) locking the locking configuration of the walls ( 91 ) of a base ( 9 b ) of the corresponding lower half-connector ( 21 i , 22 i ), and
a releasable angular position (Ad) of complementary configuration of the walls ( 72 a , 91 ) of said part ( 72 ) and said base ( 9 b ).

6. The mechanism as claimed in claim 5 , wherein each lower half-connector ( 21 i , 22 i ) is a threshold fitting that includes a base ( 8 ) adapted to fix to the floor ( 6 ), the base ( 8 ) resting on the floor ( 6 ) so that no cavity is formed between the base ( 8 ) and the floor ( 6 ).

7. The mechanism as claimed in claim 5 , wherein each lower half-connector ( 21 i , 22 i ) has an upper end ( 9 ) of globally conical shape having walls forming shoulders ( 91 ) that extend radially to form the base ( 9 b ) and between the upper end ( 9 ) and the base ( 8 ), a cylindrical intermediate portion ( 10 ) radially smaller than the shoulders ( 91 ) and adapted to form with the upper end ( 9 ) a housing for the mobile part ( 72 ) of the corresponding latch ( 7 ).

8. The mechanism as claimed in claim 5 , wherein each upper half-connector ( 21 s , 22 s ) includes a pillar ( 42 ) adapted to mount perpendicularly to the floor ( 6 ) in an arm ( 41 , 41 a ) for fixing the upper half-connector to the door ( 1 ) and a control ring ( 43 ) mobile in rotation mounted on the pillar ( 42 ) and connected to the links ( 31 , 32 ), and each locking and unlocking latch ( 7 ) are mounted on the pillar ( 42 ) and includes a casing ( 71 ) and the links ( 31 , 32 ) drive the mobile part ( 72 ) by the control ring ( 43 ).

9. The mechanism as claimed in claim 8 , wherein the mobile internal part ( 72 ) and the control ring ( 43 ) are coupled via connections by lugs ( 43 e ) and notches ( 72 e ).

10. The mechanism as claimed in claim 8 , wherein the pillar ( 42 ) is mounted in the arm ( 41 , 41 a ) via an elastic joint ( 45 ) adapted to absorb misalignments between the two half-connectors ( 21 s , 21 i ; 22 s , 22 i ).

11. The mechanism as claimed in claim 8 , wherein position sensors ( 47 , 48 ) are mounted on the mobile control ring ( 43 ) to determine the angular position (Aa, Ad) of said ring ( 43 ) and to deduce from the position of the latches ( 7 ) and the armed and disarmed status of the evacuation slide ( 3 ).

12. The mechanism as claimed in claim 8 , wherein the casing ( 71 ) of the latch ( 7 ) includes pins ( 33 ) for attaching the evacuation slide ( 3 ).

13. The mechanism as claimed in claim 8 , wherein the casing ( 71 ) of the latch ( 7 ) includes a cylindrical internal wall ( 73 ) forming a face ( 73 a ) for centering the threshold fitting ( 21 i , 22 i ).

14. The mechanism as claimed in claim 11 , wherein each mobile internal part ( 72 ) is provided with a target ( 72 c ) for the position sensors ( 47 , 48 ) of the latch ( 7 ).

15. The mechanism as claimed in claim 14 , wherein the target ( 72 c ) of the mobile internal parts ( 72 ) forms a pull-tab that is maneuvered to arm and disarm the evacuation slide ( 3 ) in the event of failure of an electric motor ( 23 ) used as an energy source.

16. The mechanism as claimed in claim 15 , wherein the motor ( 23 ) is a bistable electrical actuator of solenoid type.

17. The mechanism as claimed in claim 5 , wherein an indicator lamp ( 5 a , 5 b ) informing the operator of the armed and the disarmed status of the aircraft door and a door computer ( 14 ) manage the arming and disarming angular positions (Aa, Ad) of the upper half-connectors ( 21 s , 22 s ).

18. The aircraft comprising a door ( 1 ) equipped with two upper half-connectors ( 21 s , 22 s ), latches ( 7 ), and an energy so

Assignees

• Latecoere

Inventors

• Bessettes Cyrille
• Buchet Damien
• Othomene Renaud

Classifications

• B64D25/14 Primary

  Inflatable escape chutes · CPC title

• B64C1/1407

  Doors; surrounding frames · CPC title