Aircraft door with additional safety lift
Aircraft door ( 1 ) having: an opening panel ( 2 ) provided with engagement abutments ( 26 ); a frame ( 3 ) intended to be attached to the fuselage ( 4 ) of the aircraft and including engagement counter-abutments ( 27 ); a hinge arm ( 5 ); a lifting lever ( 10 ); and a rotary control lever ( 20 ) which can be operated in a disengagement direction in order to unlock the opening panel ( 2 ). The door includes a one-way operating rod ( 18 ) which connects the control lever ( 20 ) to the lifting lever ( 10 ) and is designed to drive the lifting lever ( 10 ) only when the control lever ( 20 ) is actuated in the direction of disengagement.
1. An aircraft door ( 1 ) comprising:
an opening panel ( 2 ) provided with engagement abutments ( 26 );
a frame ( 3 ) intended to be fixed to the fuselage ( 4 ) of the aircraft and comprising engagement counter-abutments ( 27 );
a hinge arm ( 5 ) supporting the opening panel ( 2 ) with respect to the frame ( 3 ) and guiding the opening panel ( 2 ) between a closed position in which the opening panel ( 2 ) is in the frame ( 3 ) and an open position in which the opening panel ( 2 ) is open and positioned facing the fuselage of the aircraft, freeing the opening of the frame ( 3 );
a disengagement handle to drive in rotation a rotary control lever ( 20 ) that actuated in a direction of disengagement to unlock the opening panel ( 2 );
the aircraft door comprising:
a lifting lever ( 10 ) linking the hinge arm ( 5 ) to the opening panel ( 2 ), the lifting lever ( 10 ) being driven by the control lever ( 20 ) when the control lever ( 20 ) is actuated in order to unlock the opening panel ( 2 ), the lifting lever ( 10 ) guiding the opening panel ( 2 ) between a low position of engagement in which the engagement abutments ( 26 ) of the opening panel ( 2 ) are arranged against the engagement counter-abutments ( 27 ) of the frame ( 3 ), and a high position of disengagement in which the engagement abutments ( 26 ) of the opening panel ( 2 ) are disengaged from the engagement counter-abutments ( 27 ) by a lifting motion;
a one-way operating link ( 18 ) linking the control lever ( 20 ) to the lifting lever ( 10 ) so that the rotation of the control lever ( 20 ) in the direction of disengagement drives the pivoting of the lifting lever ( 10 ) and the lifting of the opening panel ( 2 ) with respect to the frame ( 3 ), from the low position of engagement to the high position of disengagement, the one-way operating link ( 18 ) being designed to drive the lifting lever ( 10 ) only when the control lever ( 20 ) is actuated in the direction of disengagement;
wherein the lifting lever ( 10 ) is mounted to pivot on the hinge arm ( 5 ) by a first pivot ( 14 ) at one of its ends, and is also mounted to pivot on the opening panel ( 2 ) on a second pivot ( 22 ); and
wherein the one-way operating link ( 18 ) is attached to the lifting lever ( 10 ) outside of the portion of the lifting lever ( 10 ) situated between the first pivot ( 14 ) and the second pivot ( 22 ).
2. The aircraft door as claimed in claim 1 , further comprising a one-way guideway link ( 17 ) between the one-way operating link ( 18 ) and the lifting lever ( 10 ), the one-way guideway link ( 17 ) comprising an abutment ( 19 ) and allowing:
the one-way operating link ( 18 ) to slide in the one-way guideway link ( 17 ) when the lifting lever ( 10 ) is displaced toward the control lever ( 20 ); and
the lifting lever ( 10 ) to be driven by the abutment ( 19 ) when the control lever ( 20 ) is actuated in the direction of disengagement.
3. The aircraft door as claimed in claim 1 , wherein the one-way operating link ( 18 ) cooperates with a ball joint ( 16 ) mounted on the lifting lever ( 10 ).
4. The aircraft door as claimed in claim 1 , wherein the control lever ( 20 ) is mounted to rotate on the opening panel ( 2 ) on an axis ( 21 ).
5. The aircraft door as claimed in claim 1 , wherein the one-way operating link ( 18 ) is attached to the end of the lifting lever ( 10 ) opposite the first pivot ( 14 ).
6. The aircraft door as claimed in claim 1 , wherein the end of the lifting lever ( 10 ) opposite the first pivot ( 14 ) is attached to a spring ( 29 ) for compensating the weight of the opening panel ( 2 ).
7. The aircraft door as claimed in claim 6 , wherein the spring ( 29 ) is linked to the opening panel ( 2 ).
8. The aircraft door as claimed in claim 1 , further comprising two lifting levers ( 10 ), the one-way operating link ( 18 ) being attached to one of these two lifting levers ( 10 ).
9. An aircraft door ( 1 ) comprising:
an opening panel ( 2 ) provided with engagement abutments ( 26 );
a frame ( 3 ) intended to be fixed to the fuselage ( 4 ) of the aircraft and comprising engagement counter-abutments ( 27 );
a hinge arm ( 5 ) supporting the opening panel ( 2 ) with respect to the frame ( 3 ) and guiding the opening panel ( 2 ) between a closed position in which the opening panel ( 2 ) is in the frame ( 3 ) and an open position in which the opening panel ( 2 ) is open and positioned facing the fuselage of the aircraft, freeing the opening of the frame ( 3 );
a disengagement handle to drive in rotation a rotary control lever ( 20 ) that actuated in a direction of disengagement to unlock the opening panel ( 2 );
the aircraft door comprising:
a lifting lever ( 10 ) linking the hinge arm ( 5 ) to the opening panel ( 2 ), the lifting lever ( 10 ) being driven by the control lever ( 20 ) when the control lever ( 20 ) is actuated in order to unlock the opening panel ( 2 ), the lifting lever ( 10 ) guiding the opening panel ( 2 ) between a low position of engagement in which the engagement abutments ( 26 ) of the opening panel ( 2 ) are arranged against the engagement counter-abutments ( 27 ) of the frame ( 3 ), and a high position of disengagement in which the engagement abutments ( 26 ) of the opening panel ( 2 ) are disengaged from the engagement counter-abutments ( 27 ) by a lifting motion;
a one-way operating link ( 18 ) linking the control lever ( 20 ) to the lifting lever ( 10 ) so that the rotation of the control lever ( 20 ) in the direction of disengagement drives the pivoting of the lifting lever ( 10 ) and the lifting of the opening panel ( 2 ) with respect to the frame ( 3 ), from the low position of engagement to the high position of disengagement, the one-way operating link ( 18 ) being designed to drive the lifting lever ( 10 ) only when the control lever ( 20 ) is actuated in the direction of disengagement;
a device for immobilizing the control lever ( 20 ) when the door is in open position.
10. An aircraft door ( 1 ) comprising:
an opening panel ( 2 ) provided with engagement abutments ( 26 );
a frame ( 3 ) intended to be fixed to the fuselage ( 4 ) of the aircraft and comprising engagement counter-abutments ( 27 );
a hinge arm ( 5 ) supporting the opening panel ( 2 ) with respect to the frame ( 3 ) and guiding the opening panel ( 2 ) between a closed position in which the opening panel ( 2 ) is in the frame ( 3 ) and an open position in which the opening panel ( 2 ) is open and positioned facing the fuselage of the aircraft, freeing the opening of the frame ( 3 );
a disengagement handle to drive in rotation a rotary control lever ( 20 ) that actuated in a direction of disengagement to unlock the opening panel ( 2 );
the aircraft door comprising:
a lifting lever ( 10 ) linking the hinge arm ( 5 ) to the opening panel ( 2 ), the lifting lever ( 10 ) being driven by the control lever ( 20 ) when the control lever ( 20 ) is actuated in order to unlock the opening panel ( 2 ), the lifting lever ( 10 ) guiding the opening panel ( 2 ) between a low position of engagement in which the engagement abutments ( 26 ) of the opening panel ( 2 ) are arranged against the engagement counter-abutments ( 27 ) of the frame ( 3 ), and a high position of disengagement in which the engagement abutments ( 26 ) of the opening panel ( 2 ) are disengaged from the engagement counter-abutments ( 27 ) by a lifting motion;
a one-way operating link ( 18 ) linking the control lever ( 20 ) to the lifting lever ( 10 ) so that the rotation of the control lever ( 20 ) in the direction of disengagement drives the pivoting of the lifting lever ( 10 ) and the lifting of the opening panel ( 2 ) with respect to the frame ( 3 ), from the low position of engagement to the high position of disengagement, the one-way operating link ( 18 ) being designed to drive the lifting lever ( 10 ) only when the control lever ( 20 ) is actuated in the direction of disengagement; and
wherein the one-way operating link ( 18 ) comprises a rod ( 30 ) provided at one of its ends a pivot ( 33 ) linked to the control lever ( 20 ), and provided at the other of its ends with an abutment ( 19 ), a ball joint ( 16 ) being mounted on a friction ring ( 31 ) sliding along the rod ( 30 ).