Aircraft door lock, aircraft door and aircraft having an aircraft door

Abstract

An aircraft door lock having a bolt and a closure block, wherein the bolt is fastened in a movable manner to a door leaf structure and the closure block can at least partially receive the bolt. The closure block prevents any movement of the bolt in at least one direction, wherein the closure block is arranged on a portion of a hinge arm that overlaps the door leaf structure when the door leaf structure is in a closed position. Furthermore, an aircraft door having such an aircraft door lock, and an aircraft having such an aircraft door are described.

Claims

1. An aircraft door lock comprising: a first bolt and a second bolt each configured to be rotationally fastened to a door leaf structure; and a closure block that is configured to receive the first bolt and the second bolt to prevent any movement of the first and second bolts in at least one direction, wherein the closure block is arranged on a portion of a hinge arm, wherein the portion of the hinge arm overlaps the door leaf structure when the door leaf structure is in a closed position, wherein the hinge arm has a first side facing the door leaf and a second side opposite the first side facing away from the door leaf, wherein the closure block is formed on the first side of the hinge arm facing the door leaf, wherein the closure block comprises a cavity in the hinge arm, wherein the cavity has a top wall; wherein the closure block comprises an opening and a boundary wall corresponding to the top wall of the cavity, wherein the opening is sized to receive the first bolt and the second bolt in the closure block, and wherein the boundary wall is arranged at an acute angle to an opening plane formed by the opening such the boundary wall angles upwardly from the opening towards a back of the cavity.

2. The aircraft door lock according to claim 1, wherein the bolt is configured to carry out a rotary movement in order to be partially received in the closure block.

3. The aircraft door lock according to claim 2, wherein, in order to carry out the rotary movement of the bolt, the aircraft door lock comprises: a rotation element, which is connected to the bolt for conjoint rotation; and an actuating rod, which is coupled to the rotation element in a manner spaced apart from the rotation element, wherein the actuating rod is configured to carry out a reciprocating movement about an axis of rotation of the rotation element such that the bolt is moved selectively between an open position, in which the bolt is not received in the closure block, and a locked position, in which the bolt is received in the closure block.

4. The aircraft door lock according to claim 2, wherein, in order to carry out the rotary movement of the bolt, the aircraft door lock comprises: a joint, to which the bolt is fastened in a rotatable manner; and an actuating rod, which is hinged to the bolt in a manner spaced apart from the joint, wherein the actuating rod is configured to carry out a reciprocating movement about a joint axis of the joint such that the bolt can be moved selectively between an open position, in which the bolt is not received in the closure block, and a locked position, in which the bolt received in the closure block.

5. The aircraft door lock according to claim 1, also comprising: a sliding device, which is arranged on the portion of the bolt that is received in the closure block.

6. An aircraft door comprising: a door leaf structure, which is configured to close an opening in an aircraft; a hinge arm, which is coupled to the door leaf structure and is configured to guide the door leaf structure between an open position and a closed position, in which the opening in the aircraft is closed by the door leaf structure; and an aircraft door lock according to claim 1.

7. The aircraft door according to claim 6, also comprising: a lifting mechanism, which is configured to move the door leaf structure in the closed position in a direction that differs from a direction of movement of the door leaf structure between the open position and the closed position.

8. The aircraft door according to claim 7, also comprising: at least one two-part door hinge, wherein a part of the door hinge is arranged on the door leaf structure and a further part of the door hinge is arranged on an aircraft structure surrounding the opening in the aircraft, wherein the lifting mechanism is also configured to move the door leaf structure such that the two parts of the door hinge are moved into an overlapping position and a free position.

9. The aircraft door according to claim 7, also comprising: a joint arrangement, which is arranged between the hinge arm and the door leaf structure and is configured to allow a first rotary movement of the door leaf structure relative to the hinge arm while the door leaf structure is guided between the open position and the closed position, and to allow a second movement, caused by the lifting mechanism, of the door leaf structure relative to the hinge arm, wherein the second movement exhibits a direction that is substantially parallel to an axis of rotation of the first rotary movement.

10. An aircraft having at least one aircraft door according to claim 6.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) In the following text, exemplary embodiments of the invention are described in more detail with reference to the drawings.

(2) FIG. 1 schematically shows a perspective illustration of an aircraft door,

(3) FIG. 2 schematically shows a perspective illustration of an aircraft door lock,

(4) FIG. 3 schematically shows a view of the aircraft door lock from FIG. 2,

(5) FIG. 4 schematically shows cross sections through an aircraft door lock along the section line A-A in FIG. 3 with different positions of a bolt and of a door leaf structure, and

(6) FIG. 5 schematically shows an aircraft with an aircraft door.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

(7) According to the present invention, an aircraft door lock having a closure block arranged on a hinge arm is described. Furthermore, an aircraft door and an aircraft having such an aircraft door lock are described.

(8) FIG. 5 shows, for example, a vehicle in the form of an aircraft 10, while FIG. 1 schematically shows a perspective illustration of an aircraft door 20, which closes an opening in an aircraft fuselage structure 11. The aircraft door 20 is illustrated from an aircraft interior in FIG. 1. On the aircraft fuselage structure 11, it is possible for parts of door hinges 22 and a hinge arrangement 30 to be provided, these allowing a door leaf structure 21 to be opened and closed. The hinge arrangement 30 can have a hinge arm 31, which is connected, on the right in FIG. 1, to an aircraft fuselage structure 11 in an articulated manner. On an opposite side of the hinge arm 31, the latter can be coupled to the door leaf structure 21. In this case, the hinge arm 31 is configured to guide the door leaf structure 21 between an open position and a closed position, shown in FIG. 1, in which the opening in the aircraft 10 is closed.

(9) The aircraft door 20 additionally has an aircraft door lock 100. The aircraft door lock 100 can be located between an interior of the door leaf structure 21 and the hinge arm 31.

(10) FIG. 2 schematically shows a perspective illustration of an aircraft door lock 100, which has a bolt 101, which is configured to be fastened in a movable manner to the door leaf structure 21. In the variant of the aircraft door lock 100 that is illustrated in FIG. 2, the aircraft door lock 100 has a rotation element 103, which is connected to the bolt 101 for conjoint rotation. Alternatively, the bolt 101 is fastened to a joint 103 in a rotatable manner. In both cases, the bolt 101 can carry out a rotary movement relative to the door leaf structure 21.

(11) The aircraft door lock 100 also has a closure block 110, which is configured to at least partially receive the bolt 101. In this case, the closure block 110 prevents any movement of the bolt 101 in at least one direction. The direction in which the closure block 110 prevents the movement of the bolt 101 is upward in FIG. 2, in the direction of the rotation element/joint 103, as is apparent, in particular, from the illustrations in FIGS. 3 and 4. Thus, FIG. 3 schematically shows a view of the aircraft door lock 100 from FIG. 2 and FIG. 4 schematically shows a cross section through an aircraft door lock along the section line A-A in FIG. 3.

(12) The closure block 110 is arranged on a portion of the hinge arm 31, wherein the portion of the hinge arm 31 overlaps the door leaf structure 21 when the door leaf structure 21 is in its closed position. This overlap, illustrated, in particular, in FIG. 1, relates to an arrangement of the hinge arm 31 in a parallel manner in front of the door leaf structure 21. As is apparent from FIG. 4, this overlap can also comprise the location in one another (above one another) of some parts of the door leaf structure 21 and of the hinge arm 31 or at least of the closure block 110 in a viewing direction perpendicular to a main plane of the door leaf structure 21. Thus, it is possible, for example, for the hinge arm 31 to be located within a fictitious body that is defined by the outer limits of the door leaf structure 21. Thus, a very compact aircraft door 20 can be achieved.

(13) The closure block 110 can be in the form of a cavity in the hinge arm 31. In this case, an opening 111 into the cavity faces the door leaf structure 21 such that the bolt 101, coming from the door leaf structure 21, can be received at least partially in the cavity. A boundary wall 111 of the cavity, in this case a top of the cavity, limits movement of the bolt 101. The boundary wall 111 preferably exhibits an angle to an opening plane formed by the opening 112. As a result, the bolt 101 can be guided next to (in this case under) the boundary wall 111 and be blocked by the boundary wall 111 in at least one direction. Therefore, the cavity does not need to be downwardly closed but can also be in the form of a cutout in an underside of the hinge arm 31. Of course, it is also possible for only an underside of the hinge arm 31 to act as a boundary wall 111, without a cavity or a cutout being provided.

(14) The bolt 101 can be configured as a pin (not illustrated), which engages in the closure block 110 (is moved into and out of the opening) in a linear manner along a longitudinal axis of the pin. Alternatively, the bolt 101, as illustrated in FIGS. 2 to 4, can carry out a rotary movement by the rotation element or about the joint 103, wherein at least one portion of the bolt 101 can be brought into an overlapping position (for example into engagement) with the closure block 110 formed by the cavity and the boundary wall 111. For this purpose, a roller 102 or some other protrusion is provided on the illustrated bolt 101, the roller 102 or protrusion being able to be guided into the closure block 110 through the opening 112.

(15) Whereas, for a linearly guided bolt (not shown), an opening 112 having a shape corresponding to the bolt cross section is sufficient, for the rotatably mounted bolt 101, an L-shaped or T-shaped opening 112 is more suitable. As a result, the roller is introduced into the cavity in the closure block 110 together with a portion of the rest of the bolt 101, while one side of the roller or of the protrusion corresponds to a leg of the L-shaped or T-shaped opening 112 (i.e., of the boundary wall 111).

(16) In FIG. 4, different states of the aircraft door lock 100 from a locked position to an open position are illustrated from top to bottom. In the locked position illustrated at the top, the bolt 101 is prevented from moving upward by the closure block 110, in particular the boundary wall 111. Since the bolt 101 is fastened to the door leaf structure 21, the door leaf structure 21 is also prevented from moving upward. Therefore, the door leaf structure 101 is locked.

(17) For unlocking, the bolt 101 is released from the closure block 110. For this purpose, the bolt 101 is pivoted by the rotation element or about the joint 103 such that the roller 102 or other protrusion no longer overlaps the boundary wall 111.

(18) The pivoting of the bolt 101 can comprise an actuating rod 104, which is coupled to the rotation element 103 in a manner spaced apart from the rotation element 103. In this case, the actuating rod 104 is configured to carry out a reciprocating movement about an axis of rotation of the rotation element 103. As a result of this reciprocating movement, the rotation element 103 is rotated about an axis of rotation. The bolt 101 fastened thereto is thus likewise rotated.

(19) Alternatively, for pivoting the bolt 101, an actuating rod 104 can be hinged to the bolt 101 in a manner spaced apart from the joint 103. Likewise alternatively, an actuator (not shown) can be provided at the joint 103 or instead of the joint 103, the actuator rotating the bolt 101 about an axis (corresponding to an axis of rotation of the rotation element 103) between the two positions illustrated in FIG. 4.

(20) The now released bolt 101 also allows the door leaf structure 21 to move upward, as is shown at the bottom in FIG. 4, and the movement of the door leaf structure 21 is indicated by a double arrow. The door leaf structure 21 can be raised and lowered for example by a lever 32 (FIG. 1) and a lifting mechanism attached thereto. For this movement of the door leaf structure 21, various mechanisms can be provided. For example, via the lever 32, a push rod 121 can be actuated, which moves the door leaf structure 21 relative to the hinge arm 31. For this purpose, the lever 32 can be fastened in a rotatable manner to the hinge arm 31, such that the lever 32 is supported on the hinge arm 31 and moves the door leaf structure 21 relative thereto (upward and downward).

(21) For this purpose, it is also possible for a joint arrangement 120 to be arranged between the hinge arm 31 and the door leaf structure 21. This joint arrangement 120 allows a first rotary movement B1 of the door leaf structure 21 relative to the hinge arm 31, for example while the door leaf structure 21 is being guided between the open position and the closed position, and also allows a second movement B2, caused by the lifting mechanism 32, of the door leaf structure 21 relative to the hinge arm 31. In this case, the second movement exhibits a direction that is substantially parallel to an axis of rotation D (FIG. 3) of the first rotary movement B1. The first rotary movement B1 is optional and relates primarily to a movement of the hinge arm 31 relative to the aircraft fuselage structure 11.

(22) As a result of the door leaf structure 21 being lifted relative to the hinge arm 31, the door hinges 22 are brought into a free position. In other words, the parts of the door hinges 22 that are arranged on the door leaf structure 21 are moved into a free position from a position overlapping the parts of the door hinges 22 that are arranged on the aircraft fuselage structure 11. Subsequently, the door leaf structure 21 can be pivoted by the hinge arm 31 and open up the opening in the aircraft fuselage structure 11.

(23) The variants, configurations and exemplary embodiments outlined above serve merely to describe the claimed teaching, but do not limit the latter to the variants, configurations and exemplary embodiments.

(24) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.