CN115573625A - Aircraft cabin door lock mechanism - Google Patents

Abstract

The utility model belongs to the technical field of aircraft hatch lock mechanism design, concretely relates to aircraft hatch lock mechanism, it is in the lock state, when the unblock form, the locking arm, the dead point is crossed to the pin joint of articulated arm, can be with its stable maintenance in the lock state, the unblock state, and then can guarantee the dead reliability of lock to aircraft hatch door, and make aircraft hatch door open smoothly, furthermore, locking mechanism has integrateed on it, through the logic design to the part motion, only through the rotation of drive shaft, can realize in the lock state, the transform between the unblock state, compact overall structure, and convenient for operation.

Description

Aircraft cabin door lock mechanism

Technical Field

The application belongs to the technical field of design of airplane cabin door lock mechanisms, and particularly relates to an airplane cabin door lock mechanism.

Background

The cabin door locking mechanism is used for locking the cabin door of the airplane after the cabin door of the airplane is closed, and a corresponding locking structure is designed for ensuring the reliability of locking the cabin door after the cabin door is locked, so that the cabin door is reliably kept in a locking state by the locking mechanism.

Currently, the locking structure of an aircraft door lock mechanism mainly has the following two forms:

1) The technical scheme has the advantages that the spring or the actuator cylinder is used for applying resistance to the movement of the locking mechanism, so that the locking mechanism keeps the cabin door in a locked state;

2) The lock mechanism is limited by the lock key and keeps the cabin door in a locking state, and according to the technical scheme, the independent lock mechanism needs to be arranged to drive the lock key to move, so that the whole structure is complex, and the operation is complex.

The present application has been made in view of the above-mentioned technical drawbacks.

It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.

Disclosure of Invention

It is an object of the present application to provide an aircraft door lock mechanism to overcome or mitigate at least one of the technical disadvantages of the known prior art.

The technical scheme of the application is as follows:

an aircraft door lock mechanism comprising:

a lock shaft;

the fork lug rocker arm is connected to the lock shaft;

the lock latch is connected to the lock shaft;

the locking block is connected to the locking shaft and is provided with a locking groove;

a lock arm;

the locking pin is connected to the locking arm;

the articulated arm is articulated with the locking arm;

a drive arm;

a driving shaft connecting the articulated arm and the driving arm;

an aircraft door lock mechanism having:

in a locking state, after the cabin door of the airplane is closed, the driving shaft drives the hinged arm and the driving arm to swing, the driving arm is in contact with the fork ear rocker arm to drive the locking shaft to rotate, then the locking shaft is clamped into a fork ear of the fork ear rocker arm and then is separated from the fork ear, and the locking shaft is separated from the fork ear rocker arm; the driving arm drives the locking arm to swing, so that the locking pin slides in the locking groove and is in contact with the side wall of the locking groove to drive the locking block to swing, so that the locking shaft rotates, and after a hinge point of the locking arm and the hinge arm crosses a dead point, the latch is driven by the locking shaft to be inserted into a locking hole on an airplane cabin door and a lock hole on the airplane body to lock the airplane cabin door;

in an unlocking state, the driving shaft drives the articulated arm and the driving arm to swing; the driving arm drives the locking arm to swing, so that the locking pin slides in the locking groove and is separated from the side wall of the locking pin; the driving arm is contacted with the fork lug rocker arm to drive the lock shaft to rotate, then the lock shaft is clamped into the fork lug of the fork lug rocker arm, and then the lock shaft is separated from the fork lug and separated from the fork lug rocker arm; the lock pin contacts with the side wall of the lock groove to drive the lock block to swing, so that the lock shaft rotates, after the hinge point of the lock arm and the hinge arm crosses the dead point, the lock latch is driven by the lock shaft to be separated from the lock hole on the airplane cabin door and the airplane body, and the airplane cabin door can be opened.

According to at least one embodiment of the present application, in the aircraft door lock mechanism described above, the tip inner sides of the two side walls of the fork lug are inclined outward.

According to at least one embodiment of the present application, the aircraft door lock mechanism further includes:

the roller is connected to the driving arm, can contact with the fork lug rocker arm in the swinging process of the driving arm, rolls into the fork lug of the fork lug rocker arm, rolls out of the fork lug and is separated from the fork lug rocker arm.

According to at least one embodiment of the present application, in the aircraft door lock mechanism described above, the locking block is cam-shaped.

According to at least one embodiment of the present application, in the aircraft door lock mechanism described above, the locking groove has a sector shape.

The application has at least the following beneficial technical effects:

the utility model provides an aircraft hatch door latch mechanism, it is in the lock state, when the unblock form, the dead point is crossed to the pin joint of locking arm, articulated arm, can be with its stable maintenance in lock state, unblock state, and then can guarantee the reliability dead to the lock of aircraft hatch door, and make the aircraft hatch door open smoothly, furthermore, locking mechanical system has integrateed on it, through the logic design to the part motion, only through the rotation of drive shaft, can realize the transform between lock state, unblock state, overall structure is compact, and the simple operation.

Drawings

FIG. 1 is a schematic view of an aircraft door lock mechanism in a deadlocked state as provided by an embodiment of the present application;

FIG. 2 is a schematic view of an aircraft door lock mechanism provided in an embodiment of the present application in an unlocked state;

wherein:

1-locking the shaft; 2-a fork ear rocker arm; 3-a latch; 4-locking the block; 5-a locking arm; 6-a lock pin; 7-an articulated arm; 8-a drive arm; 9-a drive shaft; 10-roller.

For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.

Detailed Description

In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, and other related parts may refer to general designs, and in case of conflict, the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment.

In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.

Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.

The present application is described in further detail below with reference to fig. 1-2.

An aircraft door lock mechanism comprising:

a lock shaft 1;

the fork lug rocker arm 2 is connected to the lock shaft 1;

a latch 3 connected to the lock shaft 1;

the locking block 4 is connected to the locking shaft 1 and is provided with a locking groove;

a lock arm 5;

a locking pin 6 connected to the locking arm 5;

the hinged arm 7 is hinged with the locking arm 5;

a drive arm 8;

a driving shaft 9 connecting the articulated arm 7 and the driving arm 8;

an aircraft door lock mechanism has:

in a locking state, after the cabin door of the airplane is closed, the driving shaft 9 drives the hinged arm 7 and the driving arm 8 to swing, the driving arm 8 is in contact with the fork ear rocker arm 2 to drive the locking shaft 1 to rotate, and then the locking shaft is clamped into a fork ear of the fork ear rocker arm 2 and then is separated from the fork ear to be separated from the fork ear rocker arm 2; the driving arm 8 drives the locking arm 5 to swing, so that the locking pin 6 slides in the locking groove and is in contact with the side wall of the locking groove to drive the locking block 4 to swing, so that the locking shaft 1 rotates, and after the hinge point of the locking arm 5 and the hinge arm 7 crosses a dead point, the latch 3 is driven by the locking shaft 1 to be inserted into a locking hole on an airplane cabin door and a body to lock the airplane cabin door;

in an unlocking state, the driving shaft 9 drives the articulated arm 7 and the driving arm 8 to swing; the driving arm 8 drives the locking arm 5 to swing, so that the locking pin 6 slides in the locking groove and is separated from the side wall of the locking pin 6; the driving arm 8 is contacted with the fork lug rocker arm 2 to drive the lock shaft 1 to rotate, then is clamped into a fork lug of the fork lug rocker arm 2, then is separated from the fork lug, and is separated from the fork lug rocker arm 2; the lockpin 6 contacts with the lateral wall of locked groove, drives locking piece 4 swing, makes lock axle 1 rotate, after the pin joint of locking arm 5, articulated arm 7 crossed the dead point, and hasp 3 is deviate from the lockhole on aircraft hatch door, the organism under the drive of lock axle 1, and aircraft hatch door can be opened.

For the aircraft door lock mechanism disclosed in the above embodiment, it can be understood by those skilled in the art that the lock shaft 1 and the drive shaft 9 can be rotatably connected to the aircraft door, and the drive shaft 9 is connected to the drive handle, so that the aircraft door lock mechanism can be switched to a locked state by rotation of the drive handle after the aircraft door is closed, and can be switched to an unlocked state by rotation of the drive handle when the aircraft door needs to be opened.

For the aircraft door lock mechanism disclosed in the above embodiments, it can be further understood by those skilled in the art that when the aircraft door lock mechanism is in a locked state or an unlocked state, the hinge point of the lock arm 5 and the hinge arm 7 crosses the dead point, so that the aircraft door lock mechanism can be stably maintained in the locked state or the unlocked state, and further the reliability of locking the aircraft door can be ensured, and the aircraft door can be smoothly opened.

For the aircraft cabin door lock mechanism disclosed in the above embodiment, it can be further understood by those skilled in the art that a locking mechanism is integrated thereon, and through the logic design of the movement of the components, the conversion between the locked state and the unlocked state can be realized only through the rotation of the driving shaft 9, so that the aircraft cabin door lock mechanism has a compact overall structure and is convenient to operate.

In some alternative embodiments, the inner sides of the tips of the two side walls of the fork lug are inclined outwards in the aircraft door lock mechanism, so that the driving arm 8 can be easily snapped into and pulled out of the fork lug rocker arm 2 during swinging.

In some optional embodiments, the aircraft door lock mechanism further includes:

the gyro wheel 10 is connected on actuating arm 8, and at the actuating arm 8 swing in-process, can roll into the fork ear of fork ear rocking arm 2 with fork ear rocking arm 2 contact to and roll out from the fork ear, with fork ear rocking arm 2 separation, at this in-process, can effectually avoid taking place the jamming.

In some alternative embodiments, in the above-mentioned aircraft door lock mechanism, the locking piece 4 is in the shape of a cam protruding from the outer wall surface of the lock shaft 1.

In some alternative embodiments, in the aircraft door lock mechanism described above, the keyway is scalloped to provide sufficient space for the locking pin 6 to slide therein.

The embodiments are described in a progressive mode in the specification, the emphasis of each embodiment is on the difference from the other embodiments, and the same and similar parts among the embodiments can be referred to each other.

Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.

Claims (5)

1. An aircraft door lock mechanism, comprising:

a lock shaft (1);

the fork lug rocker arm (2) is connected to the lock shaft (1);

a latch (3) connected to the lock shaft (1);

the locking block (4) is connected to the locking shaft (1) and is provided with a locking groove;

a lock arm (5);

a locking pin (6) connected to the locking arm (5);

an articulated arm (7) articulated to the locking arm (5);

a drive arm (8);

a drive shaft (9) connected to the articulated arm (7) and the drive arm (8);

the aircraft door lock mechanism has:

in a locking state, after the door of the airplane is closed, the driving shaft (9) drives the hinged arm (7) and the driving arm (8) to swing, the driving arm (8) is in contact with the fork lug rocker arm (2) to drive the locking shaft (1) to rotate, then the locking shaft is clamped into a fork lug of the fork lug rocker arm (2), and then the locking shaft is separated from the fork lug and separated from the fork lug rocker arm (2); the driving arm (8) drives the locking arm (5) to swing, so that the locking pin (6) slides in the locking groove and is in contact with the side wall of the locking groove to drive the locking block (4) to swing, so that the locking shaft (1) rotates, and after a hinge point of the locking arm (5) and the hinge arm (7) crosses a dead point, the locking pin (3) is inserted into a locking hole on an airplane cabin door and a body under the driving of the locking shaft (1) to lock the airplane cabin door;

in an unlocked state, the driving shaft (9) drives the hinged arm (7) and the driving arm (8) to swing; the driving arm (8) drives the locking arm (5) to swing, so that the locking pin (6) slides in the locking groove and is separated from the side wall of the locking pin (6); the driving arm (8) is in contact with the fork lug rocker arm (2) to drive the lock shaft (1) to rotate, then is clamped into a fork lug of the fork lug rocker arm (2), then is separated from the fork lug, and is separated from the fork lug rocker arm (2); the lock pin (6) contacts with the side wall of the lock groove to drive the lock block (4) to swing, so that the lock shaft (1) rotates, after hinge points of the lock arm (5) and the hinge arm (7) cross dead points, the lock latch (3) is driven by the lock shaft (1) to be disengaged from lock holes on an airplane cabin door and an airplane body, and the airplane cabin door can be opened.

2. The aircraft door lock mechanism of claim 1,

the inner sides of the pointed ends of the two side walls of the fork lugs are inclined outwards.

3. The aircraft door lock mechanism of claim 1,

further comprising:

and the roller (10) is connected to the driving arm (8), and can be in contact with the fork lug rocker arm (2) in the swinging process of the driving arm (8), roll into a fork lug of the fork lug rocker arm (2), roll out of the fork lug and separate from the fork lug rocker arm (2).

4. The aircraft door lock mechanism of claim 1,

the locking block (4) is in a cam shape.

5. The aircraft door lock mechanism of claim 1,

the lock slot is fan-shaped.

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