CN218970893U

CN218970893U - Connecting structure between lock hooks of aircraft cabin door lock mechanism

Info

Publication number: CN218970893U
Application number: CN202222647271.9U
Authority: CN
Inventors: 王文浩; 高明亮; 张宇龙; 邓军锋
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2022-10-09
Filing date: 2022-10-09
Publication date: 2023-05-05
Anticipated expiration: 2032-10-09

Abstract

The application belongs to the aircraft hatch door lock mechanism latch hook connection structure design field, concretely relates to aircraft hatch door lock mechanism latch hook connection structure, include: the plurality of short shafts are correspondingly connected with one lock hook; the transmission shafts are connected between the two short shafts, are connected with one short shaft through a spline, and are connected with the other short shaft through a universal hinge, so that the lock hooks are connected in series.

Description

Connecting structure between lock hooks of aircraft cabin door lock mechanism

Technical Field

The application belongs to the field of aircraft cabin door lock mechanism lock hook connection structure design, and particularly relates to an aircraft cabin door lock mechanism lock hook connection structure.

Background

After the cabin door of the aircraft is closed, in order to ensure the reliable closing of the cabin door, a corresponding lock mechanism is designed, the lock mechanism is connected to the machine body, after the cabin door is closed, the lock hook is driven by the driving mechanism to move so as to hook a lock shaft connected to the cabin door, the cabin door is locked, and when the cabin door needs to be opened, the lock shaft is released by the movement of the lock hook driven by the driving mechanism, so that the cabin door can be opened.

In practice, in order to guarantee the reliability of locking the cabin door of the aircraft, design the locking mechanism and including a plurality of latch hooks, when locking the cabin door, each latch hook hooks the lock shaft at the same time, in addition, in order to simplify the structure and guarantee the cooperativity of each latch hook motion, only design a latch hook and actuating mechanism direct connection, other latch hooks are connected in series through the major axis with this latch hook, this kind of technical scheme has following defects:

under the condition that the machine body or the cabin door is subjected to external load and is greatly deformed, the long shaft can bear a large load, and under severe conditions, each lock hook can not smoothly hook and release the lock shaft, and even damage occurs.

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

It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present utility model, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been 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 inter-shackle connection arrangement that overcomes or alleviates at least one of the known technical drawbacks.

The technical scheme of the application is as follows:

an aircraft door lock mechanism inter-shackle connection structure comprising:

the plurality of short shafts are correspondingly connected with one lock hook;

the transmission shafts are connected between the two short shafts, are connected with one short shaft through a spline, and are connected with the other short shaft through a universal hinge, so that the lock hooks are connected in series.

According to at least one embodiment of the present application, in the above-mentioned connecting structure between lock hooks of an aircraft door lock mechanism, each transmission shaft is connected with its corresponding short shaft by a spline, specifically by an internal spline and an external spline.

According to at least one embodiment of the present application, in the above-mentioned connecting structure between the lock hooks of the aircraft door lock mechanism, each lock hook is provided with a connecting hole;

each connecting hole is sleeved on the corresponding short shaft.

According to at least one embodiment of the present application, in the above-mentioned connecting structure between lock hooks of an aircraft door lock mechanism, each short shaft is connected with a corresponding lock hook by a pin.

The application has at least the following beneficial technical effects:

the utility model provides a connection structure between aircraft hatch door lock mechanism latch hook, its design is realized the series connection to each latch hook in the aircraft hatch door lock mechanism with the cooperation of a plurality of minor axis and drive axle through spline, universal hinge, can the relative slip of spline along the axial to and with the deflection of universal hinge, compensate organism or hatch door's deformation in axial and radial, avoid bearing great load, and can guarantee the high-efficient transmission between each latch hook, make each latch hook cooperate the motion under the drive of actuating mechanism.

Drawings

Fig. 1 is a schematic view of a connection structure between latch hooks of an aircraft door lock mechanism according to an embodiment of the present disclosure;

FIG. 2 is a partial schematic view of FIG. 1;

wherein:

1-short axis; 2-latch hooks; 3-transmission shaft.

For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, 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 solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.

Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the utility model are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.

Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.

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

An aircraft door lock mechanism inter-shackle connection structure comprising:

a plurality of short shafts 1, wherein each short shaft 1 is correspondingly connected with one lock hook 2;

the transmission shafts 3 are connected between the two short shafts 1, are connected with one short shaft 1 through splines, and are connected with the other short shaft 1 through universal hinges, so that the lock hooks 2 are connected in series.

For the connection structure between the lock hooks of the aircraft cabin door lock mechanism disclosed in the above embodiment, those skilled in the art can understand that the connection structure is designed to realize the serial connection of each lock hook 2 in the aircraft cabin door lock mechanism by the cooperation of the spline and the universal hinge between the plurality of short shafts 1 and the transmission shaft 3, so that the relative sliding of the spline along the axial direction can be realized, and the deflection of the universal hinge can compensate the deformation of the machine body or the cabin door in the axial direction and the radial direction, so that the bearing of a larger load is avoided, the efficient transmission between each lock hook 2 can be ensured, and each lock hook 2 can cooperatively move under the driving of the actuating mechanism.

In some alternative embodiments, in the above-mentioned connection structure between the lock hooks of the cabin door lock mechanism, each transmission shaft 3 is connected to its corresponding stub shaft 1 by a spline, in particular by an internal spline and an external spline.

In some alternative embodiments, in the above-mentioned connection structure between the lock hooks of the cabin door lock mechanism, each lock hook 2 has a connection hole;

each connecting hole is sleeved on the corresponding short shaft 1.

In some alternative embodiments, in the above-mentioned connection structure between lock hooks of an aircraft door lock mechanism, each stub shaft 1 is connected with a corresponding lock hook 2 by a pin.

In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.

Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.

Claims

1. An aircraft door lock mechanism inter-shackle connection structure, comprising:

a plurality of short shafts (1), wherein each short shaft (1) is correspondingly connected with one lock hook (2);

the transmission shafts (3) are connected between the two short shafts (1), are connected with one short shaft (1) through splines, and are connected with the other short shaft (1) through universal hinges, so that the lock hooks (2) are connected in series.

2. The aircraft door lock mechanism inter-shackle connection structure according to claim 1, wherein,

each transmission shaft (3) is connected with the corresponding short shaft (1) through a spline, in particular to an internal spline and an external spline.

3. The aircraft door lock mechanism inter-shackle connection structure according to claim 1, wherein,

each latch hook (2) is provided with a connecting hole;

each connecting hole is sleeved on the corresponding short shaft (1).

4. An aircraft door lock mechanism inter-shackle connection according to claim 3, wherein,

the short shafts (1) are connected with the corresponding lock hooks (2) through pins.