CN218715972U

CN218715972U - Emergency separation bolt structure for airplane cabin door

Info

Publication number: CN218715972U
Application number: CN202222645498.XU
Authority: CN
Inventors: 张宇龙; 郭祥; 拜斌; 刘文光; 刘小飞
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2022-10-09
Filing date: 2022-10-09
Publication date: 2023-03-24
Anticipated expiration: 2032-10-09

Abstract

The application belongs to the technical field of the emergent bolt structural design that breaks away from of aircraft hatch door, concretely relates to emergent bolt structure that breaks away from of aircraft hatch door, include: the outer wall of the emergency bolt is provided with an annular bulge; one end of the emergency steel cable is connected to the emergency plug pin; and the spring is sleeved on the periphery of the emergency steel cable, and one end of the spring is abutted against the annular protrusion.

Description

Emergency separation bolt structure for airplane cabin door

Technical Field

The application belongs to the technical field of emergency separation bolt structure design of airplane cabin doors, and particularly relates to an emergency separation bolt structure of an airplane cabin door.

Background

The emergency separation operating handle of the airplane cabin door is arranged in the cockpit, and when a crisis condition occurs, the emergency separation operating handle is pulled by a driver to drive through the emergency steel cable, and the emergency bolt for closing the airplane cabin door is pulled open to separate the airplane cabin door, so that personnel on the airplane can jump and escape.

The current emergent bolt of closing aircraft hatch door adopts ordinary bolt mostly, does not have locking function, easily takes place to deviate from by the vibration, and can not break away from the back that operating handle pulled the perk in the emergency of aircraft cabin door in the aircraft cockpit, and the emergent operating handle that breaks away from of help aircraft cabin door resets, under the situation in the finite space in the cockpit, can cause serious interference to driver's the evacuation.

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 used for 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 in the case that there is no clear evidence 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 emergency release latch arrangement which overcomes or mitigates at least one aspect of the technical disadvantages known to exist.

The technical scheme of the application is as follows:

an aircraft door emergency disconnect latch structure comprising:

the outer wall of the emergency bolt is provided with an annular bulge;

one end of the emergency steel cable is connected to the emergency plug pin;

and the spring is sleeved on the periphery of the emergency steel cable, and one end of the spring is abutted against the annular protrusion.

According to at least one embodiment of the application, in the emergency release latch structure of the airplane door, the emergency latch is made of high-strength stainless steel.

According to at least one embodiment of the application, in the above structure of the emergency release latch for the airplane cabin door, an end of the emergency release latch is provided with a slot, and an outer wall of the emergency release latch is provided with a lock hole; the lock hole is communicated with the slot;

emergent bolt structure that breaks away from of aircraft hatch door still includes:

the adapter rod is made of low-strength stainless steel, one end of the adapter rod extends into the slot, the outer wall of the end is locked with the slot, and the end part of the other end of the adapter rod is provided with an adapter hole;

the lock pin is arranged in the lock hole and the lock groove;

the emergency steel cable extends into the switching hole towards the emergency bolt, and the switching hole shrinks to clamp the end of the emergency steel cable.

Drawings

Fig. 1 is a schematic view of an emergency release latch structure for an aircraft door according to an embodiment of the present disclosure;

fig. 2 is an assembly schematic view of an emergency release latch structure for an aircraft door provided in an embodiment of the present application;

wherein:

1-an emergency bolt; 2-emergency steel cable; 3-a spring; 4-a transfer lever; 5-a lock pin.

For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the 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 emergency disconnect latch structure comprising:

the outer wall of the emergency bolt 1 is provided with an annular bulge;

one end of the emergency steel cable 2 is connected to the emergency bolt 1;

and the spring 3 is sleeved on the periphery of the emergency steel cable 2, and one end of the spring is abutted to the annular protrusion.

For the aircraft cabin door emergency separation bolt structure disclosed by the embodiment, when the emergency separation bolt structure is applied specifically, the aircraft cabin door can be closed by the emergency bolt 1, the spring 3 is abutted between the annular protrusions and the machine body, one end, far away from the emergency bolt 1, of the emergency steel cable 2 is connected with an emergency separation operating handle of the aircraft cabin door in an aircraft cab, the spring 3 keeps the bolt 1 closed to the aircraft cabin door by virtue of elastic force, the bolt 1 has a locking function and is prevented from being separated by vibration, when a crisis condition occurs, the emergency separation operating handle is pulled by a driver, transmission is carried out by the emergency steel cable 2, the elastic force of the spring 3 is overcome, the emergency bolt 1 for closing the aircraft cabin door is pulled to separate the aircraft cabin door, people on the aircraft can jump and escape, after the emergency separation operating handle is loosened by the driver, the spring 3 is reset by virtue of the elastic force, the emergency separation operating handle is simultaneously driven to reset, and the emergency separation operating handle is prevented from being in a tilting state in the aircraft cabin and causing interference to the driver from the cabin.

In some alternative embodiments, in the above-mentioned structure of the emergency release latch for an aircraft door, the emergency latch 1 is made of high-strength stainless steel, has high strength, can bear large load, and can provide reliable connection performance.

In some optional embodiments, in the above-mentioned structure of the emergency release latch for an airplane door, an end of the emergency latch 1 has a slot, and an outer wall of the emergency latch has a lock hole; the lock hole is communicated with the slot;

the switching rod 4 is made of low-strength stainless steel, one end of the switching rod extends into the slot, the outer wall of the end is locked in the slot, and the end part of the other end of the switching rod is provided with a switching hole;

the lock pin 5 is arranged in the lock hole and the lock groove;

the emergency steel cable 2 extends into the switching hole towards the emergency bolt 1, and the switching hole shrinks to clamp the end of the emergency steel cable 2.

To the emergent bolt structure that breaks away from of aircraft hatch door that above-mentioned embodiment disclosed, technical personnel can understand in the field, its design is with the jumper bar 4 that low strength stainless steel made, the realization is to the emergent bolt 1 of making with high strength stainless steel, the connection between emergent cable wire 2, the jumper bar 4 is connected through 5 cooperation slots of lockpin, locked groove, lockhole between emergent bolt 1, the jumper bar 4 is connected through the form that the hole was received in the switching hole between emergent cable wire 2, connect reliably, and can guarantee smooth transition between overall structure.

In some alternative embodiments, in the above-mentioned aircraft door emergency release latch structure, the spring 3 is located at the periphery of the transit rod 4, and the transit rod 4 can provide a guide for the elastic expansion and contraction of the spring 3.

The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are 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

1. An emergency release latch structure for an aircraft door, comprising:

the emergency bolt (1) is provided with an annular bulge on the outer wall;

one end of the emergency steel cable (2) is connected to the emergency bolt (1);

and the spring (3) is sleeved on the periphery of the emergency steel cable (2), and one end of the spring is abutted against the annular protrusion.

2. The aircraft door emergency disconnect latch structure of claim 1,

the emergency bolt (1) is made of high-strength stainless steel.

3. The aircraft door emergency disconnect latch structure of claim 2,

the end part of the emergency bolt (1) is provided with a slot, and the outer wall of the emergency bolt is provided with a lock hole; the lock hole is communicated with the slot;

the emergency release latch structure for the aircraft door further comprises:

the adapter rod (4) is made of low-strength stainless steel, one end of the adapter rod extends into the slot, the outer wall of the end is locked with the slot, and the end part of the other end of the adapter rod is provided with an adapter hole;

the lock pin (5) is arranged in the lock hole and the lock groove;

the emergency steel cable (2) extends into the transfer hole towards the emergency bolt (1), and the end of the emergency steel cable (2) is clamped by the shrinkage of the transfer hole.