CN218953042U

CN218953042U - Error unlocking prevention device for aircraft cabin cover lock system

Info

Publication number: CN218953042U
Application number: CN202223053682.1U
Authority: CN
Inventors: 池信国; 蔡毅; 应超; 万里鹏; 林雷; 邵翔翔; 温爱鹏; 陈瑞达
Original assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Current assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Priority date: 2022-11-17
Filing date: 2022-11-17
Publication date: 2023-05-02
Anticipated expiration: 2032-11-17

Abstract

The anti-misoperation unlocking device of the aircraft cabin cover lock system comprises a rocker arm, a connecting rod, a damping mechanism and a bracket, wherein the damping mechanism comprises a push rod, a spring and a base, and the rocker arm is installed on a main shaft of an in-aircraft unlocking handle; one end of the connecting rod is connected with the rocker arm, the other end of the connecting rod is connected with the ejector rod of the damping mechanism, a column body is arranged on the base, the ejector rod capable of moving in the column body is embedded in the column body, one end of the spring is sleeved on the ejector rod embedded in the column body, and the other end of the spring is fixed at the bottom of the column body; the base is fixed on the machine body mechanism through a bracket; the spring force is utilized to enable the ejector rod to push against the rocker arm through the connecting rod, and along with the rotation of the rocker arm, the spring force is gradually increased, the possibility of unexpected unlocking is further reduced, unexpected unlocking of the canopy lock system under the condition of large heading positive overload can be prevented, the flight safety is effectively improved, and the novel lock has the characteristics of simple structure, easiness in processing, reliability in working and convenience in use and maintenance.

Description

Error unlocking prevention device for aircraft cabin cover lock system

Technical Field

The utility model relates to the technical field of aircraft system structures, in particular to an error unlocking prevention device for an aircraft cabin cover lock system.

Background

The function of the canopy lock system is to securely lock the canopy to the fuselage structure, bear simultaneous transfer of canopy loads, and ensure that accidental unlocking does not occur under various flight conditions. Therefore, the stable locking of the lock system and the guarantee that unexpected unlocking cannot occur in the flying process are key to the design of the lock system. The lock mechanism used for executing locking in the lock system used at present adopts the self-locking design like hook type lock, latch type lock, lockpin and the like generally, and unlocking can not appear when bearing the canopy load, but the lock pull rod that connects each lock mechanism is drive part, and its own exists weight, has certain course overload force in the flight to easily lead to probably appearing the motion in the flight and then unexpected drive lock mechanism unblanking, cause the canopy unexpected to open for the protection function of canopy is lost, and the pilot receives the air current blowing, influences aircraft flight safety.

At present, most of aircraft canopy lock systems are longitudinally arranged, and when the heading is greatly overloaded, the lock systems have the possibility of unexpected unlocking, so that flight safety is endangered.

Disclosure of Invention

The technical problem solved by the utility model is to provide an error unlocking prevention device for an aircraft cabin cover lock system, so as to solve the problems in the background technology.

The technical problems solved by the utility model are realized by adopting the following technical scheme:

the utility model provides an aircraft cabin cover lock system prevents mistake unlocking means, includes rocking arm, connecting rod, damping mechanism and support, wherein, damping mechanism includes ejector pin, spring and base, the rocking arm is installed on the main shaft of the interior unlocking handle of machine, is connected to the lock system through the main shaft, makes rocking arm and interior unlocking handle synchronous rotation, connecting rod one end is connected with the rocking arm, the connecting rod other end is connected with damping mechanism's ejector pin, be provided with the cylinder on the base, the embedding has ejector pin that can move in the cylinder, spring one end suit is on the ejector pin in the embedding cylinder, the spring other end is fixed in the cylinder bottom; the base is fixed on the machine body mechanism through a bracket.

In the utility model, one end of the rocker arm is provided with a mounting hole for mounting with the main shaft, and the other end of the rocker arm is provided with an opening hole for connecting with the connecting rod.

In the utility model, the two ends of the connecting rod are respectively provided with a pin hole for installing a cotter pin, and the rocker arm and the ejector rod are connected through the cotter pin.

In the utility model, the upper end of the ejector rod is provided with a mounting hole for mounting the cotter pin.

In the utility model, the column body and the base are of an integral structure.

The beneficial effects are that: the damping mechanism fixedly connected with the machine body mechanism is internally provided with the spring, the ejector rod is urged to prop against the rocker arm through the connecting rod by utilizing the action of the spring force, the spring force is gradually increased along with the rotation of the rocker arm, the possibility of unexpected unlocking is further reduced, the unexpected unlocking of the canopy lock system under the condition of larger heading positive overload can be prevented, the flight safety is effectively improved, and the cabin cover lock system has the characteristics of simple structure, easiness in processing, reliability in working and convenience in use and maintenance.

Drawings

Fig. 1 is a schematic structural view of a preferred embodiment of the present utility model.

FIG. 2 is a schematic view of a damping mechanism according to a preferred embodiment of the present utility model.

FIG. 3 is a schematic diagram of a preferred embodiment of the present utility model.

Detailed Description

The utility model is further described with reference to the following detailed drawings in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the implementation of the utility model easy to understand.

Referring to fig. 1-2, an error unlocking prevention device of an aircraft cabin cover lock system comprises a rocker arm 1, a connecting rod 2, a damping mechanism 3 and a bracket 4, wherein the rocker arm 1 is arranged on a main shaft of an in-machine unlocking handle, is connected to a lock system through the main shaft to enable the rocker arm 1 and the in-machine unlocking handle to synchronously rotate, and the connecting rod 2 is used for connecting the rocker arm 1 and the damping mechanism 3; the damping mechanism 3 comprises a push rod 31, a spring 32 and a base 33, wherein the push rod 31 is embedded into a column body arranged on the base 33, one end of the spring 32 is sleeved on the push rod 31 embedded into the column body, the other end of the spring 32 is fixed at the bottom of the column body, and the push rod 31 can move in the column body; the base 33 is fixed to the fuselage mechanism by means of the bracket 4.

In this embodiment, according to the rotation angle of the unlocking handle in the machine, the dimensions of the rocker arm 1, the connecting rod 2 and the ejector rod 31 are designed, and the initial angles of the rocker arm 1 and the connecting rod 2 are determined, so as to improve the force transmission form of the anti-misoperation unlocking device, and the specification of the spring 32 is determined through calculation, so that the lock system is ensured not to unlock accidentally under the course overload in normal flight, and the operating force of the unlocking handle in the same time can meet the use requirement, and the schematic diagram is shown in fig. 3.

In this embodiment, one end of the rocker arm 1 is provided with a mounting hole for mounting with a spindle, and the other end of the rocker arm 1 is provided with an opening hole for connecting with the connecting rod 2.

In this embodiment, two ends of the connecting rod 2 are respectively provided with a pin hole for installing a cotter pin, and the rocker arm 1 and the ejector rod 31 are connected through the cotter pin.

In this embodiment, the top end of the ejector rod 31 is provided with a mounting hole for mounting a cotter pin.

In this embodiment, the column and the base 33 are integrally formed.

In the embodiment, when in installation, the rocker arm 1 is installed on a main shaft of an in-machine unlocking handle, is connected to a lock system through the main shaft, and the rocker arm 1 rotates synchronously with the in-machine unlocking handle; the connecting rod 2 is used for connecting the rocker arm 1 and the damping mechanism 3, the damping mechanism 3 is fixed on the machine body mechanism through the bracket 4, and the ejector rod 31 needs to be ensured to move in the column body of the base 33;

after the lock system is locked in place, the spring 32 is in a compressed state, and the ejector rod 31 is pushed against the rocker arm 1 through the connecting rod 2 by the force of the spring; when unlocking, the rocker arm 1 can rotate only by overcoming the action of a spring force, and the spring force is gradually increased along with the rotation of the rocker arm 1, so that the possibility of unexpected unlocking is further reduced, and the cabin cover is ensured to be firmly locked on the machine body structure; meanwhile, after the lock system is unlocked in place, the device can lock the lock system at the unlocking position so as to ensure that the signal for unlocking in place is continuously effective, and the unlocking system can work normally.

Claims

1. The anti-misoperation unlocking device of the aircraft cabin cover lock system comprises a rocker arm, a connecting rod, a damping mechanism and a bracket, and is characterized in that the damping mechanism comprises a push rod, a spring and a base, and the rocker arm is installed on a main shaft of an in-aircraft unlocking handle; one end of the connecting rod is connected with the rocker arm, the other end of the connecting rod is connected with the ejector rod of the damping mechanism, a column body is arranged on the base, the ejector rod capable of moving in the column body is embedded in the column body, one end of the spring is sleeved on the ejector rod embedded in the column body, and the other end of the spring is fixed at the bottom of the column body; the base is fixed on the machine body mechanism through a bracket.

2. An anti-false unlocking device for an aircraft canopy lock system according to claim 1, wherein one end of the rocker arm is provided with a mounting hole for mounting with a main shaft, and the other end of the rocker arm is provided with an opening hole for connecting with a connecting rod.

3. The error unlocking prevention device for an aircraft canopy lock system according to claim 1, wherein the connecting rod is provided with pin holes for installing cotters at both ends thereof, respectively.

4. The device for preventing false unlocking of an aircraft canopy lock system according to claim 1, wherein the upper end of the ejector rod is provided with a mounting hole for mounting a cotter pin.

5. An aircraft canopy lock system false unlocking prevention device in accordance with claim 1, wherein said post is integrally formed with the base.