CN219029732U

CN219029732U - Aircraft landing gear retracting mechanism

Info

Publication number: CN219029732U
Application number: CN202222690824.9U
Authority: CN
Inventors: 潘小权; 焦斌昌; 麻军太
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2022-10-12
Filing date: 2022-10-12
Publication date: 2023-05-16
Anticipated expiration: 2032-10-12

Abstract

The application belongs to the technical field of aircraft landing gear and relates to an aircraft landing gear retraction mechanism, which comprises a lower stay bar, wherein one end of the lower stay bar is hinged with a main support, and the other end of the lower stay bar is hinged with an upper stay bar; the lower stay bar is connected with an emergency spring; the emergency spring provides a pre-tightening force for clockwise rotation of the lower stay bar, and the upper stay bar is hinged on the fixed support; when the upper stay bar moves anticlockwise to the landing gear lowering locking position, the lock key of the upper stay bar is in abutting limit with the lower stay bar; the upper stay bar is also hinged with a main retraction actuator, and the main retraction actuator drives the upper stay bar to rotate. The application is a set of retractable form and comprises an integral retractable form of unlocking, retractable and emergency unlocking, main mechanism components such as an upper lock, an unlocking actuator cylinder, an emergency unlocking actuator cylinder, a cabin door actuator cylinder and the like are removed, the whole weight of the aircraft is also integrally reduced, maintainability is easier to maintain, and the aircraft has the beneficial effects of high reliability and high safety.

Description

Aircraft landing gear retracting mechanism

Technical Field

The utility model belongs to the technical field of aircraft landing gears, and relates to an aircraft landing gear retraction mechanism.

Background

At present, the retraction mode of the landing gear of the aircraft at home and abroad mostly adopts the process of firstly unlocking a lower lock (or an upper lock) and then retracting the landing gear, so that the whole retraction has an unlocking actuator cylinder and a retraction actuator cylinder, and if a cabin door exists, the cabin door retraction actuator cylinder can be arranged.

When the emergency unlocking is carried out, the emergency unlocking actuating cylinder is adopted to unlock, and then the process of putting down is carried out, so that the whole emergency unlocking mechanism has one or more emergency unlocking actuating cylinders.

The retractable form of the landing gear structure is suitable for an aircraft with large aircraft landing gear structure and heavy weight, occupies large space and is not suitable for the requirements of economy, reliability and maintainability of general aircraft and small aircraft.

Disclosure of Invention

In order to solve the problems, the application provides an aircraft landing gear retraction mechanism, wherein an aircraft wheel is hinged with a machine body through a main support column;

the retracting mechanism comprises:

one end of the lower stay bar is hinged with the main support column, and the other end of the lower stay bar is hinged with the upper stay bar; the lower stay bar is connected with an emergency spring; the emergency spring provides a pre-tightening force for clockwise rotation of the lower stay bar.

The upper stay bar is hinged on the fixed support;

when the upper stay bar moves anticlockwise to the landing gear lowering locking position, the lock key of the upper stay bar is in abutting limit with the lower stay bar; the upper stay bar is also hinged with a main retraction actuator, and the main retraction actuator drives the upper stay bar to rotate.

Preferably, the upper brace forms an angle with the lower brace of less than 180 degrees on the upper side when the landing gear is locked down.

Preferably, a rocker arm is fixed in the middle of the upper stay bar and is connected with the main retraction actuator cylinder through the rocker arm.

Preferably, the emergency spring is connected to the tail end of the lower stay bar or the middle position of the lower stay bar;

when the emergency spring is connected to the tail end, the emergency spring is in a stretching state;

the emergency spring is connected to the middle position and is in a compressed state.

Preferably, a return spring is arranged between the lock key and the fixed support, and the return spring provides a pre-tightening force for the counterclockwise movement of the upper stay bar.

Preferably, the main support is provided with a cabin door and a cabin door pull rod, one end of the cabin door pull rod is connected with the main support through a bolt, and the other end is connected with the cabin door through a bolt

The advantages of the present application include: the utility model is a set of folding and unfolding forms including an integral folding and unfolding form of unlocking, folding and unfolding and emergency unlocking, and the main mechanism components such as an upper lock, an unlocking actuator cylinder, an emergency unlocking actuator cylinder, a cabin door actuator cylinder and the like are removed, so that the whole weight of the aircraft is also reduced integrally, the maintenance is easier, and the aircraft has the beneficial effects of high reliability and high safety.

Drawings

Fig. 1 is a schematic structural view of a retracting mechanism and an emergency mechanism according to a preferred embodiment of the present application.

The device comprises a 1-actuator cylinder outer cylinder, a 2-actuator cylinder piston rod, a 3-rocker arm, a 4-upper rotating shaft, a 5-lower rotating shaft, a 6-emergency spring, a 7-main support, an 8-lower support rod, a 9-lock key, a 10-upper support rod, a 11-return spring, a 12-fixed support rod, a 13-cabin door pull rod and a 14-cabin door.

Detailed Description

For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, based on the embodiments herein, which would be apparent to one of ordinary skill in the art without undue burden are within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

As shown in fig. 1, an aircraft landing gear retraction mechanism, wherein an aircraft wheel is hinged with a machine body through a main support column 7;

the retraction mechanism comprises an outer cylinder 1, a piston rod 2, a rocker arm 3, an upper rotating shaft 4, a lower rotating shaft 5, an emergency spring 6, a main support 7, a lower support rod 8, a lock key 9, an upper support rod 10, a return spring 11, a fixed support 12, a cabin door pull rod 13 and a cabin door 14, wherein one end of the lower support rod 8 is hinged with the main support 7, and the other end is hinged with the upper support rod 10; the lower stay bar 8 is connected with an emergency spring 6; the emergency spring 6 provides a pre-tightening force for clockwise rotation of the lower stay bar 8.

An upper stay bar 10 hinged to the fixed support 12;

when the upper stay bar 10 moves anticlockwise to the landing gear lowering locking position, the lock 9 of the upper stay bar 10 is in abutting limit with the lower stay bar 8; the upper stay bar 10 is also hinged with a main retraction actuator which drives the upper stay bar 10 to rotate.

Preferably, when the landing gear is locked in a downward direction, the angle formed by the upper stay bar 10 and the lower stay bar 8 at the upper side is smaller than 180 degrees, and the upper stay bar 10 and the lower stay bar 8 form a structure with deflection, so that stable locking is facilitated.

In some alternative embodiments, the rocker arm 3 is fixed at the middle position of the upper stay 10, and is connected with the main jack through the rocker arm 3, and the rocker arm 3 can adapt to the position of the main jack, so that the force transmission of the main jack is facilitated.

The emergency spring 6 is connected to the tail end of the lower stay bar 8 or the middle position of the lower stay bar 8; in some alternative embodiments, the upper part of the emergency spring 6 is connected with the lug at the upper end of the main strut 7 through a bolt, and the lower part of the emergency spring 6 is connected with the lug of the lower stay 8 through a bolt.

When the emergency spring 6 is connected to the tail end, the emergency spring 6 is in a stretching state;

the emergency spring 6 is connected in said intermediate position, the emergency spring 6 being in a compressed state.

In some alternative embodiments, a return spring 11 is provided between the latch 9 and the fixed support 12, the return spring 11 providing a pre-tension force for the counter-clockwise movement of the upper strut 10.

In some alternative embodiments, the main strut 7 is provided with a hatch 14 and a hatch pull rod 13, one end of the hatch pull rod 13 is connected with the main strut 7 through a bolt, and the other end is connected with the hatch 14 through a bolt

A retracting mechanism movement principle;

a) And (3) a winding and unwinding process:

(1) The piston rod 2 of the main retraction actuator cylinder is contracted to pull the rocker arm 3;

(2) The rocker arm 3 pushes the reset spring 11 to compress and pushes the lock key 9 to unlock;

(3) The rocker arm 3 continues to push the upper stay bar 10 to rotate;

(3) The upper stay bar 10 drives the lower stay bar 8 to rotate and the deflection passes 0 dead points and is retracted upwards;

(4) The main support column is pulled to rotate and is retracted upwards in the rotating process of the lower support rod 8;

(5) The main support drives the cabin doors to be retracted together through the pull rod;

(6) After the landing gear and the cabin door are at the retracted position, the main retraction actuator cylinder fixes the main landing gear at the retracted position through pressure maintaining.

b) Emergency release process

The main working parts of the emergency mechanism are as follows: the main landing gear, the main lifting stay bar lock, the emergency spring and the main lifting retraction actuator cylinder;

(1) When the hydraulic system fails;

(2) The landing gear is put down by the self weight;

(3) The emergency release spring pulls the main landing gear to be put down;

(4) The main supporting rod lock is unfolded, and meanwhile, the piston rod of the retractable actuator cylinder is extended;

(6) The main landing gear moves downwards by means of main lifting force, inertial force and emergency spring tension;

(7) The main supporting rod lock is locked by means of the reset spring, inertia force and emergency spring tension.

The application is a set of retractable form and comprises an integral retractable form of unlocking, retractable and emergency unlocking, main mechanism components such as an upper lock, an unlocking actuator cylinder, an emergency unlocking actuator cylinder, a cabin door actuator cylinder and the like are removed, the whole weight of the aircraft is also integrally reduced, maintainability is easier to maintain, and the aircraft has the beneficial effects of high reliability and high safety.

The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft landing gear retraction mechanism, wherein an aircraft wheel is hinged with a machine body through a main support (7);

the device is characterized in that the retraction mechanism comprises:

one end of the lower stay bar (8) is hinged with the main support (7), and the other end is hinged with the upper stay bar (10); the lower stay bar (8) is connected with an emergency spring (6); the emergency spring (6) provides a pre-tightening force for clockwise rotation of the lower stay bar (8);

an upper stay bar (10) hinged on the fixed support (12);

when the upper stay bar (10) moves anticlockwise to the landing gear lowering locking position, a lock key (9) of the upper stay bar (10) is in abutting limit with the lower stay bar (8); the upper stay bar (10) is also hinged with a main retraction actuator, and the main retraction actuator drives the upper stay bar (10) to rotate.

2. An aircraft landing gear extension mechanism according to claim 1, wherein the upper strut (10) forms an angle with the lower strut (8) of less than 180 degrees on the upper side when the landing gear is locked down.

3. An aircraft landing gear retraction mechanism according to claim 1, wherein a rocker arm (3) is fixed to the intermediate position of the upper strut (10) and is connected to the main retraction jack via the rocker arm (3).

4. An aircraft landing gear extension and retraction mechanism according to claim 1 wherein the emergency spring (6) is connected at the end of the lower strut (8) or at a mid-position of the lower strut (8);

when the emergency spring (6) is connected to the tail end, the emergency spring (6) is in a stretching state;

the emergency spring (6) is connected to the middle position, and the emergency spring (6) is in a compressed state.

5. An aircraft landing gear retraction mechanism according to claim 1, wherein a return spring (11) is provided between the latch (9) and the fixed support (12), the return spring (11) providing a pre-tension force for the anticlockwise movement of the upper strut (10).

6. An aircraft landing gear retraction mechanism according to claim 1, wherein the main strut (7) has a door (14) and a door pull rod (13), one end of the door pull rod (13) being connected to the main strut (7) by means of a bolt, and the other end being connected to the door (14) by means of a bolt.