CN118167140A - Locking mechanism for aircraft engine cabin inner cover - Google Patents

Abstract

The invention relates to the technical field of aviation, in particular to a locking mechanism for an aircraft engine cabin inner cover; comprising the following steps: a latch assembly mounted to the engine compartment door and including a latch member having a first locking aperture; a lock groove assembly mounted on the engine compartment inner cover and comprising a lock groove part provided with a second locking hole; and a locking assembly including a locking head part, the locking head part being disposed perpendicular to the locking groove part; when the engine compartment door is closed, the lock pin component is partially inserted into the lock groove component, and the lock head component passes through the first locking hole and the second locking hole and is used for fixing the lock pin component in the lock groove component; through the mode of this flexible bolt, realized in narrow and small space, locking engine compartment door and engine inner cover to only need extract the tapered end part and can unblock engine compartment door, and then open the engine compartment door, saved the time of unpacking and installing the engine bonnet greatly, saved whole maintenance time, maintenance efficiency is higher.

Description

Locking mechanism for aircraft engine cabin inner cover

Technical Field

The invention relates to the technical field of aviation, in particular to a locking mechanism for an aircraft engine cabin inner cover.

Background

The engine part of an aircraft is a very important component, and the safety performance of the engine needs to be ensured at all times, so that the engine needs to be checked and maintained regularly.

At present, when an engine is overhauled, the engine cover is required to be disassembled, then the engine inside is overhauled, and after the overhauling is finished, the engine and the engine cover are installed; in this process, it takes a lot of time to disassemble the hood and install the hood; and the operation is very inconvenient, the whole maintenance time is long, and the efficiency is low.

Disclosure of Invention

The purpose of the invention is that: the locking mechanism for the aircraft engine cabin inner cover can be used for rapidly opening and closing the aircraft engine cover, so that maintenance time is saved, and maintenance efficiency is improved.

The technical scheme of the invention is as follows: a locking mechanism for an aircraft engine compartment inner cover, comprising: a latch assembly mounted to the engine compartment door and including a latch member having a first locking aperture; a lock groove assembly mounted on the engine compartment inner cover and comprising a lock groove part provided with a second locking hole; and a locking assembly including a locking head member disposed perpendicularly to the locking slot member, the locking pin member being partially inserted into the locking slot member when the engine compartment door is closed, the locking head member passing through the first and second locking holes for securing the locking pin member within the locking slot member.

According to an embodiment of the invention, a locking groove is arranged in the locking groove component; the keyway assembly further comprises: the sliding seat is arranged in the locking groove; the elastic component is arranged in the locking groove, one end of the elastic component is propped against the bottom of the locking groove, and the other end of the elastic component is propped against the sliding seat; when the locking pin component is inserted into the locking groove, one end of the sliding seat is contacted with the end of the locking pin component.

According to one embodiment of the invention, the sliding seat is provided with an arc-shaped containing groove, the head of the locking pin component is an arc-shaped protrusion, and when the locking pin component is inserted into the locking groove, the head of the locking pin component abuts against the arc-shaped containing groove.

According to one embodiment of the invention, the locking pin component is provided with a limiting convex ring, and the limiting convex ring is abutted against the end part of the locking groove component after the locking pin component is inserted into the locking groove.

According to an embodiment of the invention, the latch assembly further comprises a latch mounting base through which the latch member passes; the threaded ring is arranged in the lock pin installation base and is in threaded connection with the lock pin component; the lock pin component is provided with a sliding groove, and a first pin penetrates through the lock pin mounting base and is inserted into the sliding groove; the threaded ring is rotated for moving the latch member along the slide groove.

According to an embodiment of the invention, the locking assembly comprises: the locking base is fixedly connected to the engine inner cover; a handle member slidably coupled to the locking base; and a link member having a bar shape of a long bar shape, one end of which is connected to the locking head member and the other end of which is connected to the handle member, pushing the handle member for inserting the locking head member into the first locking hole.

According to an embodiment of the invention, the locking assembly further comprises: the limiting rod component is fixedly connected with the handle component, is vertically arranged with the handle component and is rotationally connected with the locking base; and one end of the connecting component is rotationally connected with the limiting rod component, the other end of the connecting component is fixedly connected with the connecting rod component, a limiting groove is formed in the limiting rod component, a second pin is inserted into the limiting groove, the second pin is fixedly connected with the locking base, the limiting groove comprises a sliding groove part and a rotating groove part, the handle component is pushed and then rotated, and the second pin is clamped into the rotating groove part.

According to one embodiment of the invention, a first spring is arranged between the connecting component and the locking base, one end of the first spring is abutted against the locking base, and the other end of the first spring is abutted against the connecting component and used for pushing the locking component to be automatically away from the locking groove component.

According to an embodiment of the present invention, the link member includes: a first link having one end connected to the lock cylinder member; the second connecting rod is connected with the locking base in a sliding way; one end of the connecting component is fixedly connected with the connecting component; and one end of the third connecting rod is in threaded connection with the first connecting rod, the other end of the third connecting rod is in threaded connection with the second connecting rod, and the second connecting rod is rotated to adjust the length of the connecting rod component.

According to an embodiment of the invention, the locking groove part is provided with a pin head accommodating part which is in an elongated shape at one end close to the pin head part, and part of the second locking hole is positioned in the pin head accommodating part.

Compared with the prior art, the invention has the following outstanding and beneficial technical effects:

Compared with the prior art, the locking mechanism for the aircraft engine cabin inner cover comprises the lock pin assembly, the lock groove assembly and the locking assembly, when the engine cabin door is closed, the lock pin assembly is partially inserted into the lock groove assembly, the lock pin assembly penetrates through the first locking hole and the second locking hole, so that the lock pin assembly is fixed in the lock groove assembly, the engine cabin door and the engine inner cover are locked in a narrow space in a telescopic bolt mode, the engine cabin door can be unlocked only by pulling out the lock pin assembly, the engine cabin door is opened, the time for disassembling and installing the engine cover is greatly saved, the overall maintenance time is saved, and the maintenance efficiency is higher.

Further, after the pin head part is pulled out, the spring automatically stretches through the design of the elastic part and the sliding seat, the sliding seat is ejected out, and then the lock pin part is ejected out; so that the cabin door is convenient to open. Further, after the engine compartment door is closed, if the latch member is not fully inserted into the latch slot, the latch member is ejected under the action of the elastic member; the lock head component can not be inserted into the second locking hole on the lock pin component, and the locking mechanism is still in an opened state, so that the design also prevents the cabin door from being locked by mistake under the condition of no closing; and further, the door can be locked by the lock head component only when the door is completely closed (namely, the lock pin component is completely inserted into the locking groove), so that the safety of the door is improved.

Further, the pin head receiving portion is designed such that the pin head member is inserted into and out of the first locking hole after the pin head member is disengaged from the first locking hole, i.e., the pin head member can be guided to be inserted into and out of the first locking hole, and a supporting force is provided to the pin head member.

Further, the design of the threaded ring can adjust the distance between the lock pin component and the lock groove, namely the depth of the lock pin component inserted into the lock groove can be adjusted.

Further, the length of the sliding groove portion limits the insertion and protruding length of the pin head member; after the pin head part is inserted into the first locking hole, the handle part is rotated, so that the second pin 37 is clamped into the rotating groove part, and the front and rear direction vibration can be generated in the flying process of the aircraft, thereby avoiding the situation that the handle part is pulled out by mistake and improving the safety of the engine compartment.

Further, due to the design of the first spring, after the second pin is separated from the rotating groove part, the locking component can be pushed to be automatically far away from the locking groove component under the action of the first spring; when the second pin is clamped into the rotating groove part, the first spring can provide extrusion force between the second pin and the rotating groove part, so that friction force between the second pin and the rotating groove part is increased; further, the handle is prevented from being opened by mistake, and the safety of the engine compartment is improved.

Further, the design of the first connecting rod, the second connecting rod and the third connecting rod rotates the second connecting rod, the length of the connecting rod part can be adjusted, and then the depth of the pin head part inserted into and extending out of the second locking hole can be adjusted.

Drawings

Fig. 1 is a schematic view of an open state of a locking mechanism according to an embodiment of the present invention.

Fig. 2 is a schematic view of a locking state of a locking mechanism according to an embodiment of the present invention.

Fig. 3 is a cross-sectional view of a locking state of a locking mechanism in an embodiment of the present invention.

Fig. 4 is a schematic structural view of the lock slot assembly.

Fig. 5 is a schematic view of the sliding seat and related structure.

FIG. 6 is a schematic structural view of the latch assembly.

Fig. 7 is a schematic structural view of the locking assembly.

Fig. 8 is an enlarged partial view of the open state locking assembly.

Fig. 9 is an enlarged view of a portion of the lockout condition locking assembly.

Symbol description: a 10-pin assembly; 11-a latch member; 111-a first locking hole; 112-arc-shaped protrusions; 113-limiting convex rings; 114-a sliding groove; 12-a lock pin mounting base; 13-a threaded ring; 14-pins; a 20-keyway assembly; 21-a keyway component; 211-a second locking hole; 212-a locking groove; 213-pin head accommodation; 22-sliding seat; 221-an arc-shaped receiving groove; 222-a sliding limiting hole; 223-limiting shaft; 23-an elastic member; 30-a locking assembly; 31-a lock head component; 32-locking the base; 33-a handle part; 34-a link member; 35-a stop lever component; 36-connecting part; 37-a second pin; 351-limit grooves; 3511—a sliding groove portion; 3512-rotating groove portion; 38-a first spring.

Detailed Description

The foregoing and other features, aspects, and advantages of the present invention will become more apparent from the following detailed description of the preferred embodiments and examples of the present invention, read in conjunction with the accompanying drawings. The directional terms mentioned in the following embodiments are, for example: upper, lower, left, right, front, rear, inner or outer, etc., are only with reference to the orientation of the drawings; thus, the directional terminology is used for purposes of illustration and is not intended to be limiting of the invention.

Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs. The terms "first," "second," and the like in the description and in the claims, are not used for any order, quantity, or importance, but are used for distinguishing between different elements. Likewise, the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one.

The invention is further described in the following examples with reference to the accompanying drawings:

the outer side of the engine of the aircraft is generally provided with an outer cover and an inner cover, and the surfaces of the outer cover and the inner cover are very smooth in consideration of air flow resistance during flight, so that other locking structures cannot be arranged on the surfaces of the outer cover and the inner cover, and further, a cabin door cannot be arranged; therefore, when the existing aircraft engine is overhauled, the engine cover is generally required to be detached, and the engine cover is reinstalled after overhauling. This approach takes a lot of time and is inconvenient to operate, resulting in long overall service time and low efficiency.

The invention proposes a locking mechanism for an aircraft engine compartment inner cover, which is arranged between an outer cover and an inner cover, with reference to fig. 1 to 3, comprising: a latch assembly 10, a latch slot assembly 20 and a latch assembly 30, the latch assembly 10 being mounted on the engine compartment door and comprising a latch member 11, the latch member 11 having a first locking aperture 111; the lock groove assembly 20 is mounted on the engine compartment inner cover and comprises a lock groove part 21, wherein a second lock hole 211 is formed on the lock groove part 21; the lock assembly 30 includes a lock cylinder part 31, the lock cylinder part 31 being disposed perpendicular to the lock groove part 21; when the engine compartment door is closed, the lock pin member 11 is partially inserted into the lock groove member 21, and the lock head member 31 passes through the first locking hole 111 and the second locking hole 211, so that the lock pin member 11 is fixed in the lock groove member 21.

Specifically, referring to fig. 3 to 5, a lock groove 212 is provided in the lock groove member 21; the locking groove assembly 20 further comprises a sliding seat 22 and an elastic component 23, and the locking groove assembly 20 and the elastic component 23 are arranged in the locking groove 212; one end of the elastic member 23 abuts against the bottom of the locking groove 212, and the other end abuts against the sliding seat 22; when the latch member 11 is inserted into the latch groove 212, one end of the slide seat 22 contacts the end of the latch member 11. Specifically, the elastic member 23 is not limited to a spring alone; when the engine compartment door is closed, the lock pin member 11 is partially inserted into the lock groove member 21, and the lock head member 31 passes through the first locking hole 111 and the second locking hole 211, so that the lock pin member 11 is fixed in the lock groove member 21 while the elastic member 23 is in a compressed state; when the lock head part 31 is pulled out, the spring automatically stretches to push out the sliding seat 22, and then the lock pin part 11 is pushed out; so that the cabin door is convenient to open.

After closing the engine compartment door, if the latch member 11 is not fully inserted into the locking groove 212, the latch member 11 is ejected by the elastic member 23; the lock head member 31 cannot be inserted into the second locking hole 211 of the lock pin member 11, and the locking mechanism is still in an opened state; the design also avoids that the cabin door is locked by mistake under the condition of no closing; further ensuring that only when the door is fully closed, (i.e. the latch member 11 is fully inserted into the slot 212) is locked by the lock member 31; the safety of the cabin door is improved.

Specifically, referring to fig. 3 and 5, the sliding seat 22 is provided with a sliding limiting hole 222, and the sliding limiting hole 22 is a waist-shaped hole; the side wall of the locking groove 212 is provided with a bolt hole, and a limiting shaft 223 passes through the bolt hole and the sliding limiting hole 222; the limiting shaft 223 can limit the compression depth and the protruding height of the slide block 22. After the lock cylinder member 31 is pulled out, the slide seat 22 is prevented from being separated from the lock groove 212 when the lock pin member 11 is ejected.

Further, referring to fig. 4, the slide seat 22 is provided with an arc-shaped receiving groove 221, the head of the latch member 11 is an arc-shaped protrusion 112, and when the latch member 11 is inserted into the locking groove 212, the head of the latch member 11 abuts against the arc-shaped receiving groove 221. Specifically, the arc-shaped receiving groove 221 is a spherical groove, and the arc-shaped protrusion 112 is a spherical protrusion. The lock pin member 11 is provided with a limit collar 113, and after the lock pin member 11 is inserted into the lock groove 212, the limit collar 113 abuts against the end of the lock groove member 21.

Further, referring to fig. 3 and 4, the lock groove member 21 is provided at one end near the lock head member 31 with a pin head receiving portion 213, the pin head receiving portion 213 is in an outwardly protruding shape with respect to the lock groove member 21, and a part of the second locking hole 211 is located in the pin head receiving portion 213 and is in an elongated shape; after the lock head member 31 is disengaged from the first locking hole 111, the lock head member 31 is always inserted into the pin head receiving portion 213; can guide the insertion and extension of the locking head part 31 out of the first locking hole and provide a supporting force for the locking head part 31.

Referring to FIG. 6, the latch assembly 10 further includes a latch mounting base 12 and a threaded ring 13, the latch member 11 passing through the latch mounting base 12; a threaded ring 13 is provided in the latch mounting base 12 and is threadedly connected with the latch member 11; the latch component 11 is provided with a sliding groove 114, and the first pin 14 passes through the latch mounting base 12 and is inserted into the sliding groove 114; the threaded ring 13 is turned for moving the latch member 11 along the slide groove 114. This design allows for adjustment of the distance of the locking pin member 11 relative to the locking slot 212, i.e. the depth of insertion of the locking pin member 11 into the locking slot 212.

Referring to fig. 7, the locking assembly 30 includes: a lock base 32, a handle member 33, and a link member 34, the lock base 32 being fixedly attached to the engine inner cover; the handle member 33 is slidably connected to the locking base 32; the link member 34 has a bar shape of a long bar, one end of which is connected to the lock head member 31 and the other end of which is connected to the handle member 33; the handle member 33 is pushed to insert the lock cylinder member 31 into the first locking hole 111, and the handle member 33 is pulled out to disengage the lock cylinder member 31 from the first locking hole 111.

Referring to fig. 8 and 9, the locking assembly 30 further includes: a stopper rod part 35 and a connecting part 36; the limiting rod part 35 is fixedly connected with the handle part 33, is arranged vertically to the handle part 33 and is rotationally connected with the locking base 32; one end of the connecting part 36 is rotatably connected with the limit rod part 35, and the other end of the connecting part is fixedly connected with the connecting rod part 34; the limiting rod part 35 is provided with a limiting groove 351, the second pin 37 is inserted into the limiting groove 351, and the second pin 37 is fixedly connected with the locking base 32; the limit groove 351 includes a slide groove portion 3511 and a rotation groove portion 3512; after pushing the handle member 33, the handle member 33 is rotated to engage the second pin 37 with the rotation groove portion 3512. The length of the sliding groove portion 3511 limits the insertion and protruding length of the locking head part 31; after the lock head part 31 is inserted into the first locking hole, the handle part 33 is rotated, so that the second pin 37 is clamped into the rotating groove part 3512, and the front and rear direction vibration can be generated in the flying process of the aircraft, thereby avoiding the situation that the handle part 33 is pulled out by mistake and improving the safety of the engine compartment.

Referring to fig. 7 to 9, a first spring 38 is disposed between the connecting member 36 and the locking base 32, one end of the first spring abuts against the locking base 32, the other end abuts against the connecting member 36, and after the handle member 33 is rotated to disengage the second pin 37 from the rotating groove portion 3512, the locking assembly 30 can be automatically pushed away from the locking groove assembly 20 by the first spring 38; when the second pin 37 is clamped into the rotating groove portion 3512, the first spring 38 can provide the extrusion force between the second pin 37 and the rotating groove portion 3512, so that the friction force between the second pin 37 and the rotating groove portion 3512 is increased; further avoiding the handle from being opened by mistake.

Referring to fig. 1 and 7, the link member 34 includes: a first link 341, a second link 342, and a third link 343; one end of the first connecting rod 341 is connected to the lock cylinder member 31; the second link 342 is slidably coupled to the locking base 32; one end of which is fixedly connected with the connecting part 36; one end of the third link 343 is screw-coupled to the first link 341, and the other end thereof is screw-coupled to the second link 342; the second link 342 is rotated to adjust the length of the link member 34, and thus the depth of the insertion and extension of the locking head member 31 into the second locking hole 211 can be adjusted.

Specifically, the second connecting rod 342 is connected with the locking base 32 through a sliding sleeve, the locking base 32 is provided with a first convex seat and a second convex seat, the second connecting rod 342 is connected with the first convex seat through a sliding sleeve, and the connecting part 36 is connected with the first convex seat in a sliding manner; the stop lever member 35 passes through the second boss, in which a cylindrical hole is provided, through which the stop lever member 35 passes, and through which the second pin 37 passes and is partially inserted.

The above embodiments are merely preferred embodiments of the present invention, and are not intended to limit the scope of the present invention in any way, and any person skilled in the art should be able to make some changes or modifications to the embodiments disclosed in the present invention without departing from the scope of the technical means disclosed in the present invention, and the invention is not limited to the embodiments described in the present invention, and therefore, the present invention is not limited to the embodiments described in the present invention. All equivalent changes in structure, shape and principle of the invention should be covered in the scope of protection of the invention.

Claims (10)

1. A locking mechanism for an aircraft engine compartment inner cover, comprising:

A latch assembly mounted to the engine compartment door and including a latch member having a first locking aperture;

a lock groove assembly mounted on the engine compartment inner cover and comprising a lock groove part provided with a second locking hole; and

A locking assembly comprising a lock cylinder member disposed perpendicularly to the lock groove member,

The latch member is partially inserted into the keyway member when the engine compartment door is closed, and the lock head member passes through the first and second locking apertures for securing the latch member within the keyway member.

2. A locking mechanism for an aircraft engine compartment inner cover according to claim 1, wherein said locking slot member has a locking slot therein;

The keyway assembly further comprises:

The sliding seat is arranged in the locking groove; and

An elastic component which is arranged in the locking groove, one end of the elastic component is propped against the bottom of the locking groove, and the other end is propped against the sliding seat;

When the locking pin component is inserted into the locking groove, one end of the sliding seat is contacted with the end of the locking pin component.

3. A locking mechanism for an aircraft engine compartment inner cover according to claim 2,

The sliding seat is provided with an arc-shaped containing groove, the head of the lock pin component is an arc-shaped protrusion, and when the lock pin component is inserted into the lock groove, the head of the lock pin component abuts against the arc-shaped containing groove.

4. A locking mechanism for an aircraft engine compartment inner cover according to claim 2, wherein the locking pin member is provided with a stop collar which abuts against an end of the locking slot member after the locking pin member is inserted into the locking slot.

5. A latch mechanism for an aircraft engine compartment inner cover according to claim 4, wherein said latch assembly further comprises

A latch mounting base through which the latch member passes; and

The threaded ring is arranged in the lock pin installation base and is in threaded connection with the lock pin component;

The lock pin component is provided with a sliding groove, and a first pin penetrates through the lock pin mounting base and is inserted into the sliding groove;

The threaded ring is rotated for moving the latch member along the slide groove.

6. A locking mechanism for an aircraft engine compartment inner cover according to claim 1,

The locking assembly further comprises:

The locking base is fixedly connected to the engine inner cover;

a handle member slidably coupled to the locking base; and

A connecting rod part which is in a long bar shape, one end of the connecting rod part is connected with the lock head part, the other end of the connecting rod part is connected with the handle part,

Pushing the handle member for inserting the lock cylinder member into the first locking hole.

7. A locking mechanism for an aircraft engine compartment inner cover according to claim 6, wherein said locking assembly further comprises:

The limiting rod component is fixedly connected with the handle component, is vertically arranged with the handle component and is rotationally connected with the locking base; and

One end of the connecting component is rotationally connected with the limiting rod component, the other end of the connecting component is fixedly connected with the connecting rod component,

The limiting rod part is provided with a limiting groove, a second pin is inserted into the limiting groove and is fixedly connected with the locking base,

The limiting groove comprises a sliding groove part and a rotating groove part, and the handle part is pushed and rotated to enable the second pin to be clamped into the rotating groove part.

8. A locking mechanism for an aircraft engine compartment inner cover according to claim 7,

A first spring is arranged between the connecting part and the locking base, one end of the first spring is propped against the locking base, and the other end of the first spring is propped against the connecting part and used for pushing the locking assembly to be automatically away from the locking groove assembly.

9. A latch mechanism for an aircraft engine compartment inner cover according to claim 6, wherein said link member comprises:

a first link having one end connected to the lock cylinder member;

The second connecting rod is connected with the locking base in a sliding way; one end of the connecting component is fixedly connected with the connecting component; and

One end of the third connecting rod is in threaded connection with the first connecting rod, the other end of the third connecting rod is in threaded connection with the second connecting rod,

And rotating the second connecting rod for adjusting the length of the connecting rod part.

10. A locking mechanism for an aircraft engine compartment inner cover according to claim 1, wherein the locking groove member is provided with a pin head receiving portion, which is elongated, at an end adjacent to the pin head member, and a portion of the second locking hole is located inside the pin head receiving portion.