CN217812898U

CN217812898U - Cabin door lock safety mechanism and manned aircraft

Info

Publication number: CN217812898U
Application number: CN202221803650.6U
Authority: CN
Inventors: 胡华智; 陈南山; 姜国军
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-07-14
Filing date: 2022-07-14
Publication date: 2022-11-15
Anticipated expiration: 2032-07-14

Abstract

The utility model discloses a hatch door lock safety mechanism and manned airborne vehicle relates to manned airborne vehicle field. The cabin door lock safety mechanism comprises a first lock fixing piece and a second lock fixing piece; wherein the second lock is automatically locked in the first lock when a door of the manned aircraft is closed. Therefore, the double-guarantee function can be provided for the cabin door lock, secondary protection is provided when the cabin door lock fails or is opened accidentally, the safety hidden danger caused by the failure or accidental opening of the cabin door is avoided, the high-speed development requirement of the manned aircraft is met, and the problem that the safety hidden danger is caused because the currently designed cabin door lock mechanism only has one locking mechanism and cannot provide the secondary protection when the cabin door lock fails or is opened accidentally can be solved.

Description

Cabin door lock safety mechanism and manned aircraft

Technical Field

The utility model relates to a manned airborne vehicle field especially relates to a hatch door lock safety mechanism and manned airborne vehicle.

Background

At present, the manned aircraft can realize short-distance unmanned flight of manned people, and during the unmanned flight, the safety of a door lock between a cabin door and a cockpit of the manned aircraft is very important.

The locking between the cabin door and the cockpit is ensured through the cabin door locking mechanism between the cabin door of the manned aircraft and the cockpit, and in the cabin door locking mechanism of the existing design, only one locking mechanism is generally adopted, so that secondary protection cannot be provided when the cabin door lock fails or is opened accidentally, and potential safety hazards exist.

Based on this, a safety mechanism of the cabin door lock is needed to provide a double-guarantee function for the cabin door lock, so as to prevent the hidden danger of the failure or accidental opening of the cabin door and meet the requirement of high-speed development of the manned aircraft.

SUMMERY OF THE UTILITY MODEL

An embodiment of the utility model provides a hatch door lock safety mechanism and manned airborne vehicle aims at solving the hatch door latch mechanism of present current design and only locking mechanism one, can't provide the problem that secondary protection leads to having the potential safety hazard when hatch door lock inefficacy or accident are opened.

In order to solve the above technical problem, an embodiment of the present invention provides a cabin door lock safety mechanism, which is applied to a manned aircraft, and includes a first lock fixing member and a second lock fixing member; wherein the second lock is automatically locked in the first lock when a door of the manned aircraft is closed.

Optionally, the first locking member includes a first holding portion and a first supporting portion, both of which are fixed to the door and connected to each other, and the first supporting portion is disposed beside the first holding portion.

Optionally, the first holding portion includes a first locking through hole disposed at a top of the first holding portion.

Optionally, the second lock fixing member includes a bottom plate, a second holding portion and a second supporting portion; wherein:

the base plate is fixed on the cabin, and two through holes are respectively formed in two ends of one side edge of the base plate;

the second fixing part is arranged on the bottom plate and is at the same side as the through hole;

the second supporting part is arranged on the bottom plate and is arranged on the same side of the bottom plate as the second fixing part.

Optionally, the second holding portion includes a first cavity, the second holding portion is provided with a first through hole penetrating through the first cavity, and a position of the first through hole corresponds to a position of the first locking through hole.

Optionally, the second holding part further comprises a first sliding part and a first elastic part; wherein:

the first sliding piece comprises a sliding plate and two sliding arms, the sliding plate is arranged in the first cavity, and the two sliding arms are formed by extending outwards from two sides of the sliding plate; the distance between the two sliding arms corresponds to the distance between the two through holes arranged on the bottom plate, and the two sliding arms respectively penetrate through the two through holes arranged on the bottom plate;

the first elastic piece is arranged between the sliding plate and the top of the first cavity body, and two ends of the first elastic piece are respectively fixedly connected with the sliding plate and the top of the first cavity body.

Optionally, the sliding plate is provided with a second through hole;

the second supporting part comprises a second cavity, one end of the second cavity is opened to form an open end, the other end of the second cavity is closed to form a closed end, and the open end of the second cavity is in butt joint with the second through hole.

Optionally, a sliding groove is disposed at a top of the second supporting portion, and the sliding groove is communicated with the second cavity.

Optionally, the second supporting portion further comprises a second sliding member and a second elastic member;

the second slider includes a slide portion and a manual operation portion; the sliding part comprises a sliding part body and a convex column, and the convex column is formed by extending outwards from the sliding part body; the sliding part body is arranged in the second cavity and slides in the second cavity; the convex columns penetrate through the sliding grooves and slide among the sliding grooves; the manual operation part is fixedly arranged on the convex column;

the second elastic piece is arranged between the sliding part body and the inner side edge of the closed end of the second cavity body, and two ends of the second elastic piece are fixedly connected with the sliding part body and the inner side edge of the closed end of the second cavity body respectively.

Accordingly, a second aspect of the present invention provides a manned aircraft comprising a cabin door, a cabin and a door lock safety mechanism according to the first aspect of the present invention; wherein: the cabin door lock safety mechanism comprises a first lock fixing piece and a second lock fixing piece, the first lock fixing piece is fixed on the cabin door, the second lock fixing piece is fixed on the cabin, and the second lock fixing piece is automatically locked in the first lock fixing piece when the cabin door is closed.

Compared with the prior art, the embodiment of the utility model provides a pair of hatch door lock safety mechanism and manned aircraft includes first lock mounting and second lock locking piece through hatch door lock safety mechanism, wherein, second lock locking piece is in when manned aircraft's hatch door is closed automatic locking in the first lock mounting. Therefore, the double-guarantee function can be provided for the cabin door lock, secondary protection is provided when the cabin door fails or is opened accidentally, the potential safety hazard that the cabin door fails or is opened accidentally is avoided, the high-speed development requirement of the manned aircraft is met, and the problem that the potential safety hazard exists because only one locking mechanism is provided for the cabin door lock mechanism in the existing design and secondary protection cannot be provided when the cabin door fails or is opened accidentally can be solved.

Drawings

One or more embodiments are illustrated by way of example in the accompanying drawings, which correspond to the figures in which like reference numerals refer to similar elements and which are not to scale unless otherwise specified.

Fig. 1 is a schematic structural diagram of a hatch lock safety mechanism provided by the present invention;

fig. 2 is a schematic structural view of a second lock fixing member in the hatch lock safety mechanism provided in the present invention;

fig. 3 is a schematic view illustrating the locking of the first lock fixing member and the second lock fixing member in the hatch lock safety mechanism provided by the present invention;

FIG. 4 is a schematic view of a door lock safety mechanism for a passenger aircraft according to the present invention with the doors in an unopened condition;

FIG. 5 is an enlarged view of a door lock safety mechanism for a passenger aircraft provided by the present invention when the door is not closed;

FIG. 6 is a schematic view of a door lock safety mechanism of a passenger aircraft provided in accordance with the present invention with the door in a closed position;

fig. 7 is an enlarged view of a door lock safety mechanism of a passenger aircraft according to the present invention when the door is closed.

Reference numerals:

first lock fixing part 11 of cabin door lock safety mechanism 1

First fixing portion 111 and first locking through hole 1111

First support portion 112 second lock fixing member 12

Through hole 1211 of bottom plate 121

The second holding portion 122 has a first cavity 1221

First through hole 1222 first slider 1223

Second through hole 122311 of sliding plate 12231

First elastic member 1224 of slider arm 12232

Second cavity 1231 of second supporting portion 123

Sliding groove 1232 second slide 1233

Sliding part 12331 sliding part body 123311

Manual operation part 12332 of convex column 123312

Door 2 of second elastic member 1234

Cabin 3

Detailed Description

To facilitate understanding of the present invention, the present invention will be described in more detail with reference to the accompanying drawings and specific embodiments. It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may be present. The terms "upper", "lower", "inner", "outer", "bottom", and the like as used herein are used in the description to indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Furthermore, the technical features mentioned in the different embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.

In one embodiment, please refer to fig. 1, the present invention provides a door lock safety mechanism for a passenger aircraft, the door lock safety mechanism 1 includes: a first lock fixing member 11 and a second lock fixing member 12; wherein the second lock 12 is automatically locked in the first lock 11 when the door of the passenger aircraft is closed.

In this embodiment, the security mechanism comprises a first lock and a second lock, wherein the second lock automatically locks in the first lock when the door of the passenger aircraft is closed. Therefore, the double-guarantee function can be provided for the cabin door lock, secondary protection is provided when the cabin door lock fails or is opened accidentally, the safety hazard that the cabin door fails or is opened accidentally is avoided, the high-speed development requirement of the manned aircraft is met, and the problem that the safety hazard exists because only one locking mechanism is provided for the cabin door lock mechanism in the existing design and secondary protection cannot be provided when the cabin door lock fails or is opened accidentally can be solved.

In one embodiment, referring to fig. 1 to 4, the manned aircraft comprises a cabin door 2 and a cabin 3.

The first locking fixture 11 is fixed to the door 2 and rotates together with the door 2 relative to the cabin 3.

Specifically, referring to fig. 1 and 4, the first locking member 11 includes: a first holding part 111 and a first supporting part 112. Wherein:

the first fixing part 111 is fixed to the hatch door 2 and connected to the hatch door to rotate together with the hatch door 2 relative to the cabin 3. The first holding part 111 includes a first locking through hole 1111, and the first locking through hole 1111 is disposed at the top of the first holding part 111.

Preferably, the first fixing portion 111 is arched, the cross section of the top of the first fixing portion 111 is semicircular, the bottom of the first fixing portion 111 and the semicircular top are integrally formed to form a square cylinder, the bottom of the square cylinder is fixed on the cabin door 2, and the first locking through hole 1111 is arranged at the center of the semicircular arc where the top is located.

The first supporting portion 112 is disposed beside the first holding portion 111 and fixed on the door 2. Preferably, the first supporting portion 112 may be integrally formed with the first holding portion 111.

In one embodiment, referring to fig. 1-4, the second lock fastener 12 is secured to the cabin 3.

Specifically, the second lock fixing member 12 includes: a bottom plate 121, a second holding portion 122, and a second supporting portion 123. Wherein:

the base plate 121 is fixed on the cabin 3, and two through holes 1211 are respectively arranged at two ends of one side of the base plate 121.

The second holding portion 122 is disposed on the bottom plate 121 and is on the same side as the through hole 1211. The second holding portion 122 includes a first cavity 1221, and the second holding portion 122 has a first through hole 1222 penetrating through the first cavity 1221. When the hatch 2 is in the closed state, the set position of the first through hole 1222 corresponds to the set position of the first locking through hole 1111 of the first holding part 111.

Further, the second holding portion 122 further includes a first sliding member 1223 and a first elastic member 1224. Wherein:

the first slider 1223 includes a sliding plate 12231 and two sliding arms 12232, and the two sliding arms 12232 are formed by extending outward from each of both sides of the sliding plate 12231. The sliding plate 12231 is disposed inside the first chamber 1221, and the sliding plate 12231 is disposed with a second through hole 122311.

Two sliding arms 12232 extend outwards from two sides of the sliding plate 12231, a distance between the two sliding arms 12232 corresponds to a distance between the two through holes 1211 formed in the bottom plate 121, and the two sliding arms 12232 respectively pass through the two through holes 1211 formed in the bottom plate 121, so that the two sliding arms 12232 can be snapped into the two through holes 1211, and the two sliding arms 12232 can slide in the through holes 1211.

The first elastic member 1224 is disposed between the sliding plate 12231 and the top of the first chamber 1221, two ends of the first elastic member 1224 are respectively fixedly connected to the sliding plate 12231 and the top of the first chamber 1221, and the first elastic member 1224 can extend and contract between the sliding plate 12231 and the top of the first chamber 1221. Preferably, the first elastic member 1224 is a spring.

Referring to fig. 4 and 5, when the door 2 is not closed, the sliding arm 12232 of the first slider 1223 is not contacted by the door 2, and the second through hole 122311 of the sliding plate 12231 is not coaxial with the first through hole 1222 and is not in an overlapping state. At this time, the first elastic member 1224 is in a normal state, i.e., not in a compressed state. An enlarged view a of the door lock security mechanism of the passenger aircraft in fig. 4 when the door is not closed is shown in an enlarged view a of fig. 5.

Referring to fig. 6 and 7, when the door 2 is closed, the sliding arm 12232 of the first sliding member 1223 is contacted by the door 2, at this time, the door 2 overcomes the elastic force of the first elastic member 1224 and pushes the sliding arm 12232 to move, so that the second through hole 122311 of the sliding plate 12231 is coaxial with the first through hole 1222 and in a coinciding state, and at this time, the first elastic member 1224 is in a compressed state. An enlarged view B of the door lock security mechanism of the passenger aircraft in fig. 6 with the door closed is shown in an enlarged view B of fig. 7.

In one embodiment, the second supporting portion 123 is disposed on the bottom plate 121 on the same side of the bottom plate 121 as the second holding portion 122.

Specifically, the second supporting portion 123 includes a second cavity 1231, one end of the second cavity 1231 is open and closed, the open end of the second cavity 1231 is abutted to the second through hole 122311 of the sliding plate 12231 of the second holding portion 122, and the aperture of the open end of the second cavity 1231 is greater than or equal to the aperture of the second through hole 122311 of the sliding plate 12231 of the second holding portion 122.

A sliding groove 1232 is formed at the top of the second supporting portion 123, and the sliding groove 1232 is communicated with the second cavity 1231.

Further, the second supporting portion 123 further includes a second sliding member 1233 and a second elastic member 1234. Wherein:

the second slider 1233 includes a sliding portion 12331 and a manual operation portion 12332. The sliding portion 12331 is disposed inside the second cavity 1231, and can slide inside the second cavity 1231.

Specifically, the sliding part 12331 includes a sliding part body 123311 and a protruding pillar 123312, the protruding pillar 123312 is formed by extending the sliding part body 123311, the sliding part body 123311 is disposed inside the second cavity 1231, and can slide inside the second cavity 1231. The protruding post 123312 passes through the sliding groove 1232 and can slide between the sliding grooves 1232, so as to drive the sliding portion body 123311 to slide inside the second cavity 1231.

The manual operation part 12332 is fixedly installed on the sliding part 12331, and can be folded around the sliding part 12331. Specifically, the manual operation part 12332 is fixedly installed on the convex pillar 123312 of the sliding part 12331, and can be folded around the convex pillar 123312. The manual operation part 12332 is pushed to drive the protruding pillar 123312 to slide between the sliding grooves 1232, so as to drive the sliding part body 123311 to slide inside the second cavity 1231.

The second elastic member 1234 is disposed inside the second cavity 1231, and the second elastic member 1234 is connected to the second slider 1233.

Specifically, the second elastic member 1234 is disposed between the sliding body 123311 and the inner side of the closed end of the second cavity 1231, and two ends of the second elastic member are respectively connected to the sliding body 123311 and the inner side of the closed end of the second cavity 1231, so that the sliding body 123311 and the inner side of the closed end of the second cavity 1231 can be extended and retracted. Preferably, the second elastic member 1234 is a spring.

Referring to fig. 4 and 5, when the hatch door 2 is not closed, the sliding arm 12232 of the first slider 1223 is not contacted by the hatch door 2, and the second through hole 122311 of the sliding plate 12231 is not coaxial with the first through hole 1222 and is not in an overlapped state. At this time, the first elastic member 1224 is in a normal state, i.e., not in a compressed state. The second through hole 122311 of the sliding plate 12231 is not coaxial with the open end of the second chamber 1231 and does not overlap with the open end, and at this time, the sliding body 123311 of the second slider 1233 is blocked by the sliding plate 12231 and the second elastic member 1234 is compressed. An enlarged view a of the door lock security mechanism of the passenger aircraft in fig. 4 when the door is not closed is shown in an enlarged view a of fig. 5.

Referring to fig. 6 and 7, when the door 2 is closed, the sliding arm 12232 of the first sliding member 1223 is contacted by the door 2, and at this time, the door 2 pushes the sliding arm 12232 to move, so that the second through hole 122311 of the sliding plate 12231 is coaxial with the first through hole 1222 and is in a coincident state, and at this time, the first elastic member 1224 is in a compressed state. The second through hole 122311 of the sliding plate 12231 is coaxial with the open end of the second cavity 1231, and is in an overlapped state, at this time, the second elastic member 1234 in the compressed state will push the sliding body 123311, so that the sliding body 123311 of the second sliding member 1233 will pass through the second through hole 122311 of the sliding plate 12231, the first through hole 1222 and the first locking through hole 1111. So that the second locking fastener 12 is automatically locked in the first locking fastener 11 when the door of the passenger aircraft is closed. An enlarged view B of the door lock security mechanism of the passenger aircraft in fig. 6 with the door closed is shown in an enlarged view B of fig. 7. One end of the first locking through hole 1111 is further provided with a chamfer structure to guide the sliding portion body 123311 to penetrate into the first locking through hole 1111.

Based on the same concept, in one embodiment, please refer to fig. 4 to 7, the present invention provides a manned aircraft, comprising: a cabin door 2, a cabin 3 and the cabin door lock safety mechanism 1 of any one of the embodiments; wherein: the cabin door lock safety mechanism 1 includes: a first lock fixing member 11 and a second lock fixing member 12; the first locking fixture 11 is fixed to the door 2, the second locking fixture 12 is fixed to the cabin 3, and the second locking fixture 12 is automatically locked in the first locking fixture 11 when the door of the passenger aircraft is closed.

In the present embodiment, by providing a manned aircraft comprising a door, a cockpit, and a door lock safety mechanism; the cabin door lock safety mechanism comprises a first lock fixing piece and a second lock fixing piece, the first lock fixing piece is fixed on the cabin door, the second lock fixing piece is fixed on the cabin, and the second lock fixing piece is automatically locked in the first lock fixing piece when the cabin door of the manned aircraft is closed. Therefore, the double-guarantee function can be provided for the cabin door lock, secondary protection is provided when the cabin door fails or is opened accidentally, the potential safety hazard that the cabin door fails or is opened accidentally is avoided, the high-speed development requirement of the manned aircraft is met, and the problem that the potential safety hazard exists because only one locking mechanism is provided for the cabin door lock mechanism in the existing design and secondary protection cannot be provided when the cabin door fails or is opened accidentally can be solved.

The utility model provides a manned airborne vehicle, when carrying out concrete operation, as follows:

referring to fig. 4 and 5, when the hatch door 2 is not closed (i.e., in a normal state), the sliding arm 12232 of the first slider 1223 is not contacted by the hatch door 2, and the second through hole 122311 of the sliding plate 12231 is not coaxial with the first through hole 1222 and is not in an overlapped state. At this time, the first elastic member 1224 is in a normal state, i.e., not in a compressed state. The second through hole 122311 of the sliding plate 12231 is not coaxial with the open end of the second chamber 1231 and does not overlap with the open end, and at this time, the sliding body 123311 of the second slider 1233 is blocked by the sliding plate 12231 and the second elastic member 1234 is compressed. In which an enlarged view a of the door lock safety mechanism of the passenger aircraft in figure 4 when the door is not closed is shown in figure 5.

Referring to fig. 6 and 7, when the door 2 is closed, the door 2 contacts the sliding arm 12232 of the second retaining portion 122, the door 2 pushes the sliding arm 12232 to move, the sliding arm 12232 is driven to compress the first elastic member 1224 connected to the sliding plate 12231, the first sliding member 1223 moves in the compression direction of the first elastic member 1224, the second through hole 122311 of the sliding plate 12231 is coaxially located with the first through hole 1222 and the first locking through hole 1111, so that the sliding body 123311, which is originally blocked by the sliding plate 12231, is released by the elastic force of the compressed second elastic member 1234, and the sliding body 123311 passes through the second through hole 122311 and the first through hole and enters the first locking through hole 1111 by the elastic force of the second elastic member 1234, so that the second aircraft door 12 is automatically locked in the first locking portion 11 when the door of the manned aircraft is locked and closed, thereby achieving the locking action. In which an enlarged view B of the door lock safety mechanism of the passenger aircraft in figure 6 with the doors closed is shown in figure 7.

When the hatch door 2 is to be opened, the manual operating portion 12332 of the second slider 1233 is manually driven, so that the manual operating portion 12332 drives the convex pillar 123312 to slide between the sliding grooves 1232, and the sliding portion body 123311 is driven to move along the compression direction of the second elastic piece 1234, so that the sliding portion body 123311 is disengaged from the first locking through hole 1111, the first through hole 1222, and the second through hole 122311 of the sliding plate 12231. When the sliding portion body 123311 is disengaged from the second through hole 122311 of the sliding plate 12231, the sliding plate 12231 is restored by the elastic force of the first elastic member 1224, so that the sliding arm 12232 of the first sliding member 1223 is restored. At this time, the second through hole 122311 of the sliding plate 12231 is not coaxial with the open end of the second chamber 1231 and does not overlap with the open end, and the sliding portion body 123311 of the second slider 1233 is received by the sliding plate 12231. Therefore, when the cabin door is opened, the safety mechanism of the cabin door lock of the manned aircraft is opened manually, and the operation is convenient.

Therefore, the double-guarantee function can be provided for the cabin door lock, secondary protection is provided when the cabin door fails or is opened accidentally, the potential safety hazard that the cabin door fails or is opened accidentally is avoided, the high-speed development requirement of the manned aircraft is met, and the problem that the potential safety hazard exists because only one locking mechanism is provided for the cabin door lock mechanism in the existing design and secondary protection cannot be provided when the cabin door fails or is opened accidentally can be solved.

It should be noted that the above-mentioned embodiment of the passenger aircraft and the embodiment of the door lock safety mechanism belong to the same concept, and the specific implementation process thereof is described in detail in the above-mentioned embodiment of the door lock safety mechanism, and the technical features in the above-mentioned embodiment of the door lock safety mechanism are applicable correspondingly in the above-mentioned embodiment of the passenger aircraft, and are not described herein again.

It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a component of' 8230; \8230;" does not exclude the presence of another like element in a process, method, article, or apparatus that comprises the element.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; within the idea of the invention, also technical features in the above embodiments or in different embodiments can be combined, steps can be implemented in any order, and there are many other variations of the different aspects of the invention as described above, which are not provided in detail for the sake of brevity; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications or substitutions do not depart from the scope of the invention in its corresponding aspects.

Claims

1. A cabin door lock safety mechanism is applied to a manned aircraft, and is characterized by comprising a first lock fixing piece and a second lock fixing piece; wherein the second lock is automatically locked in the first lock when a door of the manned aircraft is closed.

2. The door lock safety mechanism according to claim 1, wherein the first lock fixture includes a first retaining portion and a first support portion both fixed to the door and connected to each other, the first support portion being disposed adjacent to the first retaining portion.

3. The hatch lock safety mechanism according to claim 2, characterized in that the first retaining part comprises a first through locking hole, which is arranged at the top of the first retaining part.

4. The hatch lock safety mechanism according to claim 3, wherein the second lock fastener comprises a base plate, a second retaining portion and a second support portion; wherein:

the second supporting part is arranged on the bottom plate and is on the same side of the bottom plate as the second fixing part.

5. The door lock safety mechanism according to claim 4, wherein the second retaining portion comprises a first cavity, the second retaining portion is provided with a first through hole passing through the first cavity, and the position of the first through hole corresponds to the position of the first locking through hole.

6. A hatch lock safety mechanism according to claim 5, characterised in that said second holding part further comprises a first slider and a first resilient member; wherein:

the first elastic piece is arranged between the sliding plate and the top of the first cavity body, and two ends of the first elastic piece are respectively connected with the sliding plate and the top of the first cavity body.

7. A door lock safety mechanism according to claim 6, wherein said sliding plate is provided with a second through hole;

8. The door lock safety mechanism according to claim 7, wherein a sliding slot is provided at the top of the second support portion, and the sliding slot is communicated with the second cavity.

9. A door lock safety mechanism according to claim 8, wherein said second support portion further comprises a second slider and a second resilient member;

the second slider includes a slide portion and a manual operation portion; the sliding part comprises a sliding part body and a convex column, and the convex column is formed by extending outwards from the sliding part body; the sliding part body is arranged in the second cavity and slides in the second cavity; the convex column penetrates through the sliding grooves and slides between the sliding grooves; the manual operation part is fixedly arranged on the convex column;

the second elastic piece is arranged between the sliding part body and the inner side edge of the closed end of the second cavity, and two ends of the second elastic piece are respectively connected with the sliding part body and the inner side edge of the closed end of the second cavity.

10. A manned aircraft comprising a door, a cockpit and a door lock safety mechanism according to any one of claims 1 to 9; wherein: the cabin door lock safety mechanism comprises a first lock fixing piece and a second lock fixing piece, the first lock fixing piece is fixed on the cabin door, the second lock fixing piece is fixed on the cabin, and the second lock fixing piece is automatically locked in the first lock fixing piece when the cabin door is closed.