Airplane door and ladder integrated cabin door opening keeping mechanism

Abstract

The invention belongs to the technical field of design of an aircraft door-ladder integrated cabin door opening keeping mechanism, and particularly relates to an aircraft door-ladder integrated cabin door opening keeping mechanism which is mainly composed of a triangular frame, a cabin door connecting rod, a roller bearing, a lock support, a lock body and a reset spring, is simple in overall structure and low in weight, is of a pure mechanical structure and can be opened when a cabin door is opened. The cabin door is automatically and reliably locked at the opening position through the lock hook by means of the reset spring, performance attenuation is not prone to occurring, and the cabin door can be reliably kept at the opening position for a long time.

Description

Technical Field

[0001] The present application belongs to the technical field of design of an aircraft door-ladder-in-one cabin door opening and holding mechanism, and in particular relates to an aircraft door-ladder-in-one cabin door opening and holding mechanism. Background Art

[0002] After the aircraft door-and-ladder door is opened, the top of the door touches the ground and is prone to accidental folding in strong winds, causing structural damage or even safety accidents. For this reason, a door-and-ladder door opening retention mechanism is designed to keep the door in the open position after it is opened.

[0003] Currently, the door-ladder hatch opening retention mechanism mostly relies on gas springs or hydraulic actuators to keep the hatch in the open position, where:

[0004] The technical solution of relying on gas springs to keep the hatch door in an open state is that the gas springs are prone to performance degradation and it is difficult to reliably keep the hatch door in an open position for a long time. In addition, the procurement cost of gas springs is high. The economics are not good;

[0005] The technical solution of relying on a hydraulic actuator to keep the door in the open position is usually complex in structure, poor in reliability, and heavy in weight. In addition, when the aircraft is parked, special ground support equipment is required to supply pressure, which has poor security. Summary of the invention

[0006] The purpose of the present application is to provide an aircraft door-ladder-combined cabin door open retention mechanism to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of this application is:

[0008] An aircraft door-ladder integrated door opening and holding mechanism comprises:

[0009] A tripod, the top corner of which is hinged on the door frame, one bottom corner is the first bottom corner, and the other bottom corner is the second bottom corner;

[0010] A door connecting rod, one end of which is hinged to the second bottom corner and the other end of which is hinged to the door;

[0011] A roller bearing is disposed on the first bottom angle;

[0012] A lock support, connected to the door frame, having a limit groove thereon;

[0013] The lock body is hinged on the lock support and has a stop protrusion thereon, the stop protrusion extends into the limit groove and matches with the limit groove clearance; the lock body has a lock hook and a handle; the top of the lock hook has a wedge surface outside;

[0014] The two ends of the return spring are connected to the lock body and the lock support, and the stop protrusion is pressed against the side wall of the limit groove in the counterclockwise direction by elastic force;

[0015] When the hatch is closed, the hatch is retracted, the second bottom corner is above the first bottom corner, and the tripod and the hatch connecting rod are in a folded state;

[0016] When the hatch is opened, the hatch is lowered, driving the hatch connecting rod to rotate, and then driving the tripod to rotate, so that the first bottom angle rotates to above the second bottom angle, and the roller bearing contacts the wedge surface, thereby squeezing the wedge surface, pushing the lock body to overcome the elastic force of the reset spring and rotate in the clockwise direction, and the roller bearing slides along the wedge surface, bypasses the top of the lock hook, and slides into the top of the lock hook. Under the elastic force of the reset spring, the lock body rotates counterclockwise, and the top of the lock hook hooks the roller bearing, locking the hatch in the open position, and the tripod and hatch connecting rod are in the unfolded state.

[0017] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door opening retention mechanism, when the cabin door is opened, a distance is left between the top end of the locking hook and the roller bearing.

[0018] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door opening retention mechanism, the cabin door connecting rod and the second bottom corner are hinged with pins through a single-double-ear structure.

[0019] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door opening retention mechanism, the two ends of the cabin door connecting rod are hinged to the cabin door by pins through a single-double ear structure.

[0020] In some optional embodiments, in the above-mentioned aircraft door-ladder-combined-cabin door opening retention mechanism, the two edges at the first bottom corner are connected by bolts through a single-double-ear structure.

[0021] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door opening retention mechanism, the connecting rod of the roller bearing is inserted into the opening at the top end of the single-ear and double-ear structural bolt connecting the two sides at the first bottom corner of the tripod.

[0022] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door open retention mechanism, the roller bearing is inserted into the connecting rod in the top opening hole of the single-ear and double-ear structural bolt between the two sides at the first bottom corner of the connecting tripod, and is positioned by a pin.

[0023] In some optional embodiments, in the above-mentioned aircraft door-ladder integrated door opening and holding mechanism, the lock support has a double ear piece;

[0024] The lock body is arranged between the two ear pieces on the lock support.

[0025] In some optional embodiments, in the above-mentioned aircraft door-ladder integrated door open retention mechanism, the lock body and the double ear pieces on the lock support are hinged by a pin shaft.

[0026] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door open retention mechanism, the support is provided with a hanging ear, and one end of the return spring facing the lock support is hooked on the hanging ear with a hook.

[0027] In some optional embodiments, in the above-mentioned aircraft door-ladder-combined-cabin door open retention mechanism, a pin is connected to the lock body, and one end of the return spring facing the lock body is hooked on the pin with a hook.

[0028] In some optional embodiments, the above-mentioned aircraft door-ladder integrated door opening and holding mechanism further includes:

[0029] The hinged seat is connected to the door frame and hinged to the top angle of the tripod.

[0030] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door opening retention mechanism, the hinged seat and the top angle of the tripod are hinged with pins through a single-double-ear structure.

[0031] In some optional embodiments, in the above-mentioned aircraft door-ladder-in-one cabin door opening and holding mechanism, the bottom of the limiting groove is arc-shaped;

[0032] The lock body is provided with a mounting hole;

[0033] The aircraft door-ladder integrated door opening and holding mechanism further comprises:

[0034] The stop pin has a rear end extending into the mounting hole and a front end in a hemispherical shape, forming a stop protrusion;

[0035] The retaining spring is arranged in the mounting hole, with its two ends abutting against the bottom of the mounting hole and the rear end of the stop pin, and relying on elastic force, the front end of the stop pin is kept against the bottom of the limiting groove.

[0036] In some optional embodiments, in the above-mentioned aircraft door-ladder integrated door opening retention mechanism, the lock body has an adjustment hole connected to the bottom of the mounting hole;

[0037] The aircraft door-ladder integrated door opening and holding mechanism further comprises:

[0038] The adjusting bolt is threadedly connected in the adjusting hole and abuts against one end of the retaining spring facing away from the limiting groove.

[0039] In some optional embodiments, the above-mentioned aircraft door-ladder integrated door opening and holding mechanism further includes:

[0040] A sleeve, one end of which is threadedly connected to the adjustment hole, and the other end is sleeved on the outer circumference of the retaining spring;

[0041] The adjusting bolt is threadedly connected to the other end of the sleeve.

[0042] This application has at least the following beneficial technical effects:

[0043] Provided is an aircraft door-ladder-in-one cabin door opening retention mechanism, which is mainly composed of a tripod, a cabin door connecting rod, a roller bearing, a lock support, a lock body, and a return spring. The overall structure is simple, the weight is low, and it is a purely mechanical structure. When the cabin door is opened, the return spring can be used to automatically and reliably lock the cabin door in an open position with a lock hook, the performance degradation is not likely to occur, and the cabin door can be reliably kept in the open position for a long time. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 This is a schematic diagram of the aircraft door-ladder integrated door opening and holding mechanism provided in an embodiment of the present application, when the door is closed;

[0045] Figure 2 is a schematic diagram of the contact between the roller bearing and the wedge surface in the aircraft door-ladder integrated door opening retention mechanism provided by an embodiment of the present application when the door is opened;

[0046] Figure 3 It is a schematic diagram of a roller bearing in an aircraft door-ladder integrated door opening retention mechanism provided by an embodiment of the present application sliding along a wedge surface and bypassing a top end of a lock hook when the door is opened;

[0047] Figure 4 It is a schematic diagram of the top end of the lock hook in the door-ladder-in-one door opening retention mechanism provided in an embodiment of the present application hooking the roller bearing when the door is opened;

[0048] Figure 5 This is a schematic diagram of the aircraft door-ladder integrated door opening retention mechanism provided by an embodiment of the present application, when the door is open;

[0049] Figure 6 It is a schematic diagram of the cooperation between the first bottom corner of the tripod and the roller bearing in the door-ladder-in-one cabin door opening and holding mechanism provided in an embodiment of the present application;

[0050] Figure 7 It is a schematic diagram of the assembly of the lock support and the lock body related structure provided in the embodiment of the present application;

[0051] in:

[0052] 1-tripod; 2-door frame; 3-door connecting rod; 4-door; 5-roller bearing; 6-lock support; 7-lock body; 8-lock hook; 9-handle; 10-reset spring; 11-hinge seat; 12-stop pin; 13-retaining spring; 14-adjusting bolt; 15-sleeve.

[0053] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0054] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0055] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0056] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0057] An aircraft door-ladder integrated door opening and holding mechanism comprises:

[0058] A tripod 1, the top corner of which is hinged on a door frame 2, one bottom corner being a first bottom corner, and the other bottom corner being a second bottom corner;

[0059] The hatch connecting rod 3 has one end hinged on the second bottom corner and the other end hinged on the hatch 4; the bottom of the hatch 4 is hinged to the bottom of the hatch frame 2 through a suspension hinge;

[0060] A roller bearing 5 is arranged on the first bottom angle;

[0061] A lock support 6 is connected to the door frame 2 and has a limit groove thereon;

[0062] The lock body 7 is hinged on the lock support 6 and has a stop protrusion thereon, which extends into the limit groove and fits with the limit groove gap; the lock body 7 has a lock hook 8 and a handle 9; the lock hook 8 and the handle 9 roughly form a V-shaped structure, and the top of the lock hook 8 has a wedge surface outside;

[0063] The two ends of the return spring 10 are connected to the lock body 7 and the lock support 6, and the stop protrusion is pressed against the side wall of the limit groove in the counterclockwise direction by elastic force;

[0064] When the hatch 4 is closed, the hatch 4 is retracted, the second bottom angle is above the first bottom angle, and the tripod 1 and the hatch connecting rod 3 are in a folded state. Figure 1 As shown;

[0065] When the hatch 4 is opened, the hatch 4 is lowered, driving the hatch connecting rod 3 to rotate, thereby driving the tripod 1 to rotate, so that the first bottom angle rotates to above the second bottom angle, and the roller bearing 5 contacts the wedge surface, thereby squeezing the wedge surface. Figure 2 As shown, the lock body 7 is pushed to overcome the elastic force of the reset spring 10 and rotate in the clockwise direction, the stop protrusion is separated from the side wall of the limit groove on the counterclockwise side, and the roller bearing 5 slides along the wedge surface and bypasses the top of the lock hook 8, as shown in FIG. Figure 3 As shown, the lock body 7 slides into the top of the lock hook 8. Under the elastic force of the reset spring 10, the lock body 7 rotates counterclockwise, and the stop protrusion abuts against the side wall of the limit groove on the counterclockwise side again, automatically resetting, and the top of the lock hook 8 hooks the roller bearing 5. Figure 4 As shown, the door 4 is locked in the open position to prevent it from being accidentally folded up due to strong winds, causing structural damage and safety accidents. At this time, the tripod 1 and the door connecting rod 3 are in the unfolded state, and the bottom edge of the tripod 1 faces upward and can be used as a handrail. Figure 5 As shown;

[0066] When it is necessary to close the hatch door, the handle 9 can be pressed to make the lock body 7 overcome the elastic force of the return spring 10 and rotate in the clockwise direction, the stop protrusion is separated from the side wall on the counterclockwise side of the limiting groove, and the top of the lock hook 8 is separated from the roller bearing 5, thereby releasing the lock on the open position of the hatch door 4, and the hatch door 4 can be folded and closed. When the handle 9 is pressed, the extreme position of the lock body 7 rotating in the clockwise direction is the position corresponding to the position when the stop protrusion abuts against the side wall on the clockwise side of the limiting groove, thereby preventing the lock body 7 from flipping over and ensuring the normal function of the lock body 7. After releasing the handle 9, under the action of the elastic force of the return spring 10, the lock body 7 rotates in the counterclockwise direction, and the stop protrusion abuts against the side wall on the counterclockwise side of the limiting groove again, and automatically resets.

[0067] The aircraft door-ladder-in-one cabin door opening holding mechanism disclosed in the above embodiment is mainly composed of a tripod 1, a cabin door connecting rod 3, a roller bearing 5, a lock support 6, a lock body 7, and a return spring 10. The overall structure is simple, the weight is low, and it is a purely mechanical structure. When the cabin door is opened, the return spring 10 can be used to automatically and reliably lock the cabin door 4 in the open position with the lock hook 8. It is not easy to have performance degradation, and the cabin door 4 can be reliably kept in the open position for a long time.

[0068] After the cabin door 4 is opened, if personnel enter the cabin or cargo is loaded into the cabin, the weight of the aircraft will increase, causing the center of gravity of the aircraft to drop. In this process, if the top of the locking hook 8 is tightly hooked on the roller bearing 5, the cabin door 4 will be restricted from adaptively rotating upward relative to the cabin door frame 2, so that greater contact stress is generated between the cabin door 4 and the ground, and between the top of the locking hook 8 and the roller bearing 5. For this reason, in the aircraft door-ladder integrated cabin door opening retention mechanism disclosed in the above embodiment, it is designed that when the cabin door 4 is opened, a distance is left between the top of the locking hook 8 and the roller bearing 5, so that when the center of gravity of the aircraft drops, there is a margin for the adaptive upward rotation of the cabin door 4 relative to the cabin door frame 2.

[0069] In some optional embodiments, in the aircraft door-ladder-in-one cabin door opening retention mechanism disclosed in the above embodiments, both ends of the cabin door connecting rod 3 are hinged to the second bottom corner and the cabin door 4 by pins through a single-double ear structure.

[0070] In some optional embodiments, in the aircraft door-ladder-in-one door opening and holding mechanism disclosed in the above embodiments, the two sides at the first bottom corner of the tripod 1 are connected by bolts through a single-double-ear structure, and the connecting rod of the roller bearing 5 is inserted into the opening at the top of the bolt and positioned by a pin, such as Figure 6 shown.

[0071] In some optional embodiments, in the aircraft door-ladder integrated door opening and holding mechanism disclosed in the above embodiments, the lock support 6 has a double ear piece;

[0072] The lock body 7 is arranged between the two ear pieces and is hinged to the two ear pieces by a pin shaft.

[0073] In some optional embodiments, in the aircraft door-ladder integrated door opening retention mechanism disclosed in the above embodiments, the lock support 6 has a hanging ear, and the end of the return spring 10 facing the lock support 6 is hooked on the hanging ear with a hook;

[0074] The lock body 7 is connected with a pin, and one end of the return spring 10 facing the lock body 7 is hooked on the pin with a hook.

[0075] In some optional embodiments, the aircraft door-ladder integrated door opening and holding mechanism disclosed in the above embodiments further includes:

[0076] The hinge seat 11 is connected to the door frame 2 and is hinged to the top corner by pins through a single-ear and double-ear structure.

[0077] In some optional embodiments, in the aircraft door-ladder integrated door opening and holding mechanism disclosed in the above embodiments, the bottom of the limiting groove is arc-shaped;

[0078] The lock body 7 is provided with a mounting hole, which can be located at the intersection of the lock hook 8 and the handle 9;

[0079] The aircraft door-ladder integrated door opening and holding mechanism further comprises:

[0080] The stop pin 12 has a rear end extending into the mounting hole and a front end in a hemispherical shape, forming a stop protrusion;

[0081] The retaining spring 13 is arranged in the mounting hole, with its two ends resting against the bottom of the mounting hole and the rear end of the stop pin 12. Relying on the elastic force, the front end of the stop pin 12 is kept against the bottom of the limiting groove. During the rotation of the lock body 7, it can adaptively extend and retract, and the front end of the stop pin 12 and the bottom of the limiting groove are in spherical arc contact, which greatly reduces the friction between the lock body 7 and the lock support 6 during the rotation process.

[0082] In some optional embodiments, in the aircraft door-ladder integrated door opening and holding mechanism disclosed in the above embodiments, the lock body 7 has an adjustment hole connected to the bottom of the mounting hole;

[0083] The aircraft door-ladder integrated door opening and holding mechanism further comprises:

[0084] The adjusting bolt 14 is threadedly connected in the adjusting hole and abuts against one end of the retaining spring 13 facing away from the limiting groove. By twisting, the pre-tightening degree of the retaining spring 13 can be adjusted so that the retaining spring 13 is pressed against the rear end of the stop pin 12 with appropriate force.

[0085] In some optional embodiments, the aircraft door-ladder integrated door opening and holding mechanism disclosed in the above embodiments further includes:

[0086] A sleeve 15, one end of which is threadedly connected to the adjustment hole, and the other end is sleeved on the outer circumference of the retaining spring 13;

[0087] The adjusting bolt 14 is threadedly connected to the other end of the sleeve 15. Figure 7 shown.

[0088] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0089] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An aircraft door-ladder integrated door opening and holding mechanism, characterized in that: include: A tripod (1), the top corner of which is hinged on the door frame (2), one bottom corner being a first bottom corner, and the other bottom corner being a second bottom corner; A door connecting rod (3), one end of which is hinged on the second bottom corner, and the other end of which is hinged on the door (4); A roller bearing (5) is arranged on the first bottom corner; A lock support (6) is connected to the door frame (2) and has a limiting groove thereon; The lock body (7) is hinged on the lock support (6) and has a stop protrusion thereon, the stop protrusion extends into the limit groove and is clearance-matched with the limit groove; the lock body (7) has a lock hook (8) and a handle (9); the top end of the lock hook (8) has a wedge surface outside; A return spring (10), both ends of which are connected to the lock body (7) and the lock support (6), and relies on elastic force to make the stop protrusion abut against the side wall of the limiting groove on the counterclockwise side; When the hatch (4) is closed, the hatch (4) is retracted, the second bottom corner is above the first bottom corner, and the tripod (1) and the hatch connecting rod (3) are in a folded state; When the hatch (4) is opened, the hatch (4) is lowered, driving the hatch connecting rod (3) to rotate, thereby driving the tripod (1) to rotate, so that the first bottom angle rotates to above the second bottom angle, the roller bearing (5) contacts the wedge surface, thereby squeezing the wedge surface, pushing the lock body (7) to overcome the elastic force of the return spring (10) and rotate in the clockwise direction, the roller bearing (5) slides along the wedge surface, bypasses the top of the lock hook (8), and slides into the top of the lock hook (8), under the elastic force of the return spring (10), the lock body (7) rotates in the counterclockwise direction, the top of the lock hook (8) hooks the roller bearing (5), and the hatch (4) is locked in the open position, and the tripod (1) and the hatch connecting rod (3) are in the unfolded state.

2. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: When the hatch (4) is opened, a distance is left between the top end of the lock hook (8) and the roller bearing (5).

3. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The door connecting rod (3) and the second bottom corner are hinged by a pin through a single-double-ear structure.

4. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The two ends of the door connecting rod (3) and the door (4) are hinged with pins through a single-double-ear structure.

5. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The two sides at the first bottom corner are connected by bolts through a single-double-ear structure.

6. The aircraft door-ladder integrated door opening and holding mechanism according to claim 5, characterized in that: The connecting rod of the roller bearing (5) is inserted into the opening at the top end of the single-ear and double-ear structural bolt between the two sides at the first bottom angle of the connecting tripod (1).

7. The aircraft door-ladder integrated door opening and holding mechanism according to claim 5, characterized in that: The roller bearing (5) is inserted into a connecting rod in a hole at the top end of a single-ear and double-ear structural bolt between two sides at the first bottom corner of the connecting tripod (1) and positioned by a pin.

8. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The lock support (6) is provided with double ear pieces; The lock body (7) is arranged between the two ear pieces on the lock support (6).

9. The aircraft door-ladder integrated door opening and holding mechanism according to claim 8, characterized in that: The lock body (7) and the double ear pieces on the lock support (6) are hinged by a pin shaft.

10. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The support (6) is provided with a hanging ear, and one end of the return spring (10) facing the lock support (6) is hooked on the hanging ear by a hook.

11. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: A pin is connected to the lock body (7), and one end of a return spring (10) facing the lock body (7) is hooked on the pin by a hook.

12. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: Also includes: The hinged seat (11) is connected to the door frame (2) and is hinged to the top angle of the tripod (1).

13. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The hinged seat (11) and the top corner of the tripod (1) are hinged by pins through a single-double-ear structure.

14. The aircraft door-ladder integrated door opening and holding mechanism according to claim 1, characterized in that: The bottom of the limiting groove is arc-shaped; The lock body (7) is provided with a mounting hole; The aircraft door-ladder integrated door opening and holding mechanism further comprises: A stop pin (12), the rear end of which extends into the mounting hole and the front end of which is hemispherical, forming a stop protrusion; The retaining spring (13) is arranged in the mounting hole, with its two ends abutting against the bottom of the mounting hole and the rear end of the stop pin (12), and relying on elastic force, the front end of the stop pin (12) is kept against the bottom of the limiting groove.

15. The aircraft door-ladder integrated door opening and holding mechanism according to claim 14, characterized in that: The lock body (7) is provided with an adjustment hole connected to the bottom of the installation hole; The aircraft door-ladder integrated door opening and holding mechanism further comprises: The adjusting bolt (14) is threadedly connected in the adjusting hole and abuts against one end of the retaining spring (13) which faces away from the limiting groove.

16. The aircraft door-ladder integrated door opening and holding mechanism according to claim 15, characterized in that: Also includes: A sleeve (15), one end of which is threadedly connected to the adjustment hole, and the other end is sleeved on the outer circumference of the retaining spring (13); The adjusting bolt (14) is threadedly connected to the other end of the sleeve (15).

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