A quick-release door hinge mechanism for aircraft

Abstract

The present invention provides a hinge mechanism for quickly disengaging an aircraft door, comprising a first hinge mechanism and a second hinge mechanism. The first hinge mechanism comprises a first supporting structure, a first locking structure, and a first fixing structure. The first supporting structure is mounted on the aircraft fuselage, one side of the first fixing structure is connected to the aircraft door, and the other side is locked and connected to the first supporting structure via the first locking structure. The second hinge mechanism comprises a second supporting structure, a second locking structure, and a second fixing structure. The second supporting structure is mounted on the aircraft fuselage, one side of the second fixing structure is connected to the aircraft door, and the other side is locked and connected to the second supporting structure via the second locking structure. The first locking structure and the second locking structure are connected by a connecting mechanism. The present invention is simple to operate. The door can be disengaged from the fuselage by simply pulling the middle portion of a steel cable, without requiring additional operating steps, thereby ensuring that pilots can quickly evacuate in an emergency.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft cabin doors, and in particular to a hinge mechanism for a quick-release aircraft cabin door. Background Art

[0002] In an emergency situation, such as a bird strike or an inability to recover from a spin, the pilot must quickly make a decision and parachute out. However, forward-opening doors are difficult to open due to airflow. Without other measures, the pilot loses the optimal time to parachute out, resulting in unnecessary losses. The present invention addresses this problem by providing a quick-release aircraft door hinge mechanism. In an emergency, the pilot only needs to pull a cable to quickly release the door, creating optimal conditions for the pilot's escape. Summary of the Invention

[0003] In response to the above-mentioned technical problems, a hinge mechanism for a quick-release door of an aircraft is provided.

[0004] The technical means adopted in the present invention are as follows:

[0005] A hinge mechanism for a quick-release aircraft door comprises: a first hinge mechanism and a second hinge mechanism disposed above and connected to each other, the first hinge mechanism comprising a first supporting structure, a first locking structure, and a first fixing structure; the first supporting structure is mounted on the aircraft fuselage; one side of the first fixing structure is connected to the aircraft door, and the other side is locked to the first supporting structure via the first locking structure;

[0006] The second hinge mechanism includes a second supporting structure, a second locking structure, and a second fixing structure. The second supporting structure is mounted on the aircraft fuselage. One side of the second fixing structure is connected to the aircraft door, and the other side is locked to the second supporting structure via the second locking structure.

[0007] The first locking structure and the second locking structure are connected by a connecting mechanism. By pulling the connecting mechanism, the first locking structure and the second locking structure on the upper and lower sides are pulled, and the locking connection between the first supporting structure and the first fixed structure, and the second supporting structure and the second fixed structure is released, thereby realizing the detachment of the hatch.

[0008] Furthermore, the first hinge mechanism and the second hinge mechanism have the same structure and are symmetrically arranged.

[0009] Furthermore, the first supporting structure includes a base, and the base is connected to the aircraft fuselage skin through screws.

[0010] Furthermore, the first fixing structure includes a hinge seat, and the hinge seat is connected to the aircraft door via a hinge shaft.

[0011] Furthermore, the first locking structure includes a hinge limit block, a first spring, a steel cable connector and a second spring, wherein the first spring is sleeved on the steel cable connector;

[0012] The base includes a vertical support plate and a first support plate, a second support plate and a third support plate connected to the vertical support plate from top to bottom, wherein the first support plate, the second support plate and the third support plate are respectively provided with a first through hole, a second through hole and a third through hole, and the first through hole, the second through hole and the third through hole are coaxial;

[0013] The vertical support plate is provided with a first through slot and a second through slot, wherein the first through slot is located between the first support plate and the second support plate, and the second through slot is located between the second support plate and the third support plate;

[0014] A first protrusion is provided on the middle portion of one side of the hinge seat body close to the base, the first protrusion is inserted into the first through slot and passes through, and a fourth through hole is formed on the end of the first protrusion passing through the first through slot, the fourth through hole being coaxial with the first through hole and the second through hole;

[0015] The body of the steel cable connector and the first spring are both located between the second support plate and the third support plate. One end of the steel cable connector is threadedly connected to the hinge limit block, and the other end passes through the third through hole and is connected to the connecting mechanism. The connecting mechanism is located between the upper and lower bases.

[0016] The hinge stop block includes a main structure and a protrusion connected to the main structure. The protrusion is inserted into the second through slot and can move up and down in the second through slot. One side of the main structure is inserted into the second through hole, the fourth through hole and the first through hole in sequence from bottom to top. A threaded hole is provided in the middle of the other side for threaded connection with one end of the steel cable connector. The first spring is in a compressed state, generating a reverse thrust to push the hinge stop block tightly.

[0017] A second protrusion is provided on the side of the hinge seat body close to the base, and a second spring is sleeved on the second protrusion. One end of the second spring is connected to the hinge seat body and is compressed between the hinge seat and the fuselage.

[0018] Furthermore, a limit block is provided below the second through slot, and the limit block is connected to the vertical support plate of the base through a first screw, so as to limit the movement of the protrusion.

[0019] Furthermore, the main structure of the hinge limiting block is a square structure, and the first through hole, the second through hole and the fourth through hole are square through holes.

[0020] Furthermore, two coaxial through holes are opened on the side of the hinge seat body away from the base, the hinge shaft is connected through the two through holes, and the end of the hinge shaft passing through the through hole is connected to a second cotter pin.

[0021] Furthermore, the connecting mechanism includes a steel cable, and both ends of the steel cable are connected to the upper and lower steel cable connectors respectively through second screws.

[0022] Furthermore, two pulley groups with the same structure and symmetrical arrangement are provided near the upper and lower steel cable connectors, the pulley group comprising a pulley bracket, a first cotter pin, a pulley shaft and a pulley, the pulley bracket being connected to the fuselage by screws, the pulley being connected to the pulley bracket by the pulley shaft, wherein the pulley bracket is provided with two mounting holes, the pulley is located between the two mounting holes, the pulley shaft passes through the pulley and the two mounting holes, and one end of the pulley shaft passing through the mounting hole is connected to the first cotter pin;

[0023] An accommodating space is provided between the pulley and the body of the pulley bracket, and the steel cable passes through the accommodating space.

[0024] Compared with the prior art, the present invention has the following advantages:

[0025] 1. The hinge seat is detachable. The hinge seat of the present invention is connected to the base through a hinge limit block. The hinge limit block is a square structure, so that the hinge seat will be fixed and cannot rotate, ensuring that the hinge axis is fixed and the hatch can be used normally.

[0026] 2. Highly reliable disengagement mechanism. The upper and lower hinge mechanisms of the present invention are installed in opposite directions. The springs in the cable connector push the hinge limit blocks in opposite directions. They are connected by a cable. When the cable is stressed, it drives the hinge limit blocks to move. The hinge limit blocks compress the springs. When the hinge limit blocks are disengaged from the hinge seat, the compression springs on the hinge seat push the hinge seat out. At this time, even if the pilot releases the cable, the hinge limit blocks will not pass through the holes in the hinge seat to secure the hinge seat again. The disengagement mechanism is safe and reliable.

[0027] 3. Single-point unlocking: This mechanism features a single-point unlocking function that is easy to operate. Simply pull the middle part of the cable to detach the door from the fuselage, eliminating the need for additional steps and ensuring that pilots can evacuate quickly in an emergency.

[0028] Based on the above reasons, the present invention can be widely promoted in the fields of aviation and the like. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0030] Figure 1 It is a structural schematic diagram of the present invention.

[0031] Figure 2 It is an exploded view of the local structure of the present invention.

[0032] Figure 3 It is a structural schematic diagram of the upper half of the present invention.

[0033] Figure 4 It is a structural schematic diagram of the hinge seat and the second spring of the present invention.

[0034] Figure 5 It is a structural schematic diagram of the hinge limit block and the base of the present invention.

[0035] Figure 6 It is a structural schematic diagram of the hinge limit block, base and limit block of the present invention.

[0036] In the figure: 1. Hinge base; 2. Hinge shaft; 3. Base; 4. Hinge stopper; 5. First spring; 6. Cable connector; 7. Second spring; 8. First screw; 9. Stopper; 10. Second screw; 11. Cable; 12. Pulley bracket; 13. First cotter pin; 14. Pulley shaft; 15. Pulley; 16. Second cotter pin;

[0037] 101. First protrusion; 102. Fourth through hole;

[0038] 31. First through slot; 32. Second through slot; 33. First support plate; 34. Second support plate; 35. Third support plate;

[0039] 41. Main structure; 42. Bump. DETAILED DESCRIPTION

[0040] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0041] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is in no way intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0042] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they indicate the presence of features, steps, operations, devices, components and / or combinations thereof.

[0043] Unless otherwise specifically stated, the relative arrangement of the parts and steps, numerical expressions and numerical values ​​set forth in these embodiments do not limit the scope of the present invention. At the same time, it should be clear that, for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that similar numbers and letters represent similar items in the following figures, and therefore, once an item is defined in one figure, it does not need to be further discussed in subsequent figures.

[0044] In the description of the present invention, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "horizontal, vertical, vertical, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention: the directional words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

[0045] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figures. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figures. For example, if the device in the drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below their position devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0046] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0047] The present invention provides a quick-release aircraft door hinge mechanism. This mechanism combines normal hinge functions with quick-release capabilities. It is primarily used for general-purpose aircraft conducting high-risk tests such as spin tests and stall characteristics, but can also be used on aircraft in normal use.

[0048] In the event of an emergency, such as an accidental bird strike or an inability to recover from a spin, the pilot needs to make a quick decision and parachute to escape. However, the forward-opening door is difficult to open normally due to airflow. Without other measures, the pilot will lose the best time to parachute, resulting in unnecessary losses.

[0049] The present invention provides a door hinge mechanism that, in addition to its normal hinge functions, also features a quick-release feature. This feature allows the door to be quickly released by operating a pull-wire handle. Airflow or a forceful push from the pilot can allow the door to be quickly discarded, allowing the pilot to quickly escape. The production equipment used to complete the present invention primarily utilizes CNC machine tools, which offer high precision and consistent product quality. Special processing equipment is not required to complete the present invention.

[0050] like Figure 1-6As shown, the present invention discloses a hinge mechanism for quickly disengaging an aircraft door. The mechanism consists of two hinge mechanisms, the upper and lower parts, and the two parts have the same structure. It mainly consists of a hinge seat 1, a hinge shaft 2, a base 3, a hinge limit block 4, a limit block 9, a steel cable 11, a first spring 5, a steel cable connector 6, a second spring 7, a pulley 15, a pulley bracket 12, and a pulley shaft 14. The hinge seat 1 and the hinge shaft 2 are made of stainless steel 0Cr18Ni9 (304), the steel cable 11 is made of stainless steel 304, the first spring 5 and the second spring 7 are standard parts, and the remaining structural parts are made of aluminum alloy 7075-T7351 and are all machined.

[0051] Hinge base 1 is connected to the aircraft cabin door via hinge shaft 2 and to the fuselage via hinge stopper 4. A square slot is defined in base 3 to prevent hinge base 1 from rotating. Base 3 is screwed to the fuselage skin. Stopper 9 is connected to base 3 via first screw 8, primarily to limit the movement of hinge stopper 4. A cable connector 6 has one end screwed to hinge stopper 4 and the other end connected to cable 11 via second screw 10. A spring supports hinge stopper 4 and base 3, securing hinge stopper 4 in place. Upper and lower cable connectors 6 are connected by screws and cable 11. Two pulley blocks are located near these two cable connectors. These pulley blocks ensure that when the middle cable 11 is pulled, the force applied to the upper and lower cable connectors 6 is axial, aligning with the direction of motion. This minimizes resistance and facilitates the disengagement of hinge stopper 4 from hinge base 1, thereby enabling rapid door detachment.

[0052] Specifically, the base 3 includes a vertical support plate and a first support plate 33, a second support plate 34 and a third support plate 35 connected to the vertical support plate from top to bottom. The first support plate 33, the second support plate 34 and the third support plate 35 are respectively provided with a first through hole, a second through hole and a third through hole, and the first through hole, the second through hole and the third through hole are coaxial; the vertical support plate is provided with a first through slot 31 and a second through slot 32, the first through slot 31 is located between the first support plate 33 and the second support plate 34, and the second through slot 32 is located between the second support plate 34 and the third support plate 35.

[0053] A first protrusion 101 is provided on the middle part of one side of the main body of the hinge seat 1 close to the base 3. The first protrusion 101 is inserted into the first through groove 31 and passes through it. A fourth through hole 102 is provided on the end of the first protrusion 101 that passes through the first through groove 31. The fourth through hole 102 is coaxial with the first through hole and the second through hole, and the fourth through hole 102 is located between the first through hole and the second through hole.

[0054] The main body of the steel cable connector 6 and the first spring 5 are both located between the second support plate 34 and the third support plate 35. One end of the steel cable connector 6 is threadedly connected to the hinge limit block 4, and the other end passes through the third through hole and is connected to the connecting mechanism, which is located between the upper and lower bases 3.

[0055] The hinge stopper 4 includes a main structure 41 and a protrusion 42 connected to the main structure 41. The protrusion 42 is inserted into the second through-slot 32 and can move up and down within the second through-slot 32. One side of the main structure 41 is sequentially inserted into the second through-hole, the fourth through-hole 102, and the first through-hole from bottom to top. A threaded hole is defined in the middle of the other side for threaded connection with one end of the cable connector 6. The hinge stopper 4 is inserted into the fourth through-hole 102, the second through-hole, and the first through-hole of the hinge base 1, and the first spring 5 is compressed to push the hinge stopper 4 in the opposite direction, thereby achieving a locked connection between the hinge base 1 and the base 3.

[0056] A second protrusion is provided on the main body of the hinge seat 1 near the base 3. A second spring 7 is sleeved on the second protrusion. One end of the second spring 7 is connected to the main body of the hinge seat 1 and is compressed between the hinge seat 1 and the fuselage.

[0057] A limit block 9 is provided below the second through slot 32 . The limit block 9 is connected to the vertical support plate of the base 3 via a first screw 8 and is used to limit the movement of the protrusion 42 .

[0058] The main structure 41 of the hinge limiting block 4 is a square structure, and the first through hole, the second through hole and the fourth through hole 102 are square through holes.

[0059] Two coaxial through holes are formed on the main body of the hinge seat 1 on a side away from the base 3 , the hinge shaft 2 passes through the two through holes, and the end of the hinge shaft 2 passing through the through holes is connected to a second cotter pin 16 .

[0060] Both ends of the steel cable 11 are connected to the upper and lower steel cable connectors 6 via second screws 10 .

[0061] Two pulley blocks of identical structure and symmetrical arrangement are provided near the upper and lower cable connectors 6. The pulley blocks include a pulley bracket 12, a first cotter pin 13, a pulley shaft 14, and a pulley 15. The pulley bracket 12 is connected to the body via screws, and the pulley 15 is connected to the pulley bracket 12 via the pulley shaft 14. The pulley bracket 12 has two mounting holes, with the pulley 15 located between the two mounting holes. The pulley shaft 14 extends through the pulley 15 and the two mounting holes, and one end of the pulley shaft 14 extending through the mounting holes is connected to the first cotter pin 13. A storage space is provided between the pulley 15 and the body of the pulley bracket 12, through which the steel cable 11 extends.

[0062] When the steel cable 11 between the two pulley blocks is pulled, the upper and lower steel cable connectors 6 are pulled through the steel cable 11, and the two steel cable connectors 6 move toward each other. The two steel cable connectors 6 respectively drive the two hinge stoppers 4 to move, and the hinge stoppers 4 move in the direction away from the first through hole. At the same time, the protrusion 42 of each hinge stopper 4 moves along the corresponding second through slot 32. During the movement of the hinge stopper 4, the first spring 5 is continuously compressed, and the hinge stopper 4 gradually disengages from the first through hole and the fourth through hole 102 in sequence, thereby disengaging the hinge stopper 4 from the hinge seat 1. After the hinge seat 1 is disengaged from the hinge stopper 4, the second spring 7 applies a thrust to the hinge seat 1 under the action of elastic recovery, pushing the hinge seat 1 out, and the first protrusion 101 of the hinge seat 1 disengages from the first through slot 31, that is, the upper and lower hinge seats 1 and the hatch are quickly disengaged. Afterwards, the pilot releases the steel cable 11 , and the hinge limit block 4 can be reset under the elastic recovery action of the first spring 5 , and the hinge limit block 4 can be reinserted into the second through hole and the first through hole.

[0063] The present invention requires protection for a detachable hinge mechanism, which has the following main design advantages:

[0064] (1) The hinge seat is detachable. The hinge seat is connected to the base through a hinge limit block. The hinge limit block is a square structure. In this way, the hinge seat will be fixed and cannot rotate, ensuring that the hinge axis is fixed and the hatch can be used normally.

[0065] (2) High reliability disengagement mechanism. The upper and lower hinge mechanisms are installed in opposite directions. The spring in the steel cable connector pushes the hinge limit block in opposite directions. The two hinge mechanisms are connected by a steel cable. When the steel cable is stressed, it drives the hinge limit block to move. The hinge limit block compresses the spring. When the hinge limit block is disengaged from the hinge seat, the compression spring on the hinge seat will push the hinge seat out. At this time, even if the pilot releases the steel cable, the hinge limit block will not pass through the hole on the hinge seat to fix the hinge seat again. The disengagement mechanism is safe and reliable.

[0066] (3) Single-point unlocking. This mechanism has a single-point unlocking function that is easy to operate. The door can be separated from the fuselage by simply pulling the middle part of the steel cable. No additional operating steps are required, ensuring that the pilot can evacuate quickly in an emergency.

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft quick-release door hinge mechanism, characterized in that: include: A first hinge mechanism and a second hinge mechanism are disposed above and connected to each other, wherein the first hinge mechanism includes a first supporting structure, a first locking structure, and a first fixing structure. The first supporting structure is mounted on the aircraft fuselage, and one side of the first fixing structure is connected to the aircraft door, and the other side is locked to the first supporting structure via the first locking structure. The second hinge mechanism includes a second supporting structure, a second locking structure, and a second fixing structure. The second supporting structure is mounted on the aircraft fuselage. One side of the second fixing structure is connected to the aircraft door, and the other side is locked to the second supporting structure via the second locking structure. The first locking structure and the second locking structure are connected by a connecting mechanism. By pulling the connecting mechanism, the first locking structure and the second locking structure on the upper and lower sides are pulled, and the locking connection between the first supporting structure and the first fixing structure, and the second supporting structure and the second fixing structure is released, thereby realizing the detachment of the hatch; The first hinge mechanism and the second hinge mechanism have the same structure and are symmetrically arranged; The first supporting structure comprises a base (3); The first fixing structure comprises a hinge seat (1); The first locking structure comprises a hinge limit block (4), a first spring (5), a steel cable connector (6) and a second spring (7), wherein the first spring (5) is sleeved on the steel cable connector (6); The base (3) comprises a vertical support plate and a first support plate (33), a second support plate (34) and a third support plate (35) connected to the vertical support plate from top to bottom at intervals, wherein the first support plate (33), the second support plate (34) and the third support plate (35) are respectively provided with a first through hole, a second through hole and a third through hole, and the first through hole, the second through hole and the third through hole are coaxial; The vertical support plate is provided with a first through slot (31) and a second through slot (32), wherein the first through slot (31) is located between the first support plate (33) and the second support plate (34), and the second through slot (32) is located between the second support plate (34) and the third support plate (35); A first protrusion (101) is provided on the middle portion of one side of the main body of the hinge seat (1) close to the base (3), the first protrusion (101) is inserted into the first through slot (31) and passes through it, a fourth through hole (102) is formed on the end of the first protrusion (101) passing through the first through slot (31), and the fourth through hole (102) is coaxial with the first through hole and the second through hole; The body of the steel cable connector (6) and the first spring (5) are both located between the second support plate (34) and the third support plate (35); one end of the steel cable connector (6) is threadedly connected to the hinge limit block (4); the other end passes through the third through hole and is connected to the connecting mechanism; the connecting mechanism is located between the upper and lower bases (3); The hinge stopper (4) comprises a main structure (41) and a protrusion (42) connected to the main structure (41), wherein the protrusion (42) is inserted into the second through slot (32) and can move up and down in the second through slot (32), and one side of the main structure (41) is inserted into the second through hole, the fourth through hole (102) and the first through hole in sequence from bottom to top, and a threaded hole is provided in the middle of the other side for screw connection with one end of the steel cable connector (6); the first spring (5) is in a compressed state, generating a reverse thrust to push the hinge stopper (4); A second protrusion is provided on the main body of the hinge seat (1) on one side close to the base (3), and a second spring (7) is sleeved on the second protrusion. One end of the second spring (7) is connected to the main body of the hinge seat (1) and is compressed between the hinge seat (1) and the fuselage.

2. The aircraft quick-release door hinge mechanism according to claim 1, characterized in that: The base (3) is connected to the aircraft fuselage skin via screws.

3. The aircraft quick-release door hinge mechanism according to claim 2, characterized in that: The hinge seat (1) is connected to the aircraft cabin door via a hinge shaft (2).

4. The aircraft quick-release door hinge mechanism according to claim 1, characterized in that: A limit block (9) is provided below the second through slot (32), and the limit block (9) is connected to the vertical support plate of the base (3) via a first screw (8) and is used to limit the movement of the protrusion (42).

5. The aircraft quick-release door hinge mechanism according to claim 1, characterized in that: The main structure (41) of the hinge limiting block (4) is a square structure, and the first through hole, the second through hole and the fourth through hole (102) are square through holes.

6. The aircraft quick-release door hinge mechanism according to claim 1 or 3, characterized in that: Two coaxial through holes are formed on the main body of the hinge seat (1) on a side away from the base (3); the hinge shaft (2) is connected through the two through holes, and the end of the hinge shaft (2) passing through the through hole is connected to a second cotter pin (16).

7. The aircraft quick-release door hinge mechanism according to claim 1, characterized in that: The connecting mechanism comprises a steel cable (11), and both ends of the steel cable (11) are connected to upper and lower steel cable connectors (6) via second screws (10) respectively.

8. The aircraft quick-release door hinge mechanism according to claim 7, characterized in that: Two pulley groups with the same structure and symmetrical arrangement are provided near the upper and lower steel cable connectors (6), the pulley group comprising a pulley bracket (12), a first cotter pin (13), a pulley shaft (14) and a pulley (15), the pulley bracket (12) being connected to the machine body by screws, the pulley (15) being connected to the pulley bracket (12) by the pulley shaft (14), wherein the pulley bracket (12) has two mounting holes, the pulley (15) is located between the two mounting holes, the pulley shaft (14) passes through the pulley (15) and the two mounting holes, and one end of the pulley shaft (14) passing through the mounting holes is connected to the first cotter pin (13); There is an accommodation space between the pulley (15) and the body of the pulley bracket (12), and the steel cable (11) passes through the accommodation space.

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