An aircraft outswing hatch hook type latch mechanism

Abstract

The application belongs to the technical field of aircraft out-flap door latch mechanism design, and particularly relates to an aircraft out-flap door hook latch mechanism, switching between the locking state and the unlocking state of the aircraft out-flap door hook latch mechanism is realized by manually operating a handle, the aircraft out-flap door hook latch mechanism has simple structure and high reliability, and in the locking state of the aircraft out-flap door hook latch mechanism, a dead point and a hinged point are designed to be on the same straight line and are kept by a mechanical spring retainer, in the unlocking state of the aircraft out-flap door hook latch mechanism, the hinged point is kept by the mechanical spring retainer, the locking state and the unlocking state of the aircraft out-flap door hook latch mechanism can be effectively kept, and the situation of accidental locking and unlocking is avoided, so that the danger is avoided.

Description

A hook-type latch mechanism for an aircraft outward-folding cabin door Technical Field

[0001] This application belongs to the technical field of aircraft outward-folding cabin door latch mechanism design, specifically relating to an aircraft outward-folding cabin door hook-type latch mechanism. Background Technology

[0002] Aircraft outward-opening cabin doors flip up and down, and are usually locked with a latch mechanism after closing.

[0003] There are three main types of latching mechanisms for aircraft outward-opening cabin doors: hook-type latching mechanisms, cam-type latching mechanisms, and pin-type latching mechanisms. Among them, hook-type latching mechanisms are mostly designed with a latch hook hinged to the cabin door and a latch pin installed on the door frame. After the cabin door is closed, a hydraulic actuator drives the latch hook to rotate and hook onto the latch pin to lock the cabin door. This technical solution requires a hydraulic system to be connected through pipelines, which is complex in structure and has low reliability.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0006] The purpose of this application is to provide a hook-type latch mechanism for an outward-folding aircraft cabin door to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] An outward-folding cabin door hook-type latch mechanism for aircraft includes: latch pin 3, latch hook 4, transmission bend arm 6, transmission rocker arm 7, drive shaft 8, drive rocker arm 9, intermediate link 10, intermediate rocker arm 11, intermediate shaft 12, holding rocker arm 13, operating link 14, spring retainer 15, and operating handle 16.

[0009] The latch 3 is connected to the door frame 2;

[0010] There are multiple locking hooks 4, which are hinged to the hatch 1;

[0011] There are multiple transmission bend arms 6, which are hinged to each locking hook 4;

[0012] The drive shaft 8 is connected to the hatch 1;

[0013] There are multiple transmission rocker arms 7, which are sleeved on the drive shaft 8 and hinged to each transmission rocker arm 6.

[0014] The drive rocker arm 9 is sleeved on the drive shaft 8;

[0015] The intermediate connecting rod 10 is hinged to the drive rocker arm 9;

[0016] The intermediate pivot 12 is on the hatch 1;

[0017] The intermediate rocker arm 11 is sleeved on the intermediate rotating shaft 12 and is hinged to the intermediate connecting rod 10;

[0018] The control linkage 14 is hinged to the intermediate rocker arm 11;

[0019] The control handle 16 is hinged to the hatch 1 and to the control linkage 14;

[0020] Keep the rocker arm 13 mounted on the intermediate rotating shaft 12;

[0021] The spring retainer 15 is hinged to the hatch 1 and is hinged to the retaining rocker arm 13;

[0022] By turning the control handle 16, the intermediate rocker arm 11 can be rotated via the control linkage 14, the drive rocker arm 9, the drive shaft 8 and each transmission rocker arm 7 can be rotated via the intermediate linkage 10, each transmission bend arm 6 can be rotated via each locking hook 4, and the spring retainer 15 can be rotated via the holding rocker arm 13, so that the aircraft outward-folding cabin door hook latch mechanism has a locked state and a locked-open state.

[0023] When the hook-type latch mechanism of the aircraft's outward-folding cabin door is in the locked state, each hook 4 rotates and hooks onto the latch pin 3. Each hook 4, transmission bend arm 6, and transmission rocker arm 7 are in the over-center position. The hinge points between the drive rocker arm 9 and the intermediate connecting rod 10, the intermediate connecting rod 10 and the intermediate rocker arm 11, and the intermediate rocker arm 11 and the intermediate rotating shaft 12 are on the same straight line. The spring retainer 15 maintains the tendency of the rocker arm 13 to rotate the drive rotating shaft 8. Through the intermediate connecting rod 10 and the intermediate rocker arm 11, the transmission rocker arm 7, the drive rotating shaft 8, and the drive rocker arm 9 are made to move. Through the transmission bend arm 6, each hook 4 is kept hooked onto the latch pin 3.

[0024] When the hook-type latch mechanism of the aircraft's outward-folding cabin door is in the locked / unlocked state, each latch 4 rotates and disengages from the latch pin 3. The spring retainer 15, through the retaining rocker arm 13, causes the drive shaft 8 to rotate. This rotation is then caused by the intermediate connecting rod 10 and the intermediate rocker arm 11, which in turn causes the drive rocker arm 7, drive shaft 8, and drive rocker arm 9 to move. Finally, through the transmission bent arm 6, each disengaged latch pin 3 is retained.

[0025] According to at least one embodiment of this application, in the above-described aircraft outward-folding cabin door hook-type latch mechanism, the two ends of the latch pin 3 are connected to the door frame 2 via supports;

[0026] Each locking hook 4 is hinged to the hatch 1 via a bolt assembly 5 through a support;

[0027] The two ends of the drive shaft 8 are connected to the hatch 1 via supports;

[0028] The two ends of the intermediate rotating shaft 12 are connected to the hatch 1 via supports;

[0029] The control handle 16 is hinged to the hatch 1 via a bracket;

[0030] The spring retainer 15 is hinged to the hatch 1 via a support.

[0031] According to at least one embodiment of this application, in the above-described aircraft outward-folding cabin door hook-type latch mechanism, each transmission arm 6 and each locking hook 4 are hinged together by a single and double ear structure using pins.

[0032] Each transmission rocker arm 7 and each transmission curved arm 6 are hinged together by pins through a single and double ear structure.

[0033] The intermediate connecting rod 10 and the drive rocker arm 9 are hinged together by a single and double lug structure using pins.

[0034] The intermediate rocker arm 11 and the intermediate connecting rod 10 are hinged together by a single and double lug structure using pins.

[0035] The control link 14 and the intermediate rocker arm 11 are hinged together by a single and double lug structure using pins.

[0036] The spring retainer 15 and the retaining rocker arm 13 are hinged together by a single and double lug structure using pins.

[0037] This application has at least the following beneficial technical effects:

[0038] A hook-type latch mechanism for an aircraft outward-opening cabin door is provided. The switching between the locked and unlocked states is achieved by manually operating a control handle. The mechanism has a simple structure and high reliability. In the locked state, the mechanism is designed to maintain the dead point and hinge point on the same straight line and to use a mechanical spring retainer. In the unlocked state, the mechanism is also designed to maintain the lock and unlocked states of the aircraft outward-opening cabin door hook-type latch mechanism. This effectively maintains the locked and unlocked states of the mechanism, preventing accidental locking or unlocking and avoiding danger. Attached Figure Description

[0039] Figure 1 is a schematic diagram of the hook-type latch mechanism for an aircraft outward-folding cabin door provided in an embodiment of this application;

[0040] Figure 2 is a schematic diagram of the aircraft outward-folding cabin door hook-type latch mechanism in the locked state provided in the embodiment of this application;

[0041] Figure 3 is a partial schematic diagram of Figure 2;

[0042] Figure 4 is a schematic diagram of the hook-type latch mechanism of the aircraft outward-folding cabin door provided in the embodiment of this application in the locked-open state;

[0043] in:

[0044] 1-Hatch door; 2-Door frame; 3-Latch pin; 4-Lock hook; 5-Bolt assembly; 6-Drive arm; 7-Drive rocker arm; 8-Drive shaft; 9-Drive rocker arm; 10-Intermediate link; 11-Intermediate rocker arm; 12-Intermediate shaft; 13-Retaining rocker arm; 14-Control link; 15-Spring retainer; 16-Control handle.

[0045] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0046] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0047] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0048] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral 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; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0049] The present application will now be described in further detail with reference to Figures 1 to 4.

[0050] An outward-folding cabin door hook-type latch mechanism for aircraft includes: latch pin, latch hook, bolt assembly, transmission bend arm, transmission rocker arm, drive shaft, drive rocker arm, intermediate link, intermediate rocker arm, intermediate shaft, retaining rocker arm, control link, spring retainer, and control handle, as shown in Figure 1.

[0051] The latch pins are connected to the door frame at both ends by supports.

[0052] There are multiple locking hooks, which are hinged to the hatch via bolt assemblies using supports.

[0053] The transmission arm has multiple bends, which are hinged to each locking hook using pins through a single and double ear structure.

[0054] The two ends of the drive shaft are connected to the hatch via supports.

[0055] The transmission rocker arm has multiple components, which are connected to the drive shaft by sleeves, and are hinged to each transmission rocker arm by single and double lugs using pins.

[0056] The drive rocker arm is sleeved onto the drive shaft.

[0057] The intermediate connecting rod and the drive rocker arm are hinged by a single and double lug structure using pins.

[0058] The two ends of the central pivot are connected to the hatch via supports.

[0059] The intermediate rocker arm is fitted onto the intermediate rotating shaft through a through hole, and is hinged to the intermediate connecting rod using a pin through a single or double lug structure.

[0060] The control linkage and the central rocker arm are hinged using pins through a single and double lug structure.

[0061] The control handle is hinged to the hatch via a bracket, and is hinged to the control linkage via a single or double lug structure using pins.

[0062] Keep the rocker arm fitted onto the intermediate rotating shaft through the through hole.

[0063] The spring retainer is hinged to the hatch via a support and is hinged to the retaining rocker arm via a single or double lug structure using pins.

[0064] In the aircraft outward-folding cabin door hook-type latch mechanism disclosed in the above embodiments, the intermediate rocker arm can be rotated by turning the control handle via the control linkage, and the drive rocker arm, drive shaft and each transmission rocker arm can be rotated via the intermediate linkage, and each lock hook can be rotated via each transmission bend arm, and the spring retainer can be rotated via the holding rocker arm, so that the aircraft outward-folding cabin door hook-type latch mechanism has a locked state and a locked-open state.

[0065] When the hook-type latch mechanism of the aircraft's outward-opening cabin door is in the locked state, each hook rotates clockwise and hooks onto the latch pin. Each hook, transmission arm, and transmission rocker arm is in the center position, as shown in Figure 3. When the hook is subjected to an unlocking load that causes it to rotate counterclockwise, the transmission arm will cause the transmission rocker arm, drive shaft, and drive rocker arm to tend to move clockwise. The hinge points between the drive rocker arm and the intermediate connecting rod, the intermediate connecting rod and the intermediate rocker arm, and the intermediate rocker arm and the intermediate shaft are designed to be on the same straight line. The spring retainer is designed to retain the tendency of the drive shaft to rotate clockwise via the rocker arm. The intermediate connecting rod and the intermediate rocker arm can effectively prevent the clockwise movement tendency of the transmission rocker arm, drive shaft, and drive rocker arm. In this way, the cabin door 1 can be effectively locked in the closed state, as shown in Figure 2.

[0066] When the hook-type latch mechanism of the aircraft's outward-opening cabin door is in the locked / unlocked state, each hook rotates counterclockwise and disengages from the latch pin, allowing the cabin door 1 to open. The spring retainer is designed to generate a counterclockwise rotation tendency of the drive shaft via the retaining rocker arm. This tendency can then be generated clockwise via the intermediate connecting rod and intermediate rocker arm, which in turn generates a clockwise movement tendency of the transmission rocker arm, drive shaft, and drive rocker arm. The transmission bend arm keeps each hook in a counterclockwise rotation tendency, preventing accidental reset of each hook and avoiding interference with the opening and closing of the cabin door 1.

[0067] The aircraft outward-opening cabin door hook-type latch mechanism disclosed in the above embodiments switches between the locked and unlocked states by manually operating a control handle. It has a simple structure and high reliability. Furthermore, the locked state of the aircraft outward-opening cabin door hook-type latch mechanism is designed with the dead point and hinge point on the same straight line and is maintained by a mechanical spring retainer. The unlocked state of the aircraft outward-opening cabin door hook-type latch mechanism is also maintained by a mechanical spring retainer. This effectively maintains the locked and unlocked states of the aircraft outward-opening cabin door hook-type latch mechanism, preventing accidental locking or unlocking and avoiding danger.

[0068] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0069] The technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principles of this 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 all fall within the scope of protection of this application.

Claims

1. A hook-type latch mechanism for an outward-folding aircraft cabin door, characterized in that, include: Latch pin (3), latch hook (4), transmission bend arm (6), transmission rocker arm (7), drive shaft (8), drive rocker arm (9), intermediate link (10), intermediate rocker arm (11), intermediate shaft (12), retaining rocker arm (13), operating link (14), spring retainer (15), operating handle (16); Latch pin (3) is connected to the door frame (2); There are multiple latch hooks (4), which are hinged to the hatch (1); There are multiple transmission bend arms (6), which are hinged to each latch hook (4); The drive shaft (8) is connected to the hatch (1); There are multiple transmission rocker arms (7), which are sleeved on the drive shaft (8) and hinged to each transmission bend arm (6); The drive rocker arm (9) is sleeved on the drive shaft (8); The intermediate link (10), intermediate rocker arm (11), intermediate shaft (12), retaining rocker arm (13), operating link (14), spring retainer (15), operating handle (16); The rod (10) is hinged to the drive rocker arm (9); the intermediate shaft (12) is on the hatch (1); the intermediate rocker arm (11) is sleeved on the intermediate shaft (12) and hinged to the intermediate connecting rod (10); the operating connecting rod (14) is hinged to the intermediate rocker arm (11); the operating handle (16) is hinged to the hatch (1) and hinged to the operating connecting rod (14); the retaining rocker arm (13) is sleeved on the intermediate shaft (12); the spring retainer (15) is hinged to the hatch (1) and hinged to the retaining rocker arm (13); by turning the operating handle (16), the intermediate rocker arm (11) can be rotated via the operating connecting rod (14), and the drive rocker arm (9), drive shaft (8), and each transmission rocker arm (7) can be rotated via the intermediate connecting rod (10). The movement drives each locking hook (4) to rotate via each transmission arm (6), and drives the spring retainer (15) to rotate via the holding rocker arm (13), thus enabling the aircraft outward-folding door hook-type latch mechanism to have a locked state and a locked-open state; when the aircraft outward-folding door hook-type latch mechanism is in the locked state, each locking hook (4) rotates and hooks onto the latch pin (3), each locking hook (4), transmission arm (6), and transmission rocker arm (7) are in the center position, the hinge point between the driving rocker arm (9) and the intermediate connecting rod (10), the hinge point between the intermediate connecting rod (10) and the intermediate rocker arm (11), and the hinge point between the intermediate rocker arm (11) and the intermediate rotating shaft (12) are on the same straight line, and the spring retainer (15) drives the spring retainer (15) via the holding rocker arm (13) to rotate via the holding rocker arm (14). 3) The drive shaft (8) has a tendency to rotate, which causes the transmission rocker arm (7), drive shaft (8), and drive rocker arm (9) to move via the intermediate connecting rod (10) and intermediate rocker arm (11). The transmission bend arm (6) keeps each hook (4) hooked on the latch pin (3). When the aircraft outward-folding cabin door hook latch mechanism is in the locked-open state, each hook (4) rotates and disengages from the latch pin (3). The spring retainer (15) causes the drive shaft (8) to rotate via the holding rocker arm (13), which causes the transmission rocker arm (7), drive shaft (8), and drive rocker arm (9) to move via the intermediate connecting rod (10) and intermediate rocker arm (11). The transmission bend arm (6) keeps each hook disengaged from the latch pin (3).

2. The aircraft outward-folding cabin door hook-type latch mechanism according to claim 1, characterized in that, The latch (3) is connected to the door frame (2) at both ends by supports; each lock hook (4) is hinged to the hatch (1) by bolt assembly (5) via supports; the drive shaft (8) is connected to the hatch (1) at both ends by supports; the intermediate shaft (12) is connected to the hatch (1) at both ends by supports; the operating handle (16) is hinged to the hatch (1) via bracket; the spring retainer (15) is hinged to the hatch (1) via supports.

3. The aircraft outward-folding cabin door hook-type latch mechanism according to claim 1, characterized in that, Each transmission arm (6) and each locking hook (4) are hinged together by a single or double ear structure using pins; each transmission rocker arm (7) and each transmission arm (6) are hinged together by a single or double ear structure using pins; the intermediate connecting rod (10) and the drive rocker arm (9) are hinged together by a single or double ear structure using pins; the intermediate rocker arm (11) and the intermediate connecting rod (10) are hinged together by a single or double ear structure using pins; the operating connecting rod (14) and the intermediate rocker arm (11) are hinged together by a single or double ear structure using pins; the spring retainer (15) and the retaining rocker arm (13) are hinged together by a single or double ear structure using pins.

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