An eVTOL aircraft door lock

Abstract

The utility model relates to an unmanned plane technical field especially relates to a kind of eVTOL aircraft cabin door lock, including lock body, latch assembly, lock seat and transition joint;The lock body includes a control box and two lock bolt assemblies;The latch assembly and lock seat are provided with two, wherein one lock bolt assembly is fixed on cabin door structure by one lock seat, and another lock bolt assembly is fixed on cabin door structure by another lock seat and transition joint;Two latch assemblies are fixed on machine body structure, and the cooperation of two lock bolt assemblies and two latch assemblies is controlled by control box, the opening and locking of cabin door are completed, when cabin door is locked, two lock bolt assemblies form the effect of two fulcrums to cabin door, so that cabin door stiffness is higher, more difficult to deform, and locking effect is good;The utility model has the advantages of high stiffness, high safety, fast control response and long service life.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to an eVTOL aircraft cabin door lock. Background Technology

[0002] eVTOL (Electric Vertical Takeoff and Landing) aircraft can take off and land vertically, eliminating the need for long runways and enabling takeoff and landing operations within limited spaces. This greatly improves the flexibility and accessibility of air transport, making them suitable for scenarios such as urban air traffic. Powered by electricity, they do not produce pollutants such as carbon dioxide and nitrogen oxides during operation, meeting the zero-carbon vision and environmental protection requirements. At the same time, they can significantly reduce noise, improve the passenger experience and comfort. The overall configuration can be designed with a variety of innovative aerodynamic-propulsion integrated designs and unconventional aerodynamic layouts, including multi-rotor, compound, and vector propulsion types, to meet different travel needs. Their structure is relatively simple, maintenance requirements are low, and electricity costs are usually lower than fuel costs. After large-scale commercial operation, they are expected to achieve lower operating costs.

[0003] eVTOL aircraft employ multiple lift systems during takeoff and landing, resulting in significant vibrations. When these vibrations are transmitted to the cabin door structure, which is an openable structure, a poorly locked door can easily cause it to open, exposing the occupants to the air and potentially causing panic or even injury. Therefore, the cabin door lock design must possess excellent locking characteristics and vibration resistance, while also ensuring smooth opening of the door.

[0004] Chinese utility model patent application number 202423152694.9 discloses a hatch structure for an eVTOL aircraft and an eVTOL aircraft, including: a hatch body; a hatch lock installed below the hatch body, the hatch lock including a lock body and a lock seat that are locked together, the lock seat being embedded inside the fuselage; the lock body being fixedly connected to the hatch body; the lock body being connected to a handle on the hatch body via a push-pull line; a hinge assembly fixed to the upper edge of the hatch body, the hinge assembly including a hinge pre-embedded part, a hinge seat, and a hinge; the hinge pre-embedded part being fixed inside the hatch body; two hinge seats being fixed at corresponding positions on the fuselage; the hinge being rotatably connected between the two hinge seats; and the hinge being connected to the hinge pre-embedded part by bolts; a retractable strut structure installed on the side of the hatch body, the strut structure connecting the hatch body and the fuselage at both ends. The designed hatch structure allows the hatch to be locked to the fuselage when closed, effectively reducing the gap of the double-leaf door, and has a simple configuration and low airtightness requirements.

[0005] The Chinese utility model patent application number 202423152694.9 describes a cabin door structure for an eVTOL aircraft and an eVTOL aircraft. The door handle is far from the lock body, and the pull cable needs to be arranged according to a curve, resulting in weak control over the lock. Especially in the high-vibration environment of eVTOL aircraft, the lock is easily vibrated open during flight, causing the cabin door to open in the air and affecting the safety of the occupants. Utility Model Content

[0006] The purpose of this invention is to overcome the shortcomings of the existing technology and provide an eVTOL aircraft cabin door lock with the advantages of high rigidity, high security, fast control response and long service life.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0008] An eVTOL aircraft cabin door lock includes a lock body, a latch assembly, a lock seat, and a transition joint;

[0009] The lock body includes a control box and two bolt assemblies;

[0010] There are two latch assemblies and two lock seats. One latch assembly is fixed to the door structure by one lock seat, and the other latch assembly is fixed to the door structure by another lock seat and a transition joint.

[0011] Both latch assemblies are fixed to the fuselage structure. The two latch assemblies are controlled by the control box to cooperate with the two bolt assemblies to open and close the hatch. When the hatch is locked, the two bolt assemblies form two fulcrums for the hatch, making the hatch more rigid, less prone to deformation, and with a better locking effect.

[0012] Preferably, the control box includes a handle assembly and a cable assembly. The handle assembly is fixed to the hatch and includes an outer handle, an inner handle, a corner box, and a planetary gear fixing plate. The corner box is provided with multiple connecting edges for connecting to the hatch, ensuring the strength and rigidity of the connection between the corner box and the hatch. The planetary gear fixing plate is connected to the corner box. The outer handle and the inner handle are respectively located outside and inside the hatch. The cable assembly is controlled by pulling the inner handle or the outer handle. The outer handle and the inner handle are respectively provided with an outer locking plate and an inner locking plate.

[0013] Furthermore, the pull cable assembly includes a shaft, a torsion spring, an outer handle lever, an inner handle lever, planetary gears, and a pull cable. The shaft is rotatably mounted inside the corner box. Two torsion springs are provided, each sleeved on the shaft. One end of each torsion spring is connected to the inner locking platform of the inner handle and the outer locking platform of the outer handle, respectively. The outer and inner handle levers are fixed to the shaft by fasteners and are respectively engaged with the outer and inner handles. The inner handle lever has a protrusion that mates with the planetary gears. The middle part of the planetary gears is rotatably mounted on a planetary gear fixing plate via a rotating shaft. One end of the pull cable is fixed to the planetary gears.

[0014] Furthermore, the planetary gear is X-shaped, with the pull cable attached at the diagonal ends and connected to the protrusion of the inner handle lever in the middle of the X. This allows the protrusion to move the planetary gear. When moving in a certain direction, the pull cable can be simultaneously tightened and extended, maintaining synchronous control of the pull cable on the latch assembly and achieving unlocking and locking functions.

[0015] Furthermore, the latch assembly includes a base plate, a cover plate, a crank, a latch, a first fixed shaft, a second fixed shaft, and screws. The base plate and the cover plate are connected together by screws to form a box-like structure. The base plate is mounted on the support crank and the latch respectively through the two first fixed shafts, and the support crank and the latch are rotatably mounted on the two first fixed shafts respectively. The support crank has a shaft hole that matches the second fixed shaft, and the second fixed shaft is fixedly mounted on the support crank through the shaft hole. The support crank is connected to the other end of the pull cable, and the front end of the latch has a fork-shaped structure.

[0016] Furthermore, both ends of the pull cable are provided with connection points, and the two ends of the pull cable are connected to the planetary gear and the crank respectively by fasteners. The pull cable is a steel wire structure, which still has a certain rigidity when pushed, and resists the crank.

[0017] Furthermore, the latch assembly includes a latch, a latch fixing plate, and a nut. The latch fixing plate is fixed to the machine body structure. The latch has a U-shaped structure, and the end of the latch is provided with threads and a boss. The boss serves as a limit. The latch passes through the holes in the latch fixing plate and the machine body structure. It is fixed at the rear of the machine body structure by the nut engaging with the threads on the latch to ensure a secure connection of the latch.

[0018] Furthermore, the lock seat is provided with an adjustment hole, a fixing hole, a latch clearance area, and a cable clearance area. The adjustment hole is used to install the lock seat onto the hatch, and the adjustment hole is oblong. The fixing hole is threaded, and the bolt assembly is installed into the fixing hole by a threaded fastener. The cable clearance area is used to prevent the cable from being blocked by the lock seat when it moves. The latch clearance area is used to provide a channel for the latch and the bolt to cooperate, so as to meet the movement requirements.

[0019] Furthermore, an outer limiting platform for limiting the outward handle is fixedly installed inside the corner box, and an inner limiting platform for limiting the inward handle is fixedly installed on the outer side of the corner box. A shaft hole for installing a shaft is opened on the corner box, and the shaft is rotatably installed inside the corner box through the shaft hole.

[0020] The beneficial effects of this utility model are:

[0021] The control box of this utility model is made of metal parts, has a large size, and the parts are three-dimensional, resulting in high structural rigidity.

[0022] The torsion spring tightly twists the outer and inner handles into place, preventing the crank from being pulled open. This ensures that the latch and bolt engage tightly, making it difficult to disengage in the high-vibration environment of eVTOL. Furthermore, the design incorporates two bolt assemblies and latch assemblies, so that even if one disengages, the other still retains its locking function. This design gives the invention a high level of security.

[0023] The short distance between the control box and the latch assembly prevents the soft pull cable from deforming due to excessive travel. When the handle is pulled, the latch assembly can be controlled better, thus giving this invention the advantage of fast control response.

[0024] All moving parts are made of steel, which is hard, strong, and wear-resistant, meeting the requirements for long-term use, thus giving this utility model the advantage of a long service life. Attached Figure Description

[0025] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 This is an isometric view of an eVTOL aircraft cabin door lock installed on a cabin door according to this utility model;

[0027] Figure 2 This is an isometric view of an eVTOL aircraft cabin door lock according to this utility model;

[0028] Figure 3 This is an exploded view of an eVTOL aircraft cabin door lock according to this utility model;

[0029] Figure 4 This is an isometric view of the lock base of this utility model;

[0030] Figure 5This is an exploded view of the latch assembly of this utility model;

[0031] Figure 6 This is an exploded view of the locking tongue assembly of this utility model;

[0032] Figure 7 This is an exploded view of the control box of this utility model;

[0033] Figure 8 This is an isometric view of the draw wire assembly of this utility model;

[0034] Figure 9 This is an isometric view of the cable assembly and shaft connection part of this utility model;

[0035] Figure 10 This is an isometric view of the planetary gears and the pull wire of the pull wire assembly of this utility model;

[0036] Figure 11 This is an isometric view of the connection between the latch and the bolt of this utility model.

[0037] Figure 12 This is an exploded view of the handle assembly of this utility model;

[0038] Figure 13 This is an isometric drawing of the inner handle of this utility model;

[0039] Figure 14 This is an isometric drawing of the external handle of this utility model;

[0040] Figure 15 This is an isometric view of the corner box of this utility model.

[0041] Explanation of markings in the diagram: 11. Lock body; 111. Control box; 1111. Handle assembly; 11111. Outer handle; 111111. Outer locking platform; 11112. Inner handle; 111121. Inner locking platform; 11113. Corner box; 111131. Outer limit platform; 111132. Shaft hole; 111133. Inner limit platform; 11114. Planetary gear fixing plate; 1112. Pull cable assembly; 11121. Shaft; 11122. Torsion spring; 11123. Outer handle lever; 11124. Inner handle 1. Alarm; 11125. Planetary gear; 11126. Pull cable; 112. Lock tongue assembly; 1121. Base plate; 1122. Cover plate; 1123. Crank; 1124. Lock tongue; 1125. Fixed shaft one; 1126. Fixed shaft two; 1127. Screw; 12. Latch assembly; 121. Latch; 122. Latch fixing plate; 123. Nut; 13. Lock seat; 131. Adjusting hole; 132. Fixing hole; 133. Latch clearance area; 134. Pull cable clearance area; 14. Transition joint; 2. Hatch door. Detailed Implementation

[0042] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0043] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0044] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0045] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0046] Example 1

[0047] like Figure 1 As shown, the eVTOL aircraft cabin door lock of this utility model is installed on one side of the cabin door 2, and a hinge is installed on the other side. The cabin door lock completes the locking and unlocking of the cabin door 2, realizing the function of locking and opening the cabin door 2 for passengers to enter and exit. After the cabin door lock closes the cabin door 2, the cabin door 2 has good rigidity and vibration resistance, preventing the cabin door 2 from being accidentally opened during flight.

[0048] like Figure 2 and 3 As shown, the eVTOL aircraft door lock of this utility model includes a lock body 11, a latch assembly 12, a lock seat 13 and a transition joint 14. In this example, a single lock body 11 cooperates with two latch assemblies 12 to lock the door 2.

[0049] The lock body 11 includes a control box 111 and two bolt assemblies 112;

[0050] There are two latch assemblies 12 and two lock seats 13. One latch assembly 112 is fixed to the hatch 2 structure through one lock seat 13, and the other latch assembly 112 is fixed to the hatch 2 structure through the other lock seat 13 and the transition joint 14. Specifically, due to the shape change of the hatch 2, the other lock seat 13 cannot be directly connected to the hatch 2. Therefore, the transition joint 14 is designed to connect the other lock seat 13 to the hatch 2, ensuring that the two latch assemblies 112 have the same structural form. The transition joint 14 is a machined aluminum alloy part, preferably made of 7050, and preferably heat treated in T7451 condition. The transition joint 14 is connected to the hatch 2 at one end by a fastener and to the other lock seat 13 at the other end.

[0051] Both latch assemblies 12 are fixed to the fuselage structure. The control box 111 controls the cooperation between the two latch assemblies 112 and the two bolt assemblies 12 (by separating and locking the bolt assemblies 112 and the bolt assemblies 112) to complete the opening and closing of the hatch 2. When the hatch is locked, the two bolt assemblies 112 form two fulcrums for the hatch 2, making the hatch 2 more rigid, less prone to deformation, and with a better locking effect.

[0052] like Figure 7 As shown, the control box 111 includes a handle assembly 1111 and a cable assembly 1112. The handle assembly 1111 is fixed to the hatch. The handle assembly 1111 includes an outer handle 11111, an inner handle 11112, a corner box 11113, and a planetary gear fixing plate 11114.

[0053] The outer handle 11111 and the inner handle 11112 are ergonomically designed to fit the hand comfortably. They can be machined as a single piece or assembled from multiple parts. In this example, to reduce processing costs, multiple aluminum alloy parts are connected together using countersunk fasteners.

[0054] The corner box 11113 is provided with multiple connecting edges for connecting with the hatch 2, ensuring the strength and rigidity of the connection between the corner box 11113 and the hatch 2; specifically: the corner box 11113 is composed of multiple parts spliced ​​together and connected to the hatch 2. The corner box 11113 is made of aluminum alloy, preferably 7050, and the preferred heat treatment state is T7351. After splicing, the corner box 11113 extends multiple connecting edges to connect with the hatch 2, ensuring the strength and rigidity of the connection;

[0055] The planetary gear fixing plate 11114 is connected to the corner box 11113. Specifically, the planetary gear 11125 is fixed on the outer side of the planetary gear fixing plate 11114, and the inner side of the planetary gear fixing plate 11114 is connected to the corner box 11113. The planetary gear fixing plate 11114 is made of machined aluminum alloy, preferably 7050, and preferably T7351 heat treatment state.

[0056] The outer handle 11111 is fixed to the shaft 11121 inside the corner box 11113, and the inner handle 11112 is fixed to the shaft 11121 on the outside of the corner box 11113. This way, when one handle is turned, it will not affect the other handle. A protrusion is designed at the position where the corner box 11113 connects to the planetary gear shaft. This protrusion is the inner limiting platform 111133, which limits the inner handle 11112.

[0057] The outer handle 11111 and the inner handle 11112 are respectively located on the outside and inside of the hatch. By pulling the inner handle 11112 or the outer handle 11111, the cable assembly 1112 is controlled, causing the cable 11126 to rotate along the shaft 11121. In turn, the cable 11126 pulls the crank 1123 inside the latch assembly 112 to complete the engagement of the latch 1124 with the bolt 121, thereby realizing the functions of unlocking and locking.

[0058] The outer handle 11111 and the inner handle 11112 are respectively provided with an outer locking platform 111111 and an inner locking platform 111121. The outer locking platform 111111 and the outer handle 11111 are integrally formed, and the inner locking platform 111121 and the inner handle 11112 are integrally formed.

[0059] like Figure 8 , Figure 9 and Figure 10 As shown, the pull cable assembly 1112 includes a shaft 11121, a torsion spring 11122, an outer pull handle 11123, an inner pull handle 11124, a planetary gear 11125, and a pull cable 11126. The pull cable assembly 1112 controls the synchronous movement of the two pull cables 11126. The shaft 11121 is the axis of rotation. The shaft 11121 is rotatably mounted inside the corner box 11113. The shaft 11121 is made of aluminum alloy, preferably 7050, and the preferred heat treatment state is T7451.

[0060] Two torsion springs 11122 are provided, and the two torsion springs 11122 are sleeved on the shaft 11121. One end of the two torsion springs 11122 is connected to the inner retaining plate 111121 of the inner handle 11112 and the outer retaining plate 111111 of the outer handle 11111, respectively. The other end of the two torsion springs 11122 is locked onto the corner box 11113. When installing the torsion springs 11122, a preload is applied to the torsion springs 11122 to keep them under constant tension. When the outer handle 11111 or the inner handle 11112 is pulled under stress, the cable 11126 pulls the crank 1123 to disengage the latch 1124, thus unlocking the device. After the outer handle 11111 or the inner handle 11112 is released, the torsion spring 11122 twists and tightens the outer handle 11111 and the inner handle 11112, thereby pushing the cable 11126 to its furthest position, causing the crank 1123 to press against the latch 1124.

[0061] The outer handle lever 11123 and the inner handle lever 11124 are fixed to the shaft 11121 by fasteners. The outer handle lever 11123 and the inner handle lever 11124 are respectively engaged with the outer handle 11111 and the inner handle 11112. The inner handle lever 11124 is provided with a protrusion that cooperates with the planetary gear 11125. Whether the outer handle 11111 or the inner handle 11112 is pulled, the shaft 11121 can be driven to rotate, which in turn drives the shaft of the inner handle lever 11124 to rotate the planetary gear 11125.

[0062] Both the outer handle dial 11123 and the inner handle dial 11124 are made of steel, with 15-5PH being the preferred material and H900 being the preferred heat treatment state.

[0063] The planetary gear 11125 is rotatably mounted on the planetary gear fixing plate 11114 via a rotating shaft. One end of the pull wire 11126 is fixed on the planetary gear 11125. The planetary gear 11125 is made of steel, preferably 15-5PH, and preferably has a heat treatment state of H900.

[0064] The planetary gear 11125 is X-shaped, with pull cables 11126 attached to opposite ends. It connects to a protrusion on the inner handle lever 11124 in the middle of the X, allowing the protrusion to move the planetary gear 11125. When moving in a certain direction, the pull cables 11126 can be simultaneously tightened and extended, maintaining synchronous control of the pull cables 11126 on both sides of the planetary gear 11125 on the two locking tongue assemblies 112, thus achieving unlocking and locking functions.

[0065] like Figure 6As shown, the latch assembly 112 includes a base plate 1121, a cover plate 1122, a crank 1123, a latch 1124, a first fixing shaft 1125, a second fixing shaft 1126, and screws 1127. The base plate 1121 and the cover plate 1122 are connected together by screws 1127 to form a box-like structure. The base plate 1121 is mounted with the crank 1123 and the latch 1124 respectively by the two first fixing shafts 1125. Furthermore, the support crank 1123 and the locking tongue 1124 are rotatably mounted on two fixed shafts 1125 respectively. The support crank 1123 has a shaft hole 2 that is adapted to the fixed shaft 1126. The fixed shaft 1126 is fixedly mounted on the support crank 1123 through the shaft hole 2. The support crank 1123 is connected to the other end of the pull cable 11126. When the pull cable 11126 moves, it can pull the crank 1123 to rotate around the fixed shaft 1125.

[0066] Specifically, a bushing is designed at the position where the bolts on the fixed shaft 1125 mate with the crank 1123 and the locking tongue 1124, so that the crank 1123 and the locking tongue 1124 can rotate around the fixed shaft 1125.

[0067] Both the base plate 1121 and the cover plate 1122 are machined aluminum alloy parts, preferably made of 7050, and preferably heat treated in T7451. Both the base plate 1121 and the cover plate 1122 have holes for connecting to the first fixed shaft 1125 and the second fixed shaft 1126. As machined parts, they have high positional accuracy and hole diameter accuracy, which meets the high-precision fit requirements of the lock tongue 1124.

[0068] Based on the motion simulation trajectory, the locking tongue 1124 and crank 1123 are designed with a rotation axis, which is the center line of fixed shaft one 1125 and fixed shaft two 1126. The front end of the locking tongue 1124 has a fork-shaped structure to cooperate with the latch 121. Both the locking tongue 1124 and the crank 1123 are made of steel, preferably 15-5PH, and the preferred heat treatment state is H900. They have the characteristics of wear resistance, corrosion resistance and high strength, which meet the life requirements of the motion friction of the locking tongue 1124 and the crank 1123.

[0069] Both ends of the pull cable 11126 are provided with connection points. The two ends of the pull cable 11126 are connected to the planetary gear 11125 and the crank 1123 respectively by fasteners. The pull cable 11126 is a steel wire structure, which still has a certain rigidity when pushed, and resists the crank 1123.

[0070] like Figure 5As shown, the latch assembly 12 includes a latch 121, a latch fixing plate 122, and a nut 123. The latch fixing plate 122 is fixed to the machine body structure. The latch 121 has a U-shaped structure. The end of the latch 121 is provided with threads and a boss. The boss plays a limiting role. The latch 121 passes through the holes in the latch fixing plate 122 and the machine body structure. At the rear of the machine body structure, the nut 123 is used to fix the latch 121 by engaging with the threads on the latch 121, ensuring that the connection of the latch 121 is reliable.

[0071] The latch fixing plate 122 is a machined aluminum alloy part, preferably made of 7050 material and preferably heat treated with T7351 heat treatment state;

[0072] The latch 121 is made of steel and has high wear resistance when it is used with the latch tongue 1124. The preferred material is 15-5PH stainless steel and the preferred heat treatment state is H900. In order to ensure the locking effect, the diameter of the latch 121 should not be too small. In this example, the diameter is 8mm.

[0073] The lock seat 13 is provided with an adjustment hole 131, a fixing hole 132, a latch clearance area 133, and a pull cable clearance area 134. The adjustment hole 131 is used to install the lock seat 13 onto the hatch. The adjustment hole 131 is oblong. The fixing hole 132 is provided with threads. The bolt assembly 112 is installed into the fixing hole 132 by using threaded fasteners. The pull cable clearance area 134 is used to prevent the pull cable 11126 from being blocked by the lock seat 13 when it moves. The latch clearance area 133 is used to provide a channel for the bolt 121 and the bolt 1124 to cooperate and meet the movement requirements.

[0074] An outer limiting platform 111131 is fixedly installed inside the corner box 11113 to limit the outer handle 11111. An inner limiting platform 111133 is fixedly installed on the outer side of the corner box 11113 to limit the inner handle 11112. A shaft hole 111132 for mounting the shaft 11121 is provided on the corner box 11113. The shaft 11121 is rotatably mounted inside the corner box 11113 through the shaft hole 111132. When the handle is released, the torsion spring 11122 twists the handle to reset. When the outer handle 11111 and the inner handle 11112 contact the outer limiting platform 111131 and the inner limiting platform 111133 respectively, the movement stops, keeping the surface of the outer handle 11111 flush with the outer surface of the aircraft and the surface of the inner handle 11112 flush with the interior surface. While being aesthetically pleasing, the outer handle 11111 does not affect the aerodynamic performance of the aircraft.

[0075] like Figure 11As shown, the locking method of the latch 1124 and the bolt 121 is as follows: when the outer handle 11111 or the inner handle 11112 is not pulled, the pull cable 11126 will not be tightened. The pull cable 11126 is made of steel wire and has great rigidity. In this way, the pull cable 11126 keeps the crank 1123 in this position. At this time, the crank 1123 is held in this position by the pull cable 11126. The crank 1123 presses against the latch 1124, causing the latch 1124 to lock the bolt 121, thus completing the locking.

[0076] The unlocking method of the latch 1124 and the bolt 121 is as follows: When the outer handle 11111 or the inner handle 11112 is pulled, the pull cable 11126 pulls the crank 1123 to rotate around the fixed shaft 1125. At this time, the fixed shaft 1126 moves along the arc groove of the base plate 1121, causing the contact part between the crank 1123 and the latch 1124 to move down. The latch 1124 is not obstructed. When the door is opened, the bolt 121 moves and causes the latch 1124 to rotate, aligning the opening with the direction of movement. The bolt 121 slides out from the opening of the latch 1124, completing the unlocking.

[0077] The fasteners mentioned in this embodiment include, but are not limited to, screws and bolts.

[0078] In summary, the control box 111 of this utility model is made of metal parts, has a large size, and the parts are three-dimensional, resulting in high structural rigidity.

[0079] The torsion spring 11122 tightly twists the outer handle 11111 and the inner handle 11112 into place, preventing the crank 1123 from being pulled open. This allows the latch 121 and the locking tongue 1124 to engage tightly, making it difficult to disengage in the high-vibration environment of eVTOL. At the same time, two locking tongue assemblies 112 and two latch assemblies 12 are designed so that when one disengages, the other still has a locking function, thus giving this utility model the advantage of high safety.

[0080] The distance between the control box 111 and the latch assembly 112 is relatively short, which prevents the soft pull cable from deforming due to excessive travel. When the handle is pulled, the latch assembly 112 can be controlled better, thus giving this utility model the advantage of fast control response.

[0081] All moving parts are made of steel, which is hard, strong, and wear-resistant, meeting the requirements for long-term use, thus giving this utility model the advantage of a long service life.

[0082] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should all be covered within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. An eVTOL aircraft cabin door lock, characterized in that, It includes a lock body (11), a latch assembly (12), a lock seat (13), and a transition joint (14); The lock body (11) includes a control box (111) and two latch assemblies (112); Both the latch assembly (12) and the lock seat (13) are provided in twos. One of the latch assemblies (112) is fixed to the hatch (2) structure through one of the lock seats (13), and the other latch assembly (112) is fixed to the hatch (2) structure through the other lock seat (13) and the transition joint (14). Both latch assemblies (12) are fixed to the body structure. The two latch assemblies (112) are controlled by the control box (111) to cooperate with the two bolt assemblies (12) to complete the opening and closing of the hatch. When the hatch is locked, the two latch assemblies (112) form two fulcrums for the hatch, making the hatch more rigid, less prone to deformation, and with a good locking effect.

2. The eVTOL aircraft cabin door lock of claim 1, wherein, The control box (111) includes a handle assembly (1111) and a cable assembly (1112). The handle assembly (1111) is fixed to the hatch. The handle assembly (1111) includes an outer handle (11111), an inner handle (11112), a corner box (11113), and a planetary gear fixing plate (11114). The corner box (11113) is provided with multiple connecting edges for connecting with the hatch, ensuring the strength and rigidity of the connection between the corner box (11113) and the hatch. The planetary gear fixing plate (11114) is connected to the corner box (11113). The outer handle (11111) and the inner handle (11112) are respectively located on the outside and inside of the hatch. The cable assembly (1112) is controlled by pulling the inner handle (11112) or the outer handle (11111). The outer handle (11111) and the inner handle (11112) are respectively provided with an outer locking platform (111111) and an inner locking platform (111121).

3. The eVTOL aircraft cabin door lock according to claim 2, characterized in that, The pull cable assembly (1112) includes a shaft (11121), a torsion spring (11122), an outer handle lever (11123), an inner handle lever (11124), a planetary gear (11125), and a pull cable (11126). The shaft (11121) is rotatably mounted inside the corner box (11113). Two torsion springs (11122) are provided, and the two torsion springs (11122) are sleeved on the shaft (11121). One end of the two torsion springs (11122) is respectively connected to the inner retaining plate (111121) of the inner handle (11112) and the outer retaining plate of the outer handle (11111). On (111111), the outer handle lever (11123) and the inner handle lever (11124) are fixed to the shaft (11121) by fasteners, and the outer handle lever (11123) and the inner handle lever (11124) are respectively snapped into the outer handle (11111) and the inner handle (11112). The inner handle lever (11124) is provided with a protrusion that cooperates with the planetary gear (11125). The middle part of the planetary gear (11125) is rotated on the planetary gear fixing plate (11114) through a rotating shaft. One end of the pull wire (11126) is fixed on the planetary gear (11125).

4. The eVTOL aircraft cabin door lock according to claim 3, characterized in that, The planetary gear (11125) is X-shaped, with the pull cable (11126) attached to the diagonal ends. It is connected to the protrusion of the inner handle lever (11124) in the middle of the X, so that the protrusion can move the planetary gear (11125). When it moves in a certain direction, it can simultaneously tighten and extend the pull cable (11126), maintaining the synchronous control of the pull cable (11126) on the latch assembly (112) to achieve the unlocking and locking functions.

5. The eVTOL aircraft cabin door lock according to claim 3, characterized in that, The latch assembly (112) includes a base plate (1121), a cover plate (1122), a crank (1123), a latch (1124), a first fixing shaft (1125), a second fixing shaft (1126), and screws (1127). The base plate (1121) and the cover plate (1122) are connected together by screws (1127) to form a box-like structure. The base plate (1121) supports the crank (1123) and the latch (1124) respectively through the two first fixing shafts (1125). The support crank (1123) and the locking tongue (1124) are respectively rotatably mounted on two fixed shafts (1125). The support crank (1123) has a shaft hole that matches the fixed shaft (1126). The fixed shaft (1126) is fixedly mounted on the support crank (1123) through the shaft hole. The support crank (1123) is connected to the other end of the pull cable (11126). The front end of the locking tongue (1124) has a fork-shaped structure.

6. The eVTOL aircraft cabin door lock according to claim 5, characterized in that, Both ends of the pull wire (11126) are provided with connection points. The two ends of the pull wire (11126) are connected to the planetary gear (11125) and the crank (1123) respectively by fasteners. The pull wire (11126) is a steel wire structure, which still has a certain rigidity when pushed, and resists the crank (1123).

7. The eVTOL aircraft cabin door lock according to claim 5, characterized in that, The latch assembly (12) includes a latch (121), a latch fixing plate (122), and a nut (123). The latch fixing plate (122) is fixed to the machine body structure. The latch (121) has a U-shaped structure. The end of the latch (121) is provided with a thread and a boss. The boss plays a limiting role. The latch (121) passes through the holes in the latch fixing plate (122) and the machine body structure. At the rear of the machine body structure, the nut (123) is fixed to the latch (121) by engaging with the thread on the latch (121) to ensure that the latch (121) is securely connected.

8. The eVTOL aircraft cabin door lock of claim 7, wherein, The lock seat (13) is provided with an adjustment hole (131), a fixing hole (132), a latch clearance area (133), and a pull cable clearance area (134). The adjustment hole (131) is used to install the lock seat (13) onto the hatch. The adjustment hole (131) is oblong. The fixing hole (132) is provided with threads. The latch assembly (112) is installed into the fixing hole (132) by using threaded fasteners. The pull cable clearance area (134) is used to prevent the pull cable (11126) from being blocked by the lock seat (13) when it moves. The latch clearance area (133) is used to provide a channel for the latch (121) and the latch (1124) to cooperate and meet the movement requirements.

9. The eVTOL aircraft cabin door lock of claim 3, wherein, An outer limiting platform (111131) for limiting the outer handle (11111) is fixedly installed inside the corner box (11113). An inner limiting platform (111133) for limiting the inner handle (11112) is fixedly installed on the outer side of the corner box (11113). A shaft hole (111132) for installing a shaft (11121) is provided on the corner box (11113). The shaft (11121) is rotatably installed inside the corner box (11113) through the shaft hole (111132).

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