A door release mechanism

Abstract

The present invention relates to a fuselage (G) which is an aircraft, at least one door (2) located on the fuselage (G) for providing a passenger with access into or out of the fuselage (G); at least one hinge (3) located on the fuselage (G) providing for the pivoting of the door (2) such that it can move on the fuselage (G); at least one fastener (4) providing for the securing of the door (2) to the fuselage (G) by means of the hinge (3); a handle (5) located within the fuselage (G) so as to be accessible to a user; a first position (I) in which the door (2) is fixedly positioned on the fuselage (G) so as to have a connection with the fuselage (G); at least one rod (6) located between the handle (5) and the fastener (4) in such a way that one end is connected to the handle (5) and the other end is connected to the fastener (4) for transmitting the rotational motion of the handle (5) to the fastener (4); a second position (II) having a door (2) that is separated from the fuselage (G) by the free movement of the fastener (4) which is triggered by the rod (6) with the rotation of the handle (5) by the user; the handle (5) which is brought from the first position (I) to the second position (II) by being rotated by the user; the fastener (4) which is brought from the first position (I) to the second position (II) by being triggered by the rod (6) with the rotation of the handle (5) by the user, and a trigger (7) positioned on the fuselage (G) which, with the movement of the handle (5) from the first position (I) to the second position (II), provides for the separation of the fastener (4) from the hinge (3) by the rod (6) pulling the fastener (4) from the hinge (3).

Description

[0001] A DOOR RELEASE MECHANISM

[0002] The present invention relates to a mechanism for releasing a door for egress from an aircraft in an emergency situation.

[0003] Door release systems are utilized in helicopters to enable the pilot to egress during emergency situations, such as accidents or crashes. The design of door release mechanisms must prevent the door's failure to open due to a malfunction in any component of the system during an emergency. The released door must be openable by the application of human force. Following its activation, the system must create an opening of a sufficient size for a person to pass through. In an emergency, the pilot can exit the aircraft by removing the window transparency. However, as the opening created by this method is small, it is not suitable for the pilot's passage. An explosive charge is placed inside the pin that connects the pilot's door to the fuselage, and with its detonation, the door can be separated from the fuselage. This method presents manufacturing difficulties for systems containing explosives, and the damaged connecting elements and structural parts cannot be reused.

[0004] The United States patent document No. US3851845A, which is included in the prior art, discloses an aperture closure device comprising a quick-release mechanism. It refers to an aircraft door designed to enable the jettisoning of the door in an emergency situation. The device comprises a plurality of detachable hinges operated by a single handle from inside the aircraft. The hinges also include means for the simultaneous release of the normal door closure mechanism. Thus, the complete release of the door is accomplished by the operation of the single handle. The door includes a sliding window, and inner and outer handles that are operably connected to push-pull rods to ensure the closure of the door during normal operation. The hinges have a square end for positioning within levers that are connected to an actuating handle, which is rotatably mounted with rods. Each bracket includes a hinge pin that enables the door to be mounted on the cabin structure. The hinge pin is housed within a hinge that is rotatably mounted to the cabin structure adjacent to the opening to be closed by the door.

[0005] The United States patent document No. US4102011 A, which is included in the prior art, discloses a mechanism that provides for the separation of the door hinges from the door. A linkage provides for the release of the door by simultaneously retracting both pins upon manual actuation of a handle. A mechanism is included which enables the door to be released from its hinges for opening in emergency situations. The release of the door is achieved by removing the pins located on the hinges by means of the handle.

[0006] A door release mechanism developed in accordance with the present invention provides a means for releasing a fastener, thereby allowing the door to separate from the fuselage together with the hinge.

[0007] A further object of the invention is to enable the release of the hinge by means of a reusable fastener, without causing damage to the fuselage.

[0008] A further object of the invention is to ensure the separation of the hinge with the door by means of a mechanism that can be easily actuated with a single handle.

[0009] To achieve the object of the invention, a door release mechanism is provided, as defined in the first claim and the claims dependent thereon, for use on a fixed-wing or rotary-wing aircraft, such as an airplane or a helicopter, which comprises a fuselage that serves as a cabin. There is at least one door, which is removably positioned on the fuselage and provides for ingress to and egress from the aircraft. The assembly comprises at least one hinge that enables the door to be removably mounted on the fuselage and allows it to perform opening and closing movements by rotating about its attachment point. At least one fastener is provided to mount the hinge onto the fuselage, which in turn secures the door on the fuselage via the hinge. There is at least one handle located on and / or within the fuselage, accessible to a user who is a pilot or a passenger. The system comprises a first position (I) wherein the door is connected to the fuselage by means of the fastener to perform its opening and closing function. There is at least one rod, positioned between the handle and the fastener, which transmits the rotational movement of the handle to the fastener when turned by a user. The system comprises a second position (II), in which the door is in a free state, wherein upon rotation of the handle, the rod enables the fastener to separate from the fuselage. It includes a handle that is movable from the first position (I) to the second position (II) by said rotation, in order to allow the fastener to move freely and disengage from the fuselage in an emergency. The system further comprises a trigger, which is actuated by the rod when the handle is moved from the first position (I) to the second position (II), thereby disengaging the fastener from the hinge to release it in the second position (II). The door release mechanism of the invention comprises a pin that, in the first position (I), engages the fastener to restrict its movement within the fuselage and prevent the hinge from separating. A handle is provided, which is rotated by the user from the first position (I) to the second position (II) in order to withdraw the pin, connected to the trigger, from the fastener. The separation of the pin from the fastener, caused by the movement from the first position (I) to the second position (II), enables the hinge to separate from the fuselage together with the door.

[0010] In one embodiment of the invention, the door release mechanism comprises at least one bracket that provides for the clamping of the hinge to the fuselage by means of the fastener, said bracket being aligned with the hinge relative to the fuselage to ensure its proper positioning. The assembly comprises at least one nut, located on the fastener, which secures the fastener to the bracket upon being tightened. The nut includes a nut hole through which the pin can pass to hold the nut stationary. At least one housing is provided on the bracket in the form of a protrusion, into which the nut is seated for positioning. The housing has at least one housing hole, positioned opposite and coaxially with the nut hole, through which the pin passes to engage the nut, thereby ensuring the nut remains within the housing. In the first position (I), the pin is located within the housing hole, in substantially full contact with the inner walls of said hole, thereby restricting the movement of the nut.

[0011] In one embodiment of the invention, the door release mechanism comprises at least one ejection spring located within the housing, which applies a force to the nut for its separation from the housing. In the first position (I), the ejection spring is compressed within the housing by the nut, thereby exerting a force on the nut. This force is transferred from the nut to the pin, causing the pin to bear against the housing hole. This action prevents the pin from separating from the housing hole and ensures that the pin remains immobile within said hole in the first position (I).

[0012] In one embodiment of the invention, the door release mechanism comprises at least one lever located on the trigger, which converts the linear motion of the rod into rotational motion as the rod is moved by the handle when it is brought from the first position (I) to the second position (II) by the user. The lever rotates about its pivot point and moves the pin to which it is connected, thereby causing the pin to be moved from the first position (I) to the second position (II). In one embodiment of the invention, the door release mechanism comprises a first lever end in the form of an extension on the lever, to which the rod is connected to actuate the lever. It further comprises a second lever end, in the form of an extension, where the lever is connected to the pin. At least one support rod is positioned between the second lever end and the pin. As the lever rotates into the second position (II), this support rod pulls the pin linearly away from the fastener, thereby bringing the pin into the second position (II).

[0013] In one embodiment of the invention, the door release mechanism comprises at least one retainer, positioned on the fuselage near the handle, which secures the handle to the fuselage to ensure it remains in the first position (I) and prevents its movement except in an emergency. The retainer features at least one retainer hole, and the handle comprises at least one handle hole for its connection to the retainer. At least one locking pin is provided that, when the retainer hole and handle hole are coaxial, passes through both holes to secure the handle by means of the retainer. This prevents the handle from being moved by the user and ensures it remains fixed in the first position (I).

[0014] In one embodiment of the invention, the door release mechanism comprises at least one handle spring located on the handle, which applies a counter-force to keep the handle in the first position (I). This prevents the handle from rotating to the second position (II) and causing the rod to move.

[0015] In one embodiment of the invention, the door release mechanism comprises at least one trigger spring located on the trigger. This spring applies a counter-moment to the pin, which is in an over-center position in the first position (I), ensuring that the pin remains fixed and maintains its position in the absence of user intervention. The support rod extends in a direction that is different from the axis of the second lever end. The trigger spring applies a counter-force against the lever's tendency to rotate into an in-line position, a rotation which would be caused by the support rod pulling the pin in the release direction while in the first position (I).

[0016] The door release mechanism, realized to achieve the objects of the invention, is illustrated in the accompanying drawings, wherein:

[0017] Figure 1 - A perspective view of the door release mechanism.

[0018] Figure 2 - A side view of the fuselage, door, and hinge. Figure 3 - A detailed perspective view of the hinge.

[0019] Figure 4 - A detailed perspective view of the trigger.

[0020] Figure 5 - A perspective view of the hinge, rod, and trigger.

[0021] Figure 6 - A detailed perspective view of the bracket.

[0022] Figure 7 - A perspective view of the handle, rod, and fuselage.

[0023] Figure 8 - A cross-sectional view of the fastener, hinge, and bracket in the first position (I).

[0024] Figure 9 - A cross-sectional view of the fastener, hinge, and bracket in the second position (H).

[0025] Figure 10 - A perspective view of the handle, retainer, and locking pin.

[0026] Figure 11 - A side view of the handle in the first position (I).

[0027] Figure 12 - A perspective view of the handle in the second position (II).

[0028] The components in the drawings are individually numbered, and the parts corresponding to these numbers are listed below.

[0029] 1 . Door Release Mechanism

[0030] 2. Door

[0031] 3. Hinge

[0032] 4. Fastener

[0033] 5. Handle

[0034] 510. Handle Hole

[0035] 520. Handle Spring

[0036] 6. Rod

[0037] 7. Trigger

[0038] 710. Bracket

[0039] 720. Housing

[0040] 730. Housing Hole 740. Lever

[0041] 750. First Lever End

[0042] 760. Second Lever End

[0043] 770. Support Rod

[0044] 780. Trigger Spring

[0045] 8. Pin

[0046] 9. Nut

[0047] 10. Nut Hole

[0048] 1 1 . Ejection Spring

[0049] 12. Retainer

[0050] 13. Retainer Hole

[0051] 14. Locking pin

[0052] (G) Fuselage

[0053] (1) First Position

[0054] (II) Second Position

[0055] The door release mechanism (1 ) comprises a fuselage (G) which is an aircraft; at least one door (2), located on the fuselage (G), for providing a passenger with access into or out of the fuselage (G); at least one hinge (3), located on the fuselage (G), for pivotally mounting the door (2) such that it can move relative to the fuselage (G); at least one fastener (4), for securing the door (2) to the fuselage (G) by means of the hinge (3); a handle (5), located within the fuselage (G) so as to be accessible to a user; a first position (I), in which the door

[0056] (2) is fixedly positioned on the fuselage (G) so as to be connected to the fuselage (G); at least one rod (6), positioned between the handle (5) and the fastener (4), with one end connected to the handle (5) and the other end connected to the fastener (4), for transmitting the rotational motion of the handle (5) to the fastener (4); a second position (II), in which the door (2) is separated from the fuselage (G) as the fastener (4), triggered by the rod (6) upon rotation of the handle (5) by the user, moves freely; the handle (5), which is moved from the first position (I) to the second position (II) by being rotated by the user; the fastener (4), which is moved from the first position (I) to the second position (II), being triggered by the rod (6) upon the rotation of the handle (5) by the user; a trigger (7), positioned on the fuselage (G), which, upon movement of the handle (5) from the first position (I) to the second position (II), causes the rod (6) to pull the fastener (4) from the hinge (3), providing for its separation from the hinge (3). (Figure -1 , Figure -2) The door release mechanism (1 ) subject to the invention comprises a pin (8) located on a fastener (4) wherein, in a first position (I), the pin (8) secures the fastener (4) on the fuselage (G), thereby ensuring the hinge (3) remains on the fuselage (G); the handle (5), wherein, when moved to the second position (II) by a user, rotates the trigger (7) about its pivot point by means of the rod (6), thereby causing the pin (8) to disengage from the fastener (4); the pin (8), which, by means of the handle (5) being moved from the first position (I) to the second position (II), severs the connection between the hinge (3) and the fuselage (G), providing for the simultaneous release of the fastener (4) together with the door (2) and the hinge (3). (Figure -3 and Figure -5)

[0057] A door (2) is provided on the fuselage (G) of an aircraft, such as a helicopter or an airplane, which allows users like a pilot or a passenger ingress to and egress from the fuselage (G). The door (2) is secured to the fuselage (G) by means of the hinge (3) and moves by rotating about the point where it is mounted, facilitated by said hinge (3). The hinge (3) is secured to the fuselage (G) by means of at least one fastener (4). A handle (5) is provided for use outside of normal operation, which, in emergency situations such as a crash, allows a user to exit by opening the door (2). The handle (5) enables the door (2) which is openable under normal conditions to be opened by separating from its hinges (3), allowing passengers to egress from a crashed fuselage (G). In the first position (I), the door (2) is positioned on the fuselage (G) together with the hinge (3), connected by means of the fastener (4). During an emergency, the handle (5), when rotated by the user, actuates the fastener (4) by means of the rod (6) in order to remove the fastener (4) from within the hinge (3). The rod (6) is positioned between the fastener (4) and the handle (5) in order to transmit the motion from the actuation of the handle (5) to the fastener (4). The mechanism comprises a second position (II) wherein, upon rotation and actuation of the handle (5) from the first position (I) by the user, the fastener (4) releases the hinge (3) and the door (2) separates from the fuselage (G). The handle (5), when moved from the first position (I) to the second position (II), enables egress from the fuselage (G) in an emergency by causing the separation of the door (2) from the hinge (3). In the event of a crash, the user rotates the handle (5) to move it from the first position (I) to the second position (II). Upon reaching the second position (II), the handle (5), by means of the rod (6), moves the fastener (4) from the first position (I) to the second position (II), thereby enabling the door (2) to be opened. The fastener (4) is brought to the second position (II) by means of a trigger (7). (Figure -4, Figure -7) It comprises a pin (8) that keeps the fastener (4) in the first position (I), in which the fastener (4) secures the door (2) on the fuselage (G) by means of the hinge (3). By being located on the fastener (4), the pin (8) ensures that the hinge (3) remains fixed together with the door (2). When the handle (5) is moved from the first position (I) to the second position (II) by being rotated by the user, the rod (6) connected to the handle (5) moves the trigger (7), causing it to rotate about its pivot point and thereby causing the pin (8) to disengage from the fastener (4). When the pin (8) is brought into the second position (II), it separates from the fastener (4), enabling the hinge (3) to detach from the fuselage (G). In the second position (II), the door (2) is in a free position, ready to move away from the fuselage (G) simultaneously with the hinge (3). The door (2) is preferably secured to the fuselage (G) with two hinges (3). The release of the hinges (3) is accomplished by the handle (5) by means of at least one rod (6); preferably, the number of rods (6) is equal to the number of hinges (3). Preferably, a trigger (7) is positioned on the fuselage (G) for each hinge (3) to provide for the release of the corresponding fasteners (4). In this way, the fastener (4) holding the hinge (3) on the fuselage (G) separates from the pin (8), allowing the hinge (3) to be moved away from the fuselage (G) together with the door (2). Thus, by means of a single handle (5), all hinges (3) are released, enabling the door (2) to move away from the fuselage (G). (Figure -1 1 and Figure -12)

[0058] In one embodiment of the invention, the door release mechanism (1 ) comprises at least one bracket (710), positioned on the inner surface of the fuselage (G) opposite the hinge (3) on the outer surface, for securing the fastener (4) to the fuselage (G); a nut (9), located on the fastener (4), for securing the fastener (4) to the bracket (710); a nut hole (10), located on the nut (9), through which the pin (8) passes to keep the nut (9) stationary; a housing (720), located on the bracket (710), into which the nut (9) is seated and which surrounds the nut (9); at least one housing hole (730), located on the housing (720) opposite and aligned with the nut hole (10), through which the pin (8) passes; wherein, in a first position (I), the pin (8) bears against the inner walls of the housing hole (730), thereby ensuring that the nut (9) remains fixed within the housing (720). A bracket (710) is located on the fuselage (G), which serves to hold the hinge (3) onto the fuselage (G). The bracket (710) is positioned on the fuselage (G) by means of the fastener (4) so as to be in alignment with the hinge (3). A nut (9) is located on the fastener (4). A housing (720) is provided in the form of a recess, which positions the nut (9) on the bracket (710) and, by means of said nut (9), ensures that the fastener (4) remains fixed on the bracket (710) in the first position (I). A nut hole (10) is provided on the nut (9) for the pin (8) to engage the nut (9). The pin (8) passes through the nut hole (10) to ensure the fastener (4) is positioned on the fuselage (G). In the first position

[0059] (I), the pin (8) passes through the nut hole (10) on the nut (9), thereby preventing the fastener (4) from moving. A housing hole (730) is provided on the housing (720) to hold the nut (9) within the housing (720) in the first position (I) by allowing the pin (8) to pass through the nut hole (10) on the nut (9). In the second position (II), the pin (8) disengages from the nut (9), allowing the nut (9) to be released along with the fastener (4). The housing hole (730) is positioned to be coaxial with the nut hole (10) when the nut (9) is seated in the housing (720), allowing the pin (8) to pass through both the housing hole (730) and the nut hole (10). By the pin (8) contacting the inner surface of the housing hole (730), the movement of the nut (9) is impeded, which in turn prevents the nut (9) from separating from the bracket (710). In the first position (I), the pin (8) holds the nut (9) fixedly within the housing (720). Thus, while the handle (5) is in the first position (I), the separation of the fastener (4) from the bracket (710) is prevented. (Figure -6)

[0060] In one embodiment of the invention, the door release mechanism (1 ) comprises an ejection spring (1 1 ) wherein in the second position (II), causes the released fastener (4) to be ejected from the housing (720); and in the first position (I), ensures that the pin (8) remains fixed within the housing hole (730) by damping the vibrations of the fuselage (G) through the frictional force created on the surface of the pin (8) where it contacts the housing hole (730). When the pin (8) is moved from the first position (I) to the second position (II), it separates from the housing hole (730), allowing the nut (9) to move freely within the housing (720) . An ejection spring (1 1 ) is positioned within the housing (720) to provide for the simultaneous separation of the fastener (4) as it releases the hinge (3), in order to allow the user to move the door (2) away from the fuselage (G). In the second position (II), the ejection spring (1 1 ) applies a pushing force to the released nut (9), causing the nut (9) to move away from the housing (720) and thereby enabling the fastener (4) to move together with the hinge (3). Thus, it provides for the ejection of the nut (9) from within the housing (720) by means of a pushing force against said nut (9), in order to enable the removal of the fastener (4) released in the second position (II) from the fuselage (G) along with the hinge (3). The ejection spring

[0061] (I I ), which is compressed by the nut (9) in the first position (I) to create a pushing force, applies this pushing force to the nut (9). Thus, the pushing force of the ejection spring (11 ) is transferred to the pin (8), creating a frictional force through the contact between the pin (8) and the inner walls of the housing hole (730); this frictional force acts against forces arising from external factors like fuselage (G) vibrations, ensuring the pin (8) remains in the first position (I) within the housing hole (730). (Figure -6 and Figure -9) In one embodiment of the invention, the door release mechanism (1 ) comprises at least one lever (740), which is pivotally mounted on the bracket (710) and which, when the handle (5) is moved from the first position (I) to the second position (II) by a user, transmits the linear motion of the rod (6) to the trigger (7), and by means of its rotational motion about its pivot point, causes the pin (8) to disengage from the fastener (4). A lever (740) is provided, which transmits the rotational motion of the handle (5) to the pin (8) by means of the rod (6), and which causes the pin (8) to disengage from the fastener (4) as it is moved from the first position (I) to the second position (II). The lever (740) is preferably located on the bracket (710). The lever (740) brings the pin (8) to the second position (II) when the rod (6) is pulled by the handle (5). By rotating about its pivot point on the trigger (7) under the action of the rod (6), it causes the pin (8) to be moved from the first position (I) to the second position (II). In this way, by means of the lever (740) which transmits the motion of the rod (6) to the pin (8), the pin (8) is moved away from the fastener (4). (Figure -3)

[0062] In one embodiment of the invention, the door release mechanism (1 ) comprises a first lever end (750), located on the lever (740), which is the part where the rod (6) is connected to the lever (740); a second lever end (760), located on the lever (740), which is the part where the pin (8) is connected to the lever (740); at least one support rod (770), one end of which is connected to the second lever end (760) and the other end to the pin (8), for linearly transmitting the rotational motion of the lever (740) about its pivot point to the pin (8); the support rod (770), which provides for the withdrawal of the pin (8) from the fastener (4), thereby enabling the pin (8) to move from the first position (I) to the second position (II) . A first lever end (750) is provided in the form of an extension, which is the connection point for the lever (740) with the rod (6). One end of the rod (6) pulls the first lever end (750), thereby causing the lever (740) to rotate. A second lever end (760) is provided on the lever (740), extending from the lever (740) in a direction different from that of the first lever end (750). A support rod (770) is provided, one end of which is connected to the pin (8) and the other end to the second lever end (760). In the first position (I), the support rod (770) is positioned in an over-center configuration so as to prevent the pin (8) from moving away from the fastener (4). The pin (8) is moved from the first position (I) to the second position (II) through the nut (9) located on the fastener (4) by means of the support rod (770), thereby causing the fastener (4) to separate from the trigger (7) together with the nut (9). It provides for the movement of the pin (8) from the first position (I) to the second position (II) by linearly transmitting the rotational motion of the lever (740) to the pin (8). Thus, by employing an over-center configuration in the first position (I), unintentional movement of the pin (8) to the second position (II) is prevented. (Figure -4)

[0063] In one embodiment of the invention, the door release mechanism (1 ) comprises at least one retainer (12), located on the fuselage (G), which prevents the handle (5) from moving by holding it in the first position (I); at least one retainer hole (13), located on the retainer (12); at least one handle hole (510), located on the handle (5); at least one locking pin (14), which passes through the handle hole (510) and the retainer hole (13) to secure the handle (5) to the retainer (12), thereby preventing it from moving from the first position (I) to the second position (II). A retainer (12) is provided which prevents the handle (5) from being moved from the first position (I) to the second position (II) except in an emergency. Unintentional rotation of the handle (5) is prevented by means of a locking pin (14) that passes through the handle hole (510) and the retainer hole (13) when the handle (5) is positioned in the first position (I) such that its handle hole (510) is coaxial with the retainer hole (13). In an emergency, the pilot enables the rotation of the handle (5) by pulling the locking pin (14) and removing it from the handle hole (510) and the retainer hole (13). Thus, during normal operation, the handle (5) is kept in the first position (I) by means of the locking pin (14) to prevent the unintentional release of the door (2). (Figure -10)

[0064] In one embodiment of the invention, the door release mechanism (1 ) comprises at least one handle spring (520), which prevents the movement of the handle (5) by applying a force that ensures it remains in the first position (I). A handle spring (520) is located on the handle (5), which prevents the handle (5) from moving from the first position (I) to the second position (II). The handle spring (520) prevents the handle (5) from moving on its own from the first position (I) to the second position (II) by applying a force to the handle (5) in a direction opposite to its opening direction. In this way, the application of force to the handle (5) by the handle spring (520) ensures that the handle (5) remains in the first position (I). (Figure -10)

[0065] In one embodiment of the invention, the door release mechanism (1 ) comprises at least one trigger spring (780), located on the trigger (7), which applies a force that keeps the trigger (7) in a closed state in the first position (I) by preventing the pin (8) from disengaging. The trigger spring (780) applies a force to the trigger (7), thereby preventing its rotation. In this way, the withdrawal of the pin (8) by the trigger (7) is prevented. Thus, the trigger (7) is prevented from involuntarily rotating from the first position (I) to the second position (II), ensuring that it remains in the first position (I). (Figure -8)

Claims

CLAIMS1 . The door release mechanism (1 ) comprising a fuselage (G) which is an aircraft; at least one door (2), located on the fuselage (G), for providing a passenger with access into or out of the fuselage (G); at least one hinge (3), located on the fuselage (G), for pivotally mounting the door (2) such that it can move relative to the fuselage (G); at least one fastener (4), for securing the door (2) to the fuselage (G) by means of the hinge (3); a handle (5), located within the fuselage (G) so as to be accessible to a user; a first position (I), in which the door (2) is fixedly positioned on the fuselage (G) so as to be connected to the fuselage (G); at least one rod (6), positioned between the handle (5) and the fastener (4), with one end connected to the handle (5) and the other end connected to the fastener (4), for transmitting the rotational motion of the handle (5) to the fastener (4); a second position (II), in which the door (2) is separated from the fuselage (G) as the fastener (4), triggered by the rod (6) upon rotation of the handle (5) by the user, moves freely; the handle (5), which is moved from the first position (I) to the second position (II) by being rotated by the user; the fastener (4), which is moved from the first position (I) to the second position (II), being triggered by the rod (6) upon the rotation of the handle (5) by the user; a trigger (7), positioned on the fuselage (G), which, upon movement of the handle (5) from the first position (I) to the second position (II), causes the rod (6) to pull the fastener (4) from the hinge (3), providing for its separation from the hinge (3) characterized in that it comprises a pin (8), located on the fastener (4), which in the first position (I) secures the fastener (4) on the fuselage (G), thereby ensuring that the hinge (3) remains on the fuselage (G); the handle (5), which, when moved to the second position (II) by a user, rotates the trigger (7) about its pivot point by means of the rod (6), thereby causing the pin (8) to disengage from the fastener (4); wherein the pin (8), which, by means of the handle (5) being moved from the first position (I) to the second position (II), severs the connection between the hinge (3) and the fuselage (G), providing for the simultaneous release of the fastener (4) together with the door (2) and the hinge (3).

2. The payload release mechanism (1 ) according to claim 1 , characterized in that it comprises at least one bracket (710), positioned on the inner surface of the fuselage (G) opposite the hinge (3) located on the outer surface of the fuselage (G), for securing the fastener (4) to the fuselage (G); a nut (9), located on the fastener (4), for securing the fastener (4) on the bracket (710); a nut hole (10), located on the nut (9), throughwhich the pin (8) passes, thereby ensuring the nut (9) remains stationary; at least one housing (720), located on the bracket (710), into which the nut (9) is seated and which surrounds said nut (9); at least one housing hole (730), located on the housing (720), which is opposite and aligned with the nut hole (10), and through which the pin (8) passes to ensure the nut remains fixed and the pin (8), which in the first position (I) bears against the inner walls of the housing hole (730) to ensure the nut (9) remains fixed within the housing (720).

3. The payload release mechanism (1 ) according to claim 2, characterized in that it comprises at least one ejection spring (11 ), which is positioned within the housing (720) by means of the fastener (4), and which, in the second position (II), causes the released fastener (4) to be ejected from the housing (720); at least one ejection spring (11 ), which ensures the pin (8) remains fixed within the housing hole (730) by damping vibrations of the fuselage (G) through the frictional force created in the first position (I) on the surface of the pin (8) where it contacts the housing hole (730).

4. The payload release mechanism (1 ) according to claim 2 or claim 3, characterized in that it comprises at least one lever (740), which is pivotally mounted on the bracket (710) and which, when the handle (5) is moved by a user from the first position (I) to the second position (II), transmits the linear motion of the rod (6) to the trigger (7), and by means of its rotational motion about its pivot point, causes the pin (8) to disengage from the fastener (4).

5. The payload release mechanism (1 ) according to claim 4, characterized in that it comprises a first lever end (750), located on the lever (740), which is the part where the rod (6) is connected to the lever (740); a second lever end (760), located on the lever (740), which is the part where the pin (8) is connected to the lever (740); at least one support rod (770), one end of which is connected to the second lever end (760) and the other end to the pin (8), for linearly transmitting the rotational motion of the lever (740) about its pivot point to the pin (8) and the support rod (770), which provides for the withdrawal of the pin (8) from the fastener (4), thereby enabling the pin (8) to move from the first position (I) to the second position (II).

6. The payload release mechanism (1 ) according to claim any of the preceding claims, characterized in that it comprises at least one retainer (12), located on the fuselage (G), which prevents the handle (5) from moving by holding it in the first position (I); atleast one retainer hole (13), located on the retainer (12); at least one handle hole (510), located on the handle (5); and at least one locking pin (14), which passes through the handle hole (510) and the retainer hole (13) to secure the handle (5) to the retainer (12), thereby preventing it from moving from the first position (I) to the second position (H).

7. The payload release mechanism (1 ) according to claim any of the preceding claims, characterized in that it comprises at least one handle spring (520) that prevents the movement of the handle (5) by applying a force which ensures it remains in the first position (I).

8. The payload release mechanism (1 ) according to claim any of the preceding claims, characterized in that it comprises at least one trigger spring (780), located on the trigger (7), which applies a force that keeps the trigger (7) in a closed state in the first position (I) by preventing the pin (8) from disengaging.

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