Aircraft delivery device and aircraft comprising the same

Abstract

An aircraft delivery device and an aircraft including the same are provided. The aircraft delivery device is disposed outside a delivery cabin of the aircraft and includes a cabin door mechanism having a left cabin door and a right cabin door which are symmetrical to each other, a latch mechanism disposed between the left cabin door and the right cabin door and configured to fix the cabin door mechanism in a closed state, and an opening and closing mechanism configured to actuate opening and closing of the cabin door mechanism. By disposing the aircraft delivery device outside the delivery cabin of the aircraft, adverse effects of a substance to be delivered in the delivery cabin on operation of the delivery mechanism can be avoided, and a medium such as a liquid can be properly delivered.

Description

Technical Field

[0001] This invention relates to an aircraft delivery device and an aircraft, and more specifically, to an aircraft delivery device applicable to transport aircraft and belonging to the field of aircraft fuselage door design, and an aircraft including the aircraft delivery device. Background Technology

[0002] Aircraft delivery systems are an important component of transport aircraft, primarily used to transport equipment and supplies from the air to designated locations. They are the main means of delivering these equipment and supplies to areas in need.

[0003] The delivery device of transport aircraft is mainly used to deliver liquid fire extinguishing media, bagged fire extinguishing media, pesticides, seeds, fertilizers and other items. During delivery, due to the different properties of the items to be delivered, the aircraft needs to adjust the flight altitude for delivery operations according to the characteristics of the items being delivered.

[0004] After the drop operation, the center of gravity of the aircraft will change significantly before and after the drop operation due to the large mass of materials carried on the aircraft being dropped to the ground, which may affect the safe flight of the aircraft.

[0005] At this point, increasing the aircraft's altitude is an effective way to improve safety after the deployment operation. However, if the aircraft's altitude is increased excessively, factors such as atmospheric pressure and airflow may cause liquids to evaporate or disperse, potentially preventing the proper deployment of liquid media such as pesticides.

[0006] To enable the proper delivery of liquid media, existing aircraft delivery devices primarily employ a design that places the delivery mechanism within the aircraft cabin. Examples include the door mechanisms described in patents US4936389A (Fluid Dispenser for An Aircraft), CA1320188C (Fluid Dispenser for an Aircraft), CN115447780A (A Scheme for a Water Drop Door for a Firefighting Aircraft), CN117163287A (A Water Drop Door Mechanism), CN112478129A (A Water Drop Door for a Firefighting Aircraft), and CN112478129A (An Aircraft Delivery Door). Some implementations also place the actuation mechanism of the delivery door within the aircraft cabin for liquid media delivery, such as in patent WO2012058677A9 (Pressure Assured Variele Flow Clean Throat Aircraft Reliability). The hatch actuation mechanism described in the retardant De laver system.

[0007] However, all the above-mentioned technical solutions place the delivery mechanism inside the aircraft cabin, specifically on the inner skin side of the cabin door. Due to the liquid nature of the delivered medium, the delivery mechanism is more susceptible to corrosion by the delivered medium, and its movement becomes sluggish due to the influence of the delivered medium. In addition, the above-mentioned design solutions can only deliver liquid media and are not suitable for delivering bagged extinguishing agents, seeds, fertilizers, or other solid media.

[0008] To overcome the aforementioned technical problems, it is possible to consider placing the aircraft launch mechanism inside the aircraft cabin on the front and rear panels. However, this design requires higher strength and rigidity from the aircraft's panels.

[0009] To ensure the opening and closing function requirements of the delivery device, the area of ​​each delivery opening needs to be reduced to decrease the load on the aircraft structure during the delivery process of a single delivery device. In order to ensure delivery efficiency, the number of delivery openings and delivery devices needs to be increased, which will make the overall structural design more complex.

[0010] Therefore, there is an urgent need to provide a new aircraft delivery device that can overcome the aforementioned technical problems. Summary of the Invention

[0011] This disclosure is made to solve the above-mentioned technical problems, and its purpose is to provide an aircraft delivery device and an aircraft including the aircraft delivery device, wherein the aircraft delivery device appropriately delivers a liquid medium while ensuring the flight safety of the aircraft.

[0012] To achieve the purpose of this disclosure, an aircraft delivery device is provided, which is disposed outside the delivery compartment of an aircraft. The aircraft delivery device includes: a door mechanism having a left door and a right door symmetrical to each other; a latch mechanism disposed between the left door and the right door and used to fix the door mechanism in a closed state; and an opening and closing mechanism for actuating the opening and closing of the door mechanism.

[0013] According to the configuration described above, by placing the aircraft delivery device outside the aircraft's delivery compartment, it is possible to avoid adverse effects of the material to be delivered inside the delivery compartment on the operation of the delivery mechanism, and to appropriately deliver media such as liquids.

[0014] Preferably, it further includes a sensor assembly, which is arranged on the latch mechanism and the door mechanism, and is used to monitor the latching status, unlocking status of the latch mechanism and the opening and closing status of the door mechanism.

[0015] As described above, by using sensor components to monitor the latching and unlocking status of the latching mechanism and the opening and closing status of the door mechanism, it is possible to prevent adverse situations such as the door being actuated when the latching mechanism is in the latching state, causing damage to the mechanism or the door being opened accidentally.

[0016] Preferably, the latching mechanism includes a latch shaft disposed between latch shaft supports and a latch joint disposed on the door mechanism. When the door mechanism is in the closed state, the latch shaft engages with the latch joint to lock the door mechanism in the closed state. When it is necessary to open the door mechanism, the latch shaft and the latch joint disengage to release the lock of the door mechanism.

[0017] Preferably, the latch mechanism further includes a latch actuator, a latch rocker arm, and a latch torque rod. The latch shaft is fixedly mounted on the latch torque rod. The latch actuator drives the latch torque rod to rotate around its own axis via the latch rocker arm, so as to lock and unlock the latch shaft relative to the latch joint.

[0018] As described above, the latching and unlocking of the hatch mechanism can be achieved with a simple structure through the corresponding latch shaft and latch joint, which is simple to implement and easy to operate.

[0019] Preferably, multiple latches are provided corresponding to the latch joints and are arranged along the length direction of the hatch of the hatch mechanism.

[0020] As described above, by providing multiple latch shafts and latch joints along the length of the hatch, the locking strength when locking the hatch mechanism, i.e., latching, can be improved.

[0021] Preferably, the opening and closing mechanism includes an opening and closing actuator, an opening and closing torque rod, an opening and closing rocker arm, and a connecting joint. The opening and closing actuator is connected to the opening and closing torque rod via the connecting joint and to the opening and closing rocker arm via the opening and closing torque rod. The other end of the opening and closing rocker arm is connected to the hatch of the hatch mechanism. The opening and closing actuator drives the opening and closing torque rod to rotate around its own axis, thereby driving the hatch to open and close via the opening and closing rocker arm.

[0022] Based on the above-described configuration, the opening and closing mechanism can realize the opening and closing of the hatch through a simple structure, which is simple to implement and easy to operate.

[0023] Preferably, multiple opening and closing rocker arms are provided and are arranged along the length direction of the hatch of the hatch mechanism.

[0024] As described above, by arranging multiple opening and closing rocker arms along the length of the hatch, the hatch can be stably actuated to open and close, thereby ensuring the stability of the overall structure of the delivery device.

[0025] Preferably, the aforementioned hatch mechanism employs an eccentric design where the cross-sectional center of the latch joint does not coincide with the cross-sectional center of the latch shaft.

[0026] As described above, the eccentric design of the hatch mechanism allows the latch to be engaged (locked) by utilizing the weight of the deployed medium, the rebound force of the seals, and the weight of the hatch structure when the hatch needs to be closed, thereby reducing the risk of accidental hatch opening. Furthermore, in the initial stage of hatch opening, the latch mechanism must overcome the weight of the deployed medium, the rebound force of the seals, and the weight of the hatch structure until the latch reaches the center point. After passing the center point, the weight of the deployed medium, the rebound force of the seals, and the weight of the hatch structure help open the hatch.

[0027] Preferably, the aforementioned aircraft launch device forms a V-shaped structure when it is in a fully closed state, that is, the hatch of the aforementioned door mechanism forms a certain angle with respect to the horizontal plane.

[0028] Based on the above configuration, it can help to quickly drain the leaked delivery medium, thereby reducing the impact of the leaked medium on the delivery device and the aircraft.

[0029] Preferably, when it is necessary to open the hatch of the aforementioned hatch mechanism, firstly, the aforementioned latch mechanism performs an unlocking operation to release the lock of the aforementioned hatch mechanism, then, a medium is introduced to push the hatch open, and the aforementioned opening and closing mechanism performs an opening operation to open the hatch of the aforementioned hatch mechanism; when it is necessary to close the hatch of the aforementioned hatch mechanism, firstly, the aforementioned opening and closing mechanism performs a closing operation to close the hatch of the aforementioned hatch mechanism, and then, the aforementioned latch mechanism performs a latching operation to lock the aforementioned hatch mechanism in the closed state.

[0030] As described above, when the hatch mechanism is closed, the hatch structure can be locked in the closed state by the latch mechanism, thereby ensuring the structural stability when closed and preventing the hatch from being accidentally opened and causing leakage of materials inside the cabin.

[0031] In addition, the present invention also provides an aircraft, which includes the aircraft delivery device described above. Attached Figure Description

[0032] In view of the above objectives, the technical features of the present invention are clearly described in the following technical solutions, and its advantages are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the invention by way of example, without limiting the scope of the inventive concept.

[0033] Figure 1 This is a front view of the aircraft delivery device of the present invention.

[0034] Figure 2 This is a three-dimensional structural diagram of the aircraft delivery device of the present invention.

[0035] Symbol Explanation

[0036] 1. Aircraft launch device;

[0037] 11. Cabin door mechanism;

[0038] 111 Left hatch;

[0039] 112 Starboard door;

[0040] 12-latch mechanism;

[0041] 121. Latch actuator;

[0042] 122 latch rocker arm;

[0043] 123 Latch torque lever;

[0044] 124 latch shaft support;

[0045] 125 latch shaft;

[0046] 126 Latch joint;

[0047] 13. Opening and closing mechanism;

[0048] 131 Opening and closing actuator;

[0049] 132 Opening / closing torque lever;

[0050] 133 Opening and closing rocker arm;

[0051] 134 Combined connector;

[0052] 14. Sensor assembly;

[0053] 2. Body connector;

[0054] 3. Door connector;

[0055] 4. Fuselage. Detailed Implementation

[0056] One embodiment of the invention will now be described in detail, an example of which is illustrated in the accompanying drawings. Although the invention has been described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to the exemplary embodiments described below. Rather, the invention is intended to cover not only the exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0057] The following is for reference Figure 1 The overall structure of the aircraft delivery device 1 of the present invention will be described. Figure 1 This is a schematic diagram showing the overall structure of the aircraft delivery device 1 of the present invention.

[0058] like Figure 1 As shown, the aircraft delivery device 1 of the present invention is arranged outside the delivery compartment of the aircraft, and mainly includes a door mechanism 11, a latch mechanism 12, an opening and closing mechanism 13 and a sensor assembly 14.

[0059] The aforementioned door mechanism 11 mainly includes a left door 111 and a right door 112. The left door 111 and the right door 112 are independent of each other and open opposite each other, and are joined together to form a door for closing the aircraft's drop-off compartment.

[0060] The latching mechanism 12 is mainly used to latch the left door 111 and the right door 112 of the door mechanism 11 when the aircraft's drop-off compartment is closed, so as to fix the door formed by the left door 111 and the right door 112 in the closed state, and to unlock the left door 111 and the right door 112 of the door mechanism 11 when it is necessary to open the aircraft's drop-off compartment, so as to open the door formed by the left door 111 and the right door 112.

[0061] The opening and closing mechanism 13 is mainly used to actuate the left hatch 111 and the right hatch 112 respectively when the hatch of the hatch mechanism 11 needs to be opened, so as to open the hatch composed of the left hatch 111 and the right hatch 112 to release liquid media, etc. in the compartment, and to actuate the left hatch 111 and the right hatch 112 respectively when the hatch of the hatch mechanism 11 needs to be closed, so as to close the hatch composed of the left hatch 111 and the right hatch 112.

[0062] The aforementioned sensor assembly 14 is respectively arranged on the left cabin door 111 and right cabin door 112 of the latch mechanism 12 and the cabin door mechanism 11. It is mainly used to monitor the opening and closing status of the left cabin door 111 and right cabin door 112 and the latching status of the latch mechanism 12, and transmit the monitoring results to the central control system of the aircraft, so as to prevent the cabin door from being actuated when the latch mechanism 12 is in the latching state, which would cause damage to the mechanism or the cabin door from being opened by mistake.

[0063] The following is for reference Figure 2 The specific structure of each part of the aircraft delivery device 1 of the present invention will be described. Figure 2 This is a three-dimensional structural schematic diagram of the aircraft delivery device 1 of the present invention.

[0064] It should be noted that, for ease of illustration, [the text is incomplete and requires further context]. Figure 2 The aircraft delivery device 1 shown is described by being completely reversed. Figure 2 The space above the middle section belongs to the external space of the delivery compartment, that is, the area below the aircraft. Figure 2 The area below refers to the interior space of the delivery compartment, i.e., above the aircraft. Therefore, the terms "above" and "below" as described below are primarily relative to the area above and below the aircraft.

[0065] like Figure 2 As shown, the aircraft delivery device 1 of the present invention mainly includes a door mechanism 11, a latch mechanism 12, and an opening and closing mechanism 13.

[0066] The aforementioned door mechanism 11 includes a left door 111 and a right door 112. The two doors are generally rectangular in shape and open independently and opposite each other, thus forming a door that closes the delivery compartment of the aircraft delivery device 1.

[0067] The latch mechanism 12 is arranged below the storage container of the delivery compartment and is mainly arranged between the left hatch 111 and the right hatch 112 of the door mechanism 11. It mainly includes a latch actuator 121, a latch rocker arm 122, a latch torque rod 123, a latch shaft support 124, a latch shaft 125, and a latch joint 126.

[0068] The aforementioned latch actuator 121 includes two for the left hatch 111 and the right hatch 112. One end of the actuator is connected to the fuselage joint 2, and the other end is connected to the latch rocker arm 122. The latch rocker arm 122 is used to drive the latching and unlocking operations of the two hatches.

[0069] The aforementioned latch rocker arm 122 includes two for the left hatch 111 and the right hatch 112. One end of the rocker arm is connected to the actuation rod of the latch actuator 121, and the other end is connected to the latch torque rod 123, thereby driving the latch torque rod 123 to rotate around its center line.

[0070] The aforementioned latch torque rod 123 includes two for the left hatch 111 and the right hatch 112. The length direction of the latch torque rod 123 is parallel to the long side direction of the hatch, and one end of it is connected to the latch rocker arm 122. The latch torque rod 123 is installed by passing through multiple latch shaft supports 124 and multiple latch shafts 125.

[0071] The aforementioned latch support 124 and latch shaft 125 are disposed between the left hatch 111 and the right hatch 112. The latch support 124 has two mounting holes for the latch torque rod 123 to pass through and be installed. Two latch shafts 125 are sandwiched and installed between the two latch supports 124. The two latch shafts 125 are respectively provided for the left hatch 111 and the right hatch 112. An engagement mechanism is formed on the latch shaft 125 to engage with the latch joint 126 provided on the hatch.

[0072] The latch joint 126 is provided on the hatch and is correspondingly provided with the latch shaft 125. The latch shaft 125 is fixedly installed on the latch torque rod 123 through a coupling or connecting joint, and rotates under the drive of the latch torque rod 123, thereby engaging with the latch joint 126, i.e. latching, or disengaging from the latch joint 126, i.e. unlocking.

[0073] In this embodiment, the door mechanism 11 of the above-mentioned aircraft delivery device 1 is provided with two latch actuators 121, two latch rocker arms 122, two latch torque rods 123, eleven latch shaft supports 124, eight latch shafts 125, and eight latch joints 126.

[0074] The number of latch actuators 121, latch rocker arms 122 and latch torque rods 123 is generally fixed, with two provided for the left hatch 111 and the right hatch 112 respectively. However, the latch shaft support 124, latch shaft 125 and latch joint 126 can be appropriately provided according to the length of the hatch and the latch torque rod. It is best to arrange the latch shaft 125 and latch joint 126 evenly along the length of the hatch.

[0075] In addition, the latch joint 126 of the aforementioned door mechanism 11 adopts an eccentric design, that is, the center of the cross section of the latch joint 126 does not coincide with the center of the cross section of the latch shaft 125.

[0076] In this way, the eccentric design of the latch joint can cause the latch joint to tend to latch up when the hatch needs to be closed, thereby reducing the risk of the hatch being accidentally unlatched during deployment.

[0077] The aforementioned opening and closing mechanism 13 mainly includes an opening and closing actuator 131, an opening and closing torque rod 132, an opening and closing rocker arm 133, and a connecting joint 134.

[0078] The aforementioned opening and closing actuator 131 includes two for the left cabin door 111 and the right cabin door 112, one end of which is connected to the fuselage joint 2, and the other end is connected to the opening and closing torque rod 132 via the joint joint 134.

[0079] The opening and closing torque rod 132 is formed such that its length direction is approximately orthogonal to the length direction of the opening and closing actuator 131. The opening and closing torque rod 132 is connected to the body joint 2 and the opening and closing rocker arm 133 at its two ends via connectors, and is connected to the actuating rod of the opening and closing actuator 131 via a joint joint 134 at approximately the middle position. Thus, it can rotate around its own axis under the drive of the opening and closing actuator 131.

[0080] The aforementioned opening and closing rocker arm 133 includes two for each hatch, one end of which is connected to the opening and closing torque rod 132 via a connector, and the other end is connected to the hatch via the hatch joint 3, thereby enabling the hatch to be opened and closed under the action of the opening and closing torque rod 132.

[0081] The aforementioned fuselage connector 2 is fixedly connected to the fuselage 4, thereby greatly improving the stability of the opening and closing mechanism 13.

[0082] In this embodiment, the opening and closing mechanism 13 of the above-mentioned aircraft delivery device 1 is provided with two opening and closing actuators 131, two opening and closing torque rods 132, four opening and closing rocker arms 133, and two connecting joints 134. However, the present invention is not limited to this. The number of the above-mentioned opening and closing actuators 131, opening and closing torque rods 132, opening and closing rocker arms 133 and connecting joints 134 can also be adaptively designed according to the size and weight of the hatch, as long as it can facilitate the opening and closing of the hatch.

[0083] Next, refer to Figure 2 The opening and closing operation of the aircraft delivery device 1 of the present invention will be described.

[0084] (1) Opening operation: When it is necessary to open the hatch of the hatch mechanism 11, firstly, the latch mechanism 12 performs the unlocking operation. The latch actuator 121 of the latch mechanism 12 drives the latch torque rod 123 to rotate in the unlocking direction via the latch rocker arm 122, and the latch shaft 125 set on the latch torque rod 123 is released from the latch joint 126. Then, the opening and closing mechanism 13 performs the opening operation. After unlocking, the hatch opens under the gravity of the stored medium. The opening and closing mechanism 13 is triggered to operate. The opening and closing actuator 131 of the opening and closing mechanism 13 causes the opening and closing rocker arm 133 to rotate in the opening direction via the opening and closing torque rod 132, thereby opening the hatch to the fully open position.

[0085] (2) Closing operation: When it is necessary to close the hatch of the hatch mechanism 11, firstly, the opening and closing mechanism 13 performs the closing operation. The opening and closing actuator 131 of the opening and closing mechanism 13 rotates the opening and closing rocker arm 133 in the closing direction via the opening and closing torque rod 132, thereby raising the hatch to the fully closed position. Then, the latch mechanism 12 performs the latching operation. The latch actuator 121 of the latch mechanism 12 drives the latch torque rod 123 to rotate in the latching direction via the latch rocker arm 122. The latch shaft 125 set on the latch torque rod 123 engages with the latch joint 126, thereby keeping the hatch in the fully closed position.

[0086] (Technical effect)

[0087] The aircraft delivery device 1 of the present invention is generally arranged below the storage container of the delivery cabin, that is, outside the delivery cabin.

[0088] Specifically, in this invention, the latch mechanism is arranged below the storage container and between the left and right doors, the upper part containing the latch actuator is shielded and protected, and the opening and closing mechanism is arranged on the outer skin side of the door and is located on the outside of the aircraft fuselage.

[0089] Because the latching and opening / closing mechanisms are located outside the delivery compartment, they are isolated from the delivery medium, reducing the risk of corrosion from the medium. Furthermore, since the delivery mechanism is located outside the aircraft, it does not interfere with the delivery channel, allowing for the delivery of liquid, bagged, and solid particulate media. Additionally, its location outside the aircraft does not affect the effective storage volume of the storage container.

[0090] Furthermore, when the aircraft launch device 1 is in a completely closed state, the entire aircraft launch device 1 is connected to the fuselage via hinges.

[0091] In addition, such as Figure 2As shown, when the aircraft launch device 1 is in the fully closed state, it forms a roughly V-shaped structure, that is, the door body is at a certain angle relative to the horizontal plane. Specifically, the door body is tilted downward at a certain angle relative to the horizontal plane where the aircraft is located.

[0092] This structural design facilitates the rapid discharge of leaked delivery media, thereby reducing the impact of leaked media on the delivery device and the aircraft.

[0093] Furthermore, since the latch joint of the latch mechanism adopts an eccentric structure design, that is, an over-center design, in the initial stage of opening the hatch of the delivery device, opening the hatch requires overcoming the gravity of the delivery medium. In other words, the gravity of the delivery medium itself will cause the delivery hatch to tend to be closed, thereby greatly improving the stability when it is in the closed state.

[0094] The aircraft delivery device of the present invention can appropriately deliver liquid fire extinguishing medium, bagged fire extinguishing medium, pesticides, seeds, fertilizers and other items in the air. The delivery device opens by the gravity of the delivered medium and closes by the power of the mechanical system, thus possessing the advantages of watertightness and pressurized sealing.

[0095] When it is necessary to release liquid or other fluid media, the liquid or other fluid media can be stored in a specific container and the container can be stored in the release chamber. Since the aircraft release device of the present invention is located outside the release chamber, it is possible to avoid any impact on the operation of the release device from the bagged fire extinguishing medium, thereby enabling the appropriate release of the bagged fire extinguishing medium.

[0096] While the structure and working principle of the present invention have been described above in conjunction with preferred embodiments, those skilled in the art should recognize that the above examples are merely illustrative and do not constitute a limitation of the invention. Modifications and variations can be made to the invention within the spirit and scope of the claims, and all such modifications and variations will fall within the protection scope of the present invention.

Claims

1. An aircraft delivery device (1) is disposed outside the delivery compartment of an aircraft, the aircraft delivery device (1) comprising: A hatch mechanism (11) having a left hatch (111) and a right hatch (112) symmetrical to each other; A latch mechanism (12) is disposed between the left hatch (111) and the right hatch (112) and is used to fix the hatch mechanism (11) in a closed state; An opening and closing mechanism (13) is provided, which is used to actuate the opening and closing of the hatch mechanism (11). The latch mechanism (12) includes a latch shaft (125) disposed between latch shaft supports (124) and a latch joint (126) disposed on the door mechanism (11). When the hatch mechanism (11) is in the closed state, the latch pin (125) engages with the latch joint (126) to lock the hatch mechanism (11) in the closed state. When it is necessary to open the hatch mechanism (11), the latch pin (125) disengages from the latch joint (126) to release the lock of the hatch mechanism (11). The latch mechanism (12) further includes a latch actuator (121), a latch rocker arm (122), and a latch torque rod (123). The latch shaft (125) is fixedly installed on the latch torque rod (123). The latch actuator (121) drives the latch torque rod (123) to rotate around its own axis via the latch rocker arm (122) so as to lock and unlock the latch shaft (125) relative to the latch joint (126).

2. The aircraft delivery device as described in claim 1, characterized in that, Also includes: A sensor assembly (14) is arranged on the latch mechanism (12) and the door mechanism (11) and is used to monitor the latching status and unlocking status of the latch mechanism (12) and the opening and closing status of the door mechanism (11).

3. The aircraft delivery device as described in claim 1, characterized in that, Multiple latches (125) and latch joints (126) are provided corresponding to each other and are arranged along the length direction of the hatch of the hatch mechanism (11).

4. The aircraft delivery device as described in claim 1, characterized in that, The opening and closing mechanism (13) includes an opening and closing actuator (131), an opening and closing torque rod (132), an opening and closing rocker arm (133), and a connecting joint (134). The opening / closing actuator (131) is connected to the opening / closing torque rod (132) via the joint connector (134), and is connected to the opening / closing rocker arm (133) via the opening / closing torque rod (132). The other end of the opening / closing rocker arm (133) is connected to the hatch of the hatch mechanism (11). The opening and closing actuator (131) drives the opening and closing torque rod (132) to rotate around its own axis, and then drives the hatch to open and close via the opening and closing rocker arm (133).

5. The aircraft delivery device as described in claim 4, characterized in that, Multiple opening and closing rocker arms (133) are provided and are arranged along the length direction of the hatch of the hatch mechanism (11).

6. The aircraft delivery device as described in claim 1, characterized in that, The hatch mechanism (11) adopts an eccentric design in which the cross-sectional center of the latch joint (126) does not coincide with the cross-sectional center of the latch shaft (125), i.e., an over-center design.

7. The aircraft delivery device as described in claim 1, characterized in that, When the aircraft delivery device (1) is in a fully closed state, it forms a V-shaped structure, that is, the door of the door mechanism (11) is at a certain angle relative to the horizontal plane.

8. The aircraft delivery device as described in any one of claims 1 to 7, characterized in that, When it is necessary to open the hatch of the hatch mechanism (11), firstly, the latch mechanism (12) performs an unlocking operation to release the lock of the hatch mechanism (11), then, the medium is injected to push the hatch open, and the opening and closing mechanism (13) performs an opening operation to open the hatch of the hatch mechanism (11). When it is necessary to close the hatch of the hatch mechanism (11), firstly, the opening and closing mechanism (13) performs a closing operation to close the hatch of the hatch mechanism (11), and then the latch mechanism (12) performs a latching operation to lock the hatch mechanism (11) in the closed state.

9. An aircraft comprising the aircraft delivery device according to any one of claims 1 to 8.

Images