Aircraft launching device and aircraft comprising aircraft launching device

Abstract

An aircraft delivery device and an aircraft comprising the aircraft delivery device, the aircraft delivery device is arranged outside a delivery cabin of the aircraft, and the aircraft delivery device comprises: a cabin door mechanism having a left cabin door and a right cabin door which are symmetrical to each other; the latch mechanism is arranged between the left cabin door and the right cabin door and is used for fixing the cabin door mechanism in a closed state; and the opening and closing mechanism is used for actuating opening and closing of the cabin door mechanism. The aircraft throwing device is arranged outside the throwing cabin of the aircraft, so that the bad influence of to-be-thrown substances in the throwing cabin on the operation of the throwing mechanism can be avoided, and media such as liquid and the like can be properly thrown.

Description

Technical Field

[0001] The present 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 comprising the aircraft delivery device. Background Art

[0002] The aircraft delivery device is an important component of transport aircraft. It is mainly used to transport equipment and supplies from the air to designated locations. It is the main means of delivering these equipment and supplies to areas that need them.

[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 the delivery operation according to the characteristics of the items to be delivered.

[0004] After the drop operation, since the heavy mass of materials carried on the aircraft is dropped onto the ground, the weight center of gravity, i.e., the center of mass, of the aircraft before and after the drop operation will change greatly, which may affect the safe flight of the aircraft.

[0005] At this time, in order to improve the safety of the aircraft after the delivery operation, raising the flight altitude of the aircraft is an effective method. However, if the flight altitude of the aircraft is raised too much, the liquid may evaporate or blow away due to the influence of factors such as atmospheric pressure and airflow, and it may be impossible to properly deliver the fluid medium such as pesticides.

[0006] In order to properly release the liquid medium, in the existing aircraft release device, the main design scheme adopted is to arrange the aircraft release mechanism in the aircraft cabin, such as the door mechanism described in patents US4936389A (Fluid Dispenser For An Aircraft), CA1320188C (Fluid Dispenser for an Aircraft), CN115447780A (A solution for a water-dropping door of a fire-fighting aircraft), CN117163287A (A water-dropping door mechanism), CN112478129A (A water-dropping door for a fire-fighting aircraft) and CN112478129A (A aircraft release door), etc. There are also some implementation schemes in which the actuating mechanism of the release door is arranged in the aircraft cabin for releasing the liquid medium, such as in patent WO2012058677A9 (Pressure Assisted Var iab le F low Clean Throat Aircraft Resist ion The hatch door actuation mechanism recorded in the retardant Developer System).

[0007] However, the above technical solutions all arrange the delivery mechanism inside the aircraft cabin, specifically on the inner skin side of the cabin door. Due to the liquid properties of the delivered medium, the delivery mechanism is more easily corroded by the delivered medium, and the movement of the delivery mechanism becomes unsmooth due to the impact of the delivered medium. In addition, the above design solution can only deliver liquid media, and is not suitable for delivering bagged fire extinguishing media, seeds, fertilizers and other solid media.

[0008] In order to overcome the above technical problems, it is possible to consider arranging the aircraft launching mechanism on the wall panels in the aircraft cabin in the forward and rearward directions, but this design scheme has higher design requirements on the strength and rigidity of the aircraft wall panels.

[0009] For this type of technical solution, in order to ensure the opening and closing function requirements of the delivery device, it is necessary to reduce the area of ​​each delivery opening to reduce the load on the aircraft structure during the delivery process of a single delivery device, and in order to ensure the delivery efficiency, it is necessary to increase the number of delivery openings and delivery devices, which will make the overall structural design more complicated.

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

[0011] The present 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 liquid medium under the premise of ensuring the flight safety of the aircraft.

[0012] In order to achieve the purpose of the present disclosure, there is provided an aircraft delivery device, which is arranged outside the delivery compartment of the aircraft, and the aircraft delivery device comprises: a door mechanism, the door mechanism having a left door and a right door that are symmetrical to each other; a latch mechanism, the latch mechanism is arranged between the left door and the right door, and is used to fix the door mechanism in a closed state; and an opening and closing mechanism, the opening and closing mechanism is used to actuate the opening and closing of the door mechanism.

[0013] According to the above configuration, by arranging the aircraft delivery device outside the delivery chamber of the aircraft, it is possible to avoid the adverse effect of the material to be delivered in the delivery chamber on the operation of the delivery mechanism, and to appropriately deliver the medium such as liquid.

[0014] Preferably, it further comprises: a sensor assembly, wherein the sensor assembly is arranged on the latch mechanism and the door mechanism and is used to monitor the latching state, unlatching state of the latch mechanism and the opening and closing state of the door mechanism.

[0015] According to the above-mentioned structure, the sensor component monitors the latching state, unlatching state of the latch mechanism and the opening and closing state of the door mechanism, thereby preventing the door from being damaged when the latch mechanism is latched or the aircraft door from being opened accidentally.

[0016] Preferably, the latch mechanism includes a latch shaft arranged between latch shaft supports and a latch joint arranged on the hatch mechanism, when the hatch mechanism is in a closed state, the latch shaft engages with the latch joint to lock the hatch mechanism in a closed state, and when the hatch mechanism needs to be opened, the latch shaft disengages from the latch joint to release the lock of the hatch mechanism.

[0017] Preferably, the latch mechanism further comprises a latch actuator, a latch rocker arm and a latch torque rod, the latch shaft being fixedly mounted on the latch torque rod, the latch actuator driving the latched torque rod to rotate around its own axis via the latch rocker arm, so as to drive the latch shaft to lock and unlock relative to the latch joint.

[0018] According to the above-described configuration, by means of the latch shaft and the latch joint being arranged corresponding to each other, the latching and unlatching of the hatch mechanism can be realized with a simple structure, and the realization method is simple and the operation is convenient.

[0019] Preferably, the latch shafts are provided in plurality corresponding to the latch joints and are arranged along the length direction of the door of the door mechanism.

[0020] According to the above configuration, by providing a plurality of latch shafts and latch joints and arranging them along the longitudinal direction of the hatch, it is possible to increase the locking strength when the hatch mechanism is locked, that is, when latching.

[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 joint joint, the opening and closing actuator is connected to the opening and closing torque rod via the joint joint, and is connected 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, and then drives the hatch to open and close via the opening and closing rocker arm.

[0022] According to the above-mentioned structure, the opening and closing mechanism can realize the opening and closing of the hatch door through a simple structure, and the implementation method is simple and the operation is convenient.

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

[0024] According to the above-described structure, by providing a plurality of opening and closing rocker arms and arranging them along the length direction of the hatch, the hatch can be stably actuated to open and close, thereby ensuring the stability of the overall structure of the launching device.

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

[0026] According to the above-mentioned structure, through the eccentric design of the hatch mechanism, when the hatch needs to be closed, the gravity of the delivery medium, the rebound force of the seal, and the gravity of the hatch structure borne by the hatch can make the latch joint tend to latch, that is, lock, so as to reduce the risk of accidental opening of the hatch. In addition, in the initial stage of opening the delivery hatch, the latch mechanism needs to overcome the gravity of the delivery medium, the rebound force of the seal, and the gravity of the hatch structure until the latch joint moves to the center point. After passing the center point, the gravity of the delivery medium, the rebound force of the seal, and the gravity of the hatch structure help the delivery hatch to open.

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

[0028] According to the above-mentioned structure, it is possible to help quickly discharge the leaked delivery medium, thereby reducing the impact of the leaked medium on the delivery device and the aircraft.

[0029] Preferably, when the hatch of the hatch mechanism needs to be opened, first, the latch mechanism performs an unlatching operation to release the lock of the hatch mechanism, then, the medium is introduced to push the hatch open, and the opening and closing mechanism performs an opening operation to open the hatch of the hatch mechanism; when the hatch of the hatch mechanism needs to be closed, first, the opening and closing mechanism performs a closing operation to close the hatch of the hatch mechanism, and then, the latch mechanism performs a latching operation to lock the hatch mechanism in a closed state.

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

[0031] In addition, the present invention also provides an aircraft, which includes the aircraft launching device as described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] With reference to the above purposes, the technical features of the present invention are clearly described in the following technical scheme, and its advantages are obvious from the following detailed description with reference to the accompanying drawings, which show preferred embodiments of the present invention by way of example without limiting the scope of the inventive concept.

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

[0034] Figure 2 It is a schematic diagram of the three-dimensional structure of the aircraft launching device of the present invention. Explanation of symbols

[0035] 1 Aircraft delivery device; 11. Door mechanism; 111 left hatch; 112 right door; 12 Latch mechanism; 121 Latch actuator; 122 Latch rocker arm; 123 Latch torque rod; 124 latch shaft support; 125 Latch shaft; 126 Latch joint; 13. Opening and closing mechanism; 131 Opening and closing actuator; 132 Open and close torque rod; 133 Open and close rocker arm; 134 Union joint; 14 sensor components; 2 fuselage connectors; 3. Door connector; 4 Body. DETAILED DESCRIPTION

[0036] An embodiment of the present invention will now be described in detail, examples of which are shown in the accompanying drawings. Although the present invention is described in conjunction with exemplary embodiments, it should be appreciated that this specification is not intended to limit the present invention to the exemplary embodiments described below. On the contrary, the present invention is intended to cover not only the exemplary embodiments, but also various alternative forms, modifications, equivalent forms and other embodiments that may be included within the spirit and scope of the present invention as defined by the appended claims.

[0037] Below, refer to Figure 1 , the overall structure of the aircraft launching device 1 of the present invention is described. Figure 1 It is a schematic diagram showing the overall structure of the aircraft launching device 1 of the present invention.

[0038] like Figure 1 As shown, the aircraft launching device 1 of the present invention is arranged outside the launching compartment of the aircraft, and as a whole mainly comprises a door mechanism 11 , a latch mechanism 12 , an opening and closing mechanism 13 and a sensor assembly 14 .

[0039] The 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 to each other, and are combined to form a door for closing the launch bay of the aircraft.

[0040] The above-mentioned latch 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 launch bay is closed, so as to fix the door composed of the left door 111 and the right door 112 in a closed state, and to unlatch the left door 111 and the right door 112 of the door mechanism 11 when the aircraft's launch bay needs to be opened, so as to open the door composed of the left door 111 and the right door 112.

[0041] The above-mentioned opening and closing mechanism 13 is mainly used for respectively actuating the left door 111 and the right door 112 when the door of the door mechanism 11 needs to be opened, so as to open the door formed by the left door 111 and the right door 112, so as to release the liquid medium in the cabin, and when the door of the door mechanism 11 needs to be closed, respectively actuating the left door 111 and the right door 112, so as to close the door formed by the left door 111 and the right door 112.

[0042] The above-mentioned sensor components 14 are respectively arranged on the latch mechanism 12 and the left door 111 and the right door 112 of the door mechanism 11, and are mainly used to monitor the opening and closing states of the left door 111 and the right door 112 and the latching state of the latch mechanism 12, and transmit the monitoring results to the central control system of the aircraft to avoid the occurrence of adverse situations such as damage to the mechanism or accidental opening of the aircraft door when the latch mechanism 12 is latched and the cabin door is actuated.

[0043] Below, refer to Figure 2 , the specific structure of each part of the aircraft launching device 1 of the present invention is explained. Figure 2 It is a schematic diagram showing the three-dimensional structure of the aircraft launching device 1 of the present invention.

[0044] It should be noted that for the sake of illustration, Figure 2 The aircraft delivery device 1 shown in FIG. is described by reversing the entire device. Figure 2 The upper part of the picture belongs to the outer space of the launch cabin, that is, the lower part of the aircraft. Figure 2 The lower part belongs to the space inside the launch cabin, that is, above the aircraft. Therefore, the upper and lower parts described below are mainly relative to the upper and lower parts of the aircraft.

[0045] like Figure 2 As shown, the aircraft launching device 1 of the present invention as a whole mainly includes a door mechanism 11, a latch mechanism 12 and an opening and closing mechanism 13.

[0046] The door mechanism 11 includes a left door 111 and a right door 112 . The two doors are formed into a substantially rectangular shape and are independent of each other and open opposite to each other, thereby forming a door for closing the delivery compartment of the aircraft delivery device 1 .

[0047] The above-mentioned latch mechanism 12 is arranged below the storage container of the launch bay, and is mainly arranged between the left door 111 and the right door 112 of the door mechanism 11, and 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.

[0048] The above-mentioned latch actuator 121 includes two for the left door 111 and the right door 112, one end of which is connected to the fuselage joint 2, and the other end is connected to the latch rocker 122, and the latching and unlatching operations of the two doors are driven by the latch rocker 122.

[0049] The above-mentioned latch rocker arm 122 includes two for the left door 111 and the right door 112, one end of which is connected to the actuating 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.

[0050] The above-mentioned latch torque rod 123 includes two for the left door 111 and the right door 112. The length direction of the latch torque rod 123 is parallel to the long side direction of the door, and one end thereof is connected to the latch rocker arm 122, and the latch torque rod 123 is installed by passing through multiple latch shaft supports 124 and multiple latch shafts 125.

[0051] The latch shaft support 124 and the latch shaft 125 are arranged between the left cabin door 111 and the right cabin door 112. The latch shaft support 124 is formed with two mounting holes for the latch torque rod 123 to pass through and be installed, and two latch shafts 125 are sandwiched and installed between the two latch shaft supports 124. The two latch shafts 125 are respectively arranged for the left cabin door 111 and the right cabin door 112, and a locking mechanism is formed on the latch shaft 125 for locking with the latch joint 126 arranged on the cabin door.

[0052] The latch joint 126 is arranged on the cabin door and is arranged corresponding to the latch shaft 125. The latch shaft 125 is fixedly installed on the latch torque rod 123 through a coupling or a connecting joint, and rotates under the drive of the latch torque rod 123, so as to engage with the latch joint 126, that is, latch, or separate from the latch joint 126, that is, unlatch.

[0053] In this embodiment, the door mechanism 11 of the aircraft launching 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.

[0054] The number of the above-mentioned latch actuators 121, latch rocker arms 122 and latch torque rods 123 is generally fixed, with two provided for the left door 111 and the right door 112 respectively. However, the above-mentioned latch shaft support 124, latch shaft 125 and latch joint 126 can be appropriately arranged according to the length of the door and the latch torque rod. It is best to arrange the latch shaft 125 and the latch joint 126 evenly along the length direction of the door.

[0055] In addition, the latch joint 126 of the hatch mechanism 11 is designed to be eccentric, that is, the cross-sectional center of the latch joint 126 does not coincide with the cross-sectional center of the latch shaft 125 .

[0056] In this way, through the eccentric design of the latch joint, the latch joint can tend to latch when the hatch needs to be closed, thereby reducing the risk of accidental unlatching of the launch hatch.

[0057] The 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 joint joint 134 .

[0058] The opening and closing actuator 131 includes two for the left door 111 and the right door 112 , one end of which is connected to the fuselage joint 2 , and the other end of which is connected to the opening and closing torque rod 132 via a joint joint 134 .

[0059] The above-mentioned opening and closing torque rod 132 is formed so that its length direction is approximately orthogonal to the length direction of the opening and closing actuator 131. The above-mentioned opening and closing torque rod 132 is connected to the fuselage joint 2 and the opening and closing rocker arm 133 via connecting parts at both ends thereof, and is connected to the actuating rod of the opening and closing actuator 131 via a joint joint 134 at an approximately middle position, thereby being able to rotate around its own axis driven by the opening and closing actuator 131.

[0060] The above-mentioned opening and closing rocker arms 133 include two for each cabin door, 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 cabin door via a cabin door joint 3, thereby enabling the cabin door to be opened and closed under the drive of the opening and closing torque rod 132.

[0061] The fuselage joint 2 is fixedly connected to the fuselage 4 , thereby greatly improving the stability of the opening and closing mechanism 13 .

[0062] In this embodiment, the opening and closing mechanism 13 of the above-mentioned aircraft launching 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 joint joints 134, but 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 joint joints 134 can also be adaptively designed according to the size and weight of the cabin door, as long as the cabin door can be easily opened and closed.

[0063] Next, refer to Figure 2 , the opening and closing operations of the aircraft launching device 1 of the present invention are explained.

[0064] (1) Opening operation: When the door of the door mechanism 11 needs to be opened, first, the latch mechanism 12 performs an unlatching operation, and the latch actuator 121 of the latch mechanism 12 drives the latch torque rod 123 to rotate in the unlatching direction via the latch rocker arm 122, and the engagement between the latch shaft 125 and the latch joint 126 provided on the latch torque rod 123 is released; then, the opening and closing mechanism 13 performs an opening operation. After unlatching, the door opens under the action of the gravity of the stored medium, and 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 door to a fully open position.

[0065] (2) Closing operation: When the hatch of the door mechanism 11 needs to be closed, first, the opening and closing mechanism 13 performs a closing operation, and 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 closing direction via the opening and closing torque rod 132, thereby lifting the hatch to the fully closed position; then, the latch mechanism 12 performs a latching operation, and the latch actuator 121 of the latch mechanism 12 drives the latch torque rod 123 to rotate in the upward latching direction via the latch rocker arm 122, and the latch shaft 125 provided on the latch torque rod 123 engages with the latch joint 126, thereby keeping the hatch in the fully closed position. (Technical Effect)

[0066] The aircraft launching device 1 of the present invention is arranged as a whole below the storage container of the launching cabin, that is, outside the launching cabin.

[0067] Specifically, in the present invention, the latch mechanism is arranged below the storage container and between the left and right doors, the upper part including 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 outside the fuselage of the aircraft.

[0068] Since the latch mechanism and the opening and closing mechanism are arranged outside the delivery cabin, the latch mechanism and the opening and closing mechanism are isolated from the delivery medium, which can reduce the risk of the delivery mechanism being corroded by the delivery medium, and since the delivery mechanism is arranged outside the aircraft, the delivery mechanism will not affect the delivery channel, and can be compatible with the delivery of liquid media, bag-shaped media and solid particle-shaped media. In addition, since the delivery mechanism is arranged outside the aircraft, it will not affect the effective storage volume of the storage container.

[0069] In addition, when the aircraft launching device 1 is in a fully closed state, the entire aircraft launching device 1 is connected to the fuselage via a hinge.

[0070] In addition, if Figure 2 As shown, the aircraft launching device 1 forms a roughly V-shaped structure when in a fully closed state, 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.

[0071] This structural design is conducive to quickly discharging the leaked delivery medium, thereby reducing the impact of the leaked medium on the delivery device and the aircraft.

[0072] In addition, since the latch joint of the latch mechanism adopts an eccentric structural design, that is, an over-center design, in the initial stage of opening the hatch of the delivery device, it is necessary to overcome the gravity from the delivery medium to open the hatch. In other words, the gravity of the delivery medium itself will make the delivery hatch tend to become a closed state, thereby greatly improving the stability when in the closed state.

[0073] Through the aircraft delivery device of the present invention, liquid fire extinguishing media, bagged fire extinguishing media, pesticides, seeds, fertilizers and other items can be appropriately delivered in the air, and the delivery device opens by relying on the gravity of the delivered medium and closes by the power of the mechanical system, and can have the performance advantages of watertightness and pressurized sealing.

[0074] 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 placed in a release compartment. Since the aircraft release device of the present invention is arranged outside the release compartment, any influence on the operation of the release device caused by the bagged fire extinguishing medium can be avoided, so that the bagged fire extinguishing medium can be properly released.

[0075] Although the structure and working principle of the present invention are described above in combination with the preferred embodiments, those skilled in the art should recognize that the above examples are only for illustration and do not constitute a limitation of the present invention. The present invention can be modified and varied within the spirit of the claims, and these modifications and variations will fall within the protection scope of the present invention.

Claims

1. An aircraft delivery device (1), the aircraft delivery device (1) being arranged outside a delivery compartment of an aircraft, the aircraft delivery device (1) comprising: A door mechanism (11), the door mechanism (11) comprising a left door (111) and a right door (112) that are symmetrical to each other; a latch mechanism (12), the latch mechanism (12) being arranged between the left cabin door (111) and the right cabin door (112) and being used to fix the cabin door mechanism (11) in a closed state; An opening and closing mechanism (13), wherein the opening and closing mechanism (13) is used to actuate the opening and closing of the hatch mechanism (11).

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

3. The aircraft delivery device (1) according to claim 1, characterized in that: The latch mechanism (12) comprises a latch shaft (125) arranged between latch shaft supports (124) and a latch joint (126) arranged on the door mechanism (11). When the hatch mechanism (11) is in a closed state, the latch shaft (125) engages with the latch joint (126) to lock the hatch mechanism (11) in the closed state. When the hatch mechanism (11) needs to be opened, the latch shaft (125) and the latch joint (126) are released from engagement to release the lock of the hatch mechanism (11).

4. The aircraft delivery device (1) according to claim 3, characterized in that: The latch mechanism (12) further comprises a latch actuator (121), a latch rocker arm (122) and a latch torque rod (123). The latch shaft (125) is fixedly mounted on the latch torque rod (123), and 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 drive the latch shaft (125) to lock and unlock relative to the latch joint (126).

5. The aircraft delivery device (1) according to claim 4, characterized in that: The latch shafts (125) and the latch joints (126) are arranged in plurality corresponding to each other and are arranged along the length direction of the door of the door mechanism (11).

6. The aircraft delivery device (1) according to claim 1, characterized in that: The opening and closing mechanism (13) comprises an opening and closing actuator (131), an opening and closing torque rod (132), an opening and closing rocker arm (133) and a joint joint (134). The opening and closing actuator (131) is connected to the opening and closing torque rod (132) via the joint joint (134), and is connected to the opening and closing rocker arm (133) via the opening and closing torque rod (132); the other end of the opening and closing rocker arm (133) is connected to the door of the door mechanism (11). The opening and closing actuator (131) drives the opening and closing torque rod (132) to rotate around its own axis, thereby driving the cabin door to open and close via the opening and closing rocker arm (133).

7. The aircraft delivery device (1) according to claim 6, characterized in that: The opening and closing rocker arms (133) are provided in plurality and are arranged along the length direction of the door of the door mechanism (11).

8. The aircraft delivery device (1) according to claim 4, 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), that is, an over-center design.

9. The aircraft delivery device (1) according to claim 1, characterized in that: The aircraft launching device (1) forms a V-shaped structure when in a fully closed state, that is, the door of the door mechanism (11) forms a certain angle with respect to the horizontal plane.

10. The aircraft delivery device (1) according to any one of claims 1 to 9, characterized in that: When the hatch of the hatch mechanism (11) needs to be opened, first, the latch mechanism (12) performs an unlocking operation to release the lock of the hatch mechanism (11), then, a medium is introduced to push the hatch to open, and the opening and closing mechanism (13) performs an opening operation to open the hatch of the hatch mechanism (11); When the hatch of the hatch mechanism (11) needs to be closed, first, 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 a closed state.

11. An aircraft, comprising the aircraft launching device (1) according to any one of claims 1 to 10.

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