Five-door linked transport category aircraft rear cargo door

Abstract

The application belongs to the field of machine body structure design, and particularly relates to a five-door linkage rear cargo door of a transport aircraft. The rear cargo door comprises a ramp assembly, a sealed door assembly, a middle door and two side doors. The ramp assembly comprises a ramp body which is hinged to the belly of the fuselage through a first hinge and is driven to deflect around the front end by a ramp driving mechanism. The sealed door assembly comprises a sealed door body which is hinged to the top frame on the top of the fuselage through a second hinge and is driven to deflect around the top end by a sealed door driving mechanism. The middle door and the two side doors are located behind the sealed door assembly, and the middle door is located between the two side doors. In the opening process, the middle door is driven to deflect its body towards the inside of the fuselage by a driving mechanism, and the two side doors are driven to deflect their bodies towards the two sides outside the fuselage by a driving mechanism. The application can obtain a large-size, high-load air transport, air drop and air landing passage.

Description

Technical Field

[0001] This application belongs to the field of airframe structure design, specifically relating to a five-door linkage rear cargo door for transport aircraft. Background Technology

[0002] Large transport aircraft are typically equipped with a rear cargo door to enable the airlift, airdrop, and airdrop of large, heavy-duty equipment and cargo. For such large transport aircraft requiring a rear cargo door, the fuselage shape design must consider many factors, such as the need to reserve sufficient height for structural components to bear loads, the requirement for a large clear passage for cargo entry and exit, and the composition of the rear cargo door and its position when closed or open.

[0003] Existing rear cargo doors typically consist of two doors, one in front and one behind. The front door opens outwards from the fuselage, while the rear door opens inwards. On the one hand, when the rear cargo door is closed, it serves as a structure that bears the airtight pressurization, requiring consideration of both structural load-bearing capacity and door passage size requirements. On the other hand, the rear door moves inside the fuselage, necessitating a larger fuselage width, and the fuselage cannot be designed with the minimum airflow resistance in mind. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a five-door linked rear cargo door for transport aircraft. While ensuring reasonable loading and unloading passages and weight, it allows the rear fuselage to be designed with minimal drag during cruise, which is particularly advantageous for aircraft equipped with engines that have relatively weak power and high fuel consumption.

[0005] The five-door linked rear cargo door of the transport aircraft provided in this application mainly includes:

[0006] The inclined platform assembly includes an inclined platform body, the front end of which is hinged to the fuselage belly via a first hinge, the inclined platform body is driven to deflect around the front end by an inclined platform drive mechanism, and the inclined platform body has multiple first locking shafts on both sides for connecting to the side beams on both sides of the fuselage when the inclined platform body is in the closed state.

[0007] The sealed door assembly includes a sealed door body. The top of the sealed door body is hinged to the bulkhead on the top of the fuselage via a second hinge. The sealed door body is driven to deflect around the top by a sealed door drive mechanism. The bottom of the sealed door body has a locking claw. When the sealed door assembly is in the closed state, the second locking shaft of the ramp assembly can be inserted into the slot of the locking claw after the ramp assembly is closed. The ramp body and the sealed door body together constitute the rear sealing structure of the pressurized cargo compartment of the aircraft in the closed state.

[0008] The center hatch and the two side hatches are located behind the sealed hatch assembly. The center hatch is located between the two side hatches. During the opening process, the center hatch is driven by a drive mechanism to deflect its body inward into the fuselage, and the two side hatches are driven by a drive mechanism to deflect their bodies outward to the sides of the fuselage.

[0009] Preferably, the first locking shaft of the ramp assembly is locked by a ramp locking mechanism distributed under the side beams on both sides of the machine body. The ramp locking mechanism includes multiple ramp locking hooks, each ramp locking hook is hinged to a ramp locking hook support, and multiple ramp locking hooks are connected in series by a torsion shaft. The torsion shaft is driven to rotate by a ramp locking hook electric drive device installed at the end of the torsion shaft, so as to drive each ramp locking hook to hook each first locking shaft on both sides of the ramp body.

[0010] Preferably, the inclined platform drive mechanism includes a hydraulic actuator, the cylinder of which is connected to a first support on the machine body beam via a universal joint, and the piston rod of which is hinged to a second support on the inclined platform body.

[0011] Preferably, the inclined platform assembly further includes an airdrop lever with multiple through holes. One end of the airdrop lever is hinged to a third support on the inclined platform body, and the other end slides in a fourth support on the side beam of the machine. After the inclined platform body is opened to a set angle, it is limited by a limiting ball pre-installed in the corresponding through hole on the airdrop lever and locked on the fourth support, thereby locking the inclined platform body at the set angle position.

[0012] Preferably, the sealed hatch drive mechanism includes two helical actuators connected by a drive shaft. An electric drive reduction assembly is provided on the drive shaft. The helical actuators drive the drive rocker arm and the sealed hatch drive rocker arm to deflect through the drive shaft, thereby driving the sealed hatch body to switch from a closed state to an open state.

[0013] Preferably, the sealed hatch assembly further includes a sealed hatch upper lock, which includes an electric lock device and a lock ring. The lock ring is installed on the left and right sides of the bottom end of the sealed hatch body, and the electric lock device is fixed on the fuselage frame. It is used to connect with the lock ring to fix the sealed hatch body when the sealed hatch body is in the open state.

[0014] Preferably, the middle cabin door includes a middle cabin door body, the rear end of which is hinged to the tail bulkhead of the fuselage via a third hinge. The middle cabin door body is driven to deflect around the rear end by a middle cabin door drive mechanism. Middle cabin door docking lock mechanisms are provided on both sides of the middle cabin door body for interconnecting with the side cabin door lock rings on the side cabin doors, which are also in the closed state, when the middle cabin door is in the closed state.

[0015] Preferably, the middle cabin door also includes a middle cabin door upper locking device and an upper locking ring. The middle cabin door upper locking device is installed on the fuselage bulkhead, and the upper locking ring is located on the middle cabin door body. After the middle cabin door body is opened to the correct position, the upper locking ring on the middle cabin door body is locked in the open state by the middle cabin door upper locking device.

[0016] Preferably, the side hatch includes a left hatch body and a right hatch body, each hatch body is driven to deflect by a side hatch drive device, the side hatch drive device includes a side hatch drive shaft, each hatch body is connected to the side hatch drive shaft through multiple rocker arms, and the side hatch drive shaft is connected to and driven to rotate by an electric drive reduction device.

[0017] This application enables the creation of large-size, high-load airlift and airdrop drop routes, while also allowing for a more optimized aerodynamic drag design for the rear fuselage. Attached Figure Description

[0018] Figure 1 This is a side view of the rear cargo door in the closed state of a preferred embodiment of the five-door linkage rear cargo door of a transport aircraft according to this application.

[0019] Figure 2 This application Figure 1 The diagram shows the rear cargo door of the embodiment being opened to the ground of the inclined platform.

[0020] Figure 3 This application Figure 1 The diagram shows the rear cargo door of the embodiment opened to the horizontal position of the ramp.

[0021] Figure 4 This application Figure 1 The illustrated embodiment shows an axonometric view of the rear cargo door in the open position, viewed from the right rear of the aircraft.

[0022] Figure 5 This is a schematic diagram of the rear cargo door's inclined platform locking mechanism.

[0023] Figure 6a This is a schematic diagram of the inclined plane drive mechanism.

[0024] Figure 6b yes Figure 6a The diagram shows the inclined plane drive mechanism connected to the first support at point I.

[0025] Figure 6c yes Figure 6a The diagram shows the connection between the inclined platform drive mechanism and the second support at point II.

[0026] Figure 7a This is a schematic diagram of the airdrop lever structure.

[0027] Figure 7b yes Figure 7aThe diagram shows the connection between the airdrop lever and the fourth support at point III.

[0028] Figure 7c yes Figure 7a The diagram shows the connection between the airdrop lever and the third support at point IV.

[0029] Figure 8 This application Figure 1 Rear view of the sealed compartment door in the closed state of the embodiment shown.

[0030] Figure 9 This is a schematic diagram showing the connection between the sealed compartment door and the upper lock of the sealed compartment door when the sealed compartment door is open.

[0031] Figure 10a yes Figure 8 The diagram shows the positional relationship between the sealed hatch at point V and the second locking shaft on the inclined platform when the hatch is closed.

[0032] Figure 10b yes Figure 8 The diagram shows the positional relationship between the sealed hatch at point VI and the second locking shaft on the inclined platform when the hatch is closed.

[0033] Figure 11 This application Figure 1 A schematic diagram of the structure of the middle cabin door in the embodiment shown in the closed state.

[0034] Figure 12 yes Figure 11 The diagram shows the connection between the main body of the middle cabin door and the fuselage at point VII.

[0035] Figure 13 yes Figure 11 The diagram shows the connection between the main body of the middle cabin door and the middle cabin door drive mechanism at point VIII.

[0036] Figure 14 This is a schematic diagram showing the connection between the middle cabin door drive mechanism and the fuselage.

[0037] Figure 15 This application Figure 1 A schematic diagram of the side hatch structure of the embodiment shown.

[0038] Among them, 1-sloping platform assembly, 2-sealed hatch assembly, 3-middle hatch, 4-side hatch, 5-sloping platform drive mechanism, 6-airdrop lever, 7-first hinge, 8-middle hatch upper lock device, 9-middle hatch drive mechanism, 10-third hinge, 11-sealed hatch upper lock, 12-sloping platform body, 13-sloping platform lock mechanism, 14-fuselage, 15-first lock shaft, 16-hydraulic actuator, 17-universal joint, 18-first support, 19-second support, 20-sloping platform lock hook, 21-sloping platform lock hook support, 22-torsion shaft, 23-sloping platform lock hook electric drive device, 24-third support, 25-fourth support, 26-limit ball, 27-sealed hatch body, 28-sealed hatch drive mechanism Mechanism, 29-Second hinge, 30-Locking claw, 31-Second locking shaft, 32-Electric drive reduction assembly, 33-Drive shaft, 34-Screw actuator, 35-Driver drive shaft, 36-Driver drive rocker arm, 37-Sealed hatch drive rocker arm, 38-Electric lock device, 39-Locking ring, 40-Middle hatch body, 41-Middle hatch docking lock mechanism, 42-Side hatch locking ring, 43-Upper locking ring, 44-Second hydraulic actuator cylinder, 45-Cylinder body, 46-Piston rod, 47-Second universal joint, 48-Side hatch drive device, 49-Support joint, 50-Left hatch body, 51-Right hatch body, 52-Electric drive reduction device, 53-Side hatch drive shaft, 54-Rocker arm. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0040] For ease of description, this application follows Figure 1 The front and rear ends of each structure are described in the forward and backward directions shown, with the front end near the nose and the rear end near the tail. Figure 1 The top and bottom of each structure are shown in the vertical direction, with the top near the back of the aircraft and the bottom near the belly.

[0041] This application provides a five-door linked rear cargo door for a transport aircraft, such as... Figures 1-15 As shown, it mainly includes:

[0042] The inclined platform assembly 1 includes an inclined platform body 12. The front end of the inclined platform body 12 is hinged to the fuselage belly via a first hinge 7. The inclined platform body 12 is driven to deflect around the front end by an inclined platform drive mechanism 5. The inclined platform body 12 has multiple first locking shafts 15 on both sides for connecting to the side beams on both sides of the fuselage 14 when the inclined platform body 12 is in the closed state.

[0043] The sealed door assembly 2 includes a sealed door body 27. The top of the sealed door body 27 is hinged to the bulkhead on the top of the fuselage 14 via a second hinge 29. The sealed door body 27 is driven to deflect around the top by a sealed door drive mechanism 28. The bottom of the sealed door body 27 has a locking claw 30. When the sealed door assembly 2 is in the closed state, the second locking shaft 31 of the ramp assembly 1 can be inserted into the slot of the locking claw 30 after the ramp assembly 1 is closed. The ramp body 12 and the sealed door body 27 together constitute the rear sealing structure of the pressurized cargo compartment of the aircraft in the closed state.

[0044] The middle cabin door 3 and the two side cabin doors 4 are located after the sealed cabin door assembly 2. The middle cabin door 3 is located between the two side cabin doors 4. During the opening process, the middle cabin door 3 is driven by the drive mechanism to deflect its body into the fuselage, and the two side cabin doors 4 are driven by the drive mechanism to deflect their bodies to the sides of the fuselage.

[0045] This application utilizes a five-door linkage rear cargo door system comprised of a ramp assembly 1, a sealed door assembly 2, a central cargo door 3, and two side cargo doors 4. Following a predetermined control sequence, the rear cargo door opens and closes on the ground and in the air to achieve its intended function. Specifically, the ramp assembly 1 and the sealed door assembly 2, when closed, together form the rear sealing structure of the aircraft's pressurized cargo hold, bearing the internal airtight pressure. The central cargo door 3 and the two side cargo doors 4 no longer need to consider the cargo hold pressure load, allowing for more design options regarding the thickness of each door and their connection structure. Furthermore, the side-by-side design of the central cargo door 3 and the two side cargo doors 4 ensures a spacious loading and unloading passageway and eliminates the need for a large rotation space in the rear fuselage due to the deflection of a single, wider rear door into the fuselage. Only space needs to be reserved for the deflection of the central cargo door 3 into the fuselage. This provides more design margin for the aerodynamic design of the aircraft's rear fuselage, ensuring that the aircraft's aerodynamic shape is designed to minimize cruise drag. On the other hand, after the rear cargo door of this application is opened, it can provide a certain amount of airflow shielding for paratroopers jumping from the inclined platform, ensuring their safety upon exiting the aircraft, and also ensuring the directional stability of the aircraft during airdrop.

[0046] refer to Figures 1-4The ramp body 12 is a closed box-type structure, with the upper surface being the cargo floor and the lower surface being the outer skin. It is part of the aircraft's shape and is equipped with a construction and maintenance access cover. The ramp body 12 is mainly made of high-strength aluminum alloy, while the joints subjected to concentrated forces are made of titanium alloy and alloy steel, depending on the load conditions. Four sets of first hinges 7 are symmetrically arranged at the front end of the ramp body 12. These first hinges 7 can connect the ramp body 12 to the corresponding end frame of the fuselage 14, and the ramp body 12 can rotate around the first hinges 7 based on the ramp drive mechanism 5. The four sets of first hinges 7 are located on the four longitudinal load-bearing beams of the ramp body 12. Eight first locking shafts 15 are provided on each side of the ramp body 12, which cooperate with the corresponding ramp locking hooks 20 on the fuselage side beams to lock the ramp body 12 when it is closed.

[0047] Specifically, such as Figure 5 As shown, in some optional embodiments, the first locking shaft 15 of the ramp assembly 1 is locked by a ramp locking mechanism 13 distributed under the side beams on both sides of the body 14. The ramp locking mechanism 13 includes a plurality of ramp locking hooks 20, each ramp locking hook 20 is hinged to a ramp locking hook support 21, and the plurality of ramp locking hooks 20 are connected in series by a torsion shaft 22. The torsion shaft 22 is driven to rotate by a ramp locking hook electric drive device 23 installed at the end of the torsion shaft 22, so as to drive each ramp locking hook 20 to hook each first locking shaft 15 on both sides of the ramp body 12.

[0048] In this embodiment, the ramp locking mechanism 13 is symmetrically arranged on the rear engine side beam structure corresponding to the positions on both sides of the ramp. Multiple ramp locking hooks 20 are connected to the drive element of the ramp locking hook electric drive device 23 via a torsion shaft 22 for locking and unlocking. The ramp locking hook support 21 is bolted to the lower surface and side of the side beam, serving as a support and force transmission structure for the ramp locking hook and the torsion shaft, and forming a rotary pair with the ramp locking hook and the torsion shaft.

[0049] In some alternative embodiments, the inclined platform drive mechanism 5 includes a hydraulic actuator 16, the cylinder of which is connected to a first support 18 on the machine body beam via a universal joint 17, and the piston rod of the hydraulic actuator 16 is hinged to a second support 19 on the inclined platform body 12.

[0050] In this embodiment, reference Figures 6a-6c The first support 18 is connected to the machine body beam as a whole by bolt fasteners. Using this as the point of action, the piston rod of the hydraulic actuator 16 extends and retracts, driving the inclined platform body 12 to move.

[0051] In some optional embodiments, the inclined platform assembly 1 further includes an airdrop lever 6. The airdrop lever 6 is provided with multiple through holes. One end of the airdrop lever 6 is hinged to the third support 24 on the inclined platform body 12, and the other end slides in the fourth support 25 on the side beam of the machine. After the inclined platform body 12 is opened to a set angle, it is limited by the limiting ball 26 pre-installed in the corresponding through hole on the airdrop lever 6 and placed on the fourth support 25, thereby locking the inclined platform body at the set angle position.

[0052] like Figures 7a-7c One airdrop lever 6 is installed on each side of the rear end of the inclined platform body 12. When limit balls are installed in different through holes on the airdrop lever 6, the inclined platform body 12 can be at different tilt angles, such as... Figure 1 The deflection angle shown is to Figure 2 In any of the deflection angles shown, in the alternative embodiment, it is only necessary to make the inclined platform body 12 at any of the deflection angles shown. Figure 3 The deflection angle shown is to Figure 2 The multiple deflection angles shown are, in other words, these through holes are set to correspond to multiple tilting states that make the inclined platform body 12 horizontal or tilted downward at different angles during the opening process.

[0053] It is understandable that the limiting ball 26 can be of various structural forms, such as two hemispherical structures connected by bolts, as long as it can be detachably installed onto different through holes of the airdrop lever 6. In this embodiment, the theoretical position of the limiting ball 26 in the through hole is calculated in advance based on the expected tilt angle of the ramp body 12, and the limiting ball 26 is installed at the through hole. Then, the ramp body 12 is driven to deflect until the limiting ball 26 contacts the fourth support 25, thereby fixing the ramp body 12 at the set angle position. In this embodiment, the fourth support 25 is connected to the rear fuselage as a whole using bolts or other fasteners.

[0054] refer to Figure 1 , Figure 2 and Figure 8 , Figure 1 This is a schematic diagram showing the closed state of the sealed hatch assembly 2. Figure 2 This is a schematic diagram showing the open state of the sealed hatch assembly 2. Figure 8 This is a structural schematic diagram of the sealed hatch assembly 2. The sealed hatch body 27 of the sealed hatch assembly 2 is located in front of the rear end of the inclined platform body 12, as shown below. Figure 1 , Figure 10a and Figure 10b As shown, this allows the sealed cargo door body 27, once closed, to lock the second locking shaft 31 on the ramp body, which is also in the closed state, via the locking claw 30, thus forming the rear area of ​​the aircraft pressurized cargo hold.

[0055] like Figure 8As shown, the top of the sealed hatch body 27 is connected to the rear fuselage bulkhead via eight second hinges 29. When the sealed hatch body 27 is closed, it is on the same plane as the bulkhead it is connected to. When the sealed hatch body 27 is opened rearward to the horizontal position, as shown... Figure 2 or Figure 3 As shown, it is locked by the upper lock 11 of the sealed hatch at the corresponding position on the rear fuselage. In some optional embodiments, such as Figure 9 As shown, the upper lock 11 of the sealed hatch includes an electric lock device 38 and a lock ring 39. The lock ring 39 is installed on the left and right sides of the bottom end of the sealed hatch body 27. The electric lock device 38 is fixed on the fuselage frame and is used to connect with the lock ring 39 to fix the sealed hatch body 27 when the sealed hatch body 27 is in the open state.

[0056] The sealed hatch body 27 is deflected by the sealed hatch drive mechanism 28. In some optional embodiments, the sealed hatch drive mechanism 28 includes two helical actuators 34 connected by a drive shaft 33. An electric drive reduction assembly 32 is provided on the drive shaft 33. The helical actuators 34 drive the drive rocker arm 36 and the sealed hatch drive rocker arm 37 to deflect through the drive shaft 35, so as to drive the sealed hatch body 27 to switch from the closed state to the open state.

[0057] like Figures 1-4 As shown, the center hatch 3 and the two side hatches are located at the rear of the aft cargo door area. In some alternative embodiments, such as... Figure 11 As shown, the middle cabin door 3 includes a middle cabin door body 40. The rear end of the middle cabin door body 40 is hinged to the tail bulkhead of the fuselage via a third hinge 10. The middle cabin door body 40 is driven to deflect around the rear end by a middle cabin door drive mechanism 9. Middle cabin door docking lock mechanisms 41 are provided on both sides of the middle cabin door body 40, which are used to connect with the side cabin door lock rings 42 on the side cabin door 4, which are also closed, when the middle cabin door 3 is in the closed state.

[0058] like Figure 12 As shown, the rear of the middle hatch body is connected to the aft fuselage bulkhead via two symmetrically arranged third hinges 10. The middle hatch body 40 can be opened or closed by the middle hatch drive mechanism 9, revolving around the third hinges 10. One part of the third hinge 10 is connected to the middle hatch body 40 as a whole, and the other part of the third hinge 10 is connected to the corresponding bulkhead structure of the aft fuselage as a whole via fasteners. The two parts of the hinge form a rotatable pair via a hinge shaft. When the middle hatch body 40 is open, it retracts into the fuselage. When the middle hatch body 40 is closed, it is locked in the closed position by the middle hatch docking locking mechanism 41, along with the two side hatches in the closed position. Figure 11 and Figure 15As shown, the middle cabin door docking lock mechanism 41 is installed on the middle cabin door body 40, with 4 sets on each side. The middle cabin door docking lock mechanism 41 includes an electric cylinder, a locking hook mechanism, etc. The middle cabin door closes to the position first, and then, after the side cabin doors close to the position, the side cabin door locking ring 42 is locked in the closed position by the locking hook of the middle cabin door docking lock mechanism 41.

[0059] like Figure 13 and Figure 14 As shown, the mid-cabin door drive mechanism 9, which drives the mid-cabin door body 40 to deflect, is similar to the ramp drive mechanism 5, which drives the ramp body to deflect; both are actuator cylinder structures. Specifically, the mid-cabin door drive mechanism 9 includes two symmetrically arranged second hydraulic actuator cylinders 44. The cylinder body 45 of the second hydraulic actuator cylinder 44 is connected to the corresponding bulkhead of the aft fuselage 14 via a second universal joint 47, and the piston rod 46 of the second hydraulic actuator cylinder 44 is connected to the mid-cabin door body 40 via a hinge.

[0060] When the middle cabin door body 40 of this application is opened, it also needs to be locked in the open position by the upper lock, as per the reference. Figure 1 In some optional embodiments, the middle cabin door 3 also includes a middle cabin door upper locking device 8 and an upper locking ring 43. The middle cabin door upper locking device 8 is installed on the fuselage bulkhead, and the upper locking ring 43 is located on the middle cabin door body 40. After the middle cabin door body 40 is opened to the position, the upper locking ring 43 on the middle cabin door body 40 is locked in the open state by the middle cabin door upper locking device 8.

[0061] In this embodiment, the upper locking device 8 of the middle cabin door is similar or the same as the upper locking device 11 of the sealed cabin door. There are two of them arranged symmetrically and installed on the corresponding bulkhead of the fuselage 14.

[0062] like Figure 4 and Figure 15 As shown, the side doors 4 are symmetrically arranged with respect to the aircraft's plane of symmetry. In some alternative embodiments, the side doors 4 include a left door body 50 and a right door body 51. Each door body is driven to deflect by a side door drive device 48, which includes a side door drive shaft 53. Each door body is connected to the side door drive shaft 53 via multiple rocker arms 54. The side door drive shaft 53 is driven to rotate by an electric drive reduction gear 52.

[0063] In this embodiment, the left and right side hatch bodies are supported by support joints 49 installed on the corresponding side wall structures of the rear fuselage. The side hatch drive shaft 53 and rocker arm 54 are connected to each side hatch body as a whole and rotate together to open or close the side hatches. Here, the electric drive reduction device 52 refers to an integrated component including an electric motor or cylinder, a reduction gear, a screw drive, and a mechanism linkage, which has the function of outputting rotational torque or linear motion. Similarly, the electric components such as the inclined platform lock hook electric drive device 23, the electric drive reduction assembly 32, and the electric lock device 38 of this application are similar and will not be described in detail further.

[0064] The hinges described in the above embodiments typically consist of a single lug, two lugs, and a bolt. The single lug and two lugs are respectively fixed to two mutually rotating components, and the bolt acts as a pivot.

[0065] The opening sequence of each door component in the five-door linked rear cargo door of the transport aircraft in this application is as follows:

[0066] 1. Unlock the docking lock on the middle cabin door;

[0067] 2. The left and right side hatches are opened;

[0068] 3. The middle cabin door opens;

[0069] 4. The upper lock of the middle cabin door is engaged;

[0070] 5. Unlocking the inclined platform lock;

[0071] 6. The ramp opens;

[0072] 7. The sealed hatch is opened;

[0073] 8. Lock the upper lock of the sealed hatch.

[0074] The closing sequence of each door component in the five-door linked rear cargo door of the transport aircraft in this application is as follows:

[0075] 1. Unlock the sealed hatch;

[0076] 2. The sealed hatch is closed;

[0077] 3. The ramp is closed;

[0078] 4. Lock the ramp lock;

[0079] 5. Unlock the upper lock of the middle cabin door;

[0080] 6. The middle cabin door is closed;

[0081] 7. Close the left and right side hatches;

[0082] 8. Lock the docking lock on the middle cabin door.

[0083] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A five-door linked transport category aircraft aft cargo door, characterized by, The application relates to a ramp and sealable cargo door assembly of a cargo aircraft. The ramp assembly (1) comprises a ramp body (12), the front end of the ramp body (12) is hinged to the belly of the fuselage through a first hinge (7), the ramp body (12) is driven to deflect around the front end through a ramp driving mechanism (5), the two sides of the ramp body (12) are provided with a plurality of first locking shafts (15) for connecting with the side beams on the two sides of the fuselage (14) when the ramp body (12) is in a closed state; The sealable cargo door assembly (2) comprises a sealable cargo door body (27), the top end of the sealable cargo door body (27) is hinged to the partition frame on the top of the fuselage (14) through a second hinge (29), the sealable cargo door body (27) is driven to deflect around the top end through a sealable cargo door driving mechanism (28), the bottom end of the sealable cargo door body (27) is provided with a locking claw (30), when the sealable cargo door assembly (2) is in a closed state, the second locking shaft (31) of the ramp assembly (1) can be inserted into the slot of the locking claw (30) after the ramp assembly (1) is closed in place, and the ramp body (12) and the sealable cargo door body (27) in the closed state jointly form the rear sealing structure of the pressurized cargo compartment of the aircraft; The middle cargo door (3) and the two side cargo doors (4) are located behind the sealable cargo door assembly (2), the middle cargo door (3) is located between the two side cargo doors (4), and in the opening process, the middle cargo door (3) is driven to deflect its body towards the inside of the fuselage through a driving mechanism, and the two side cargo doors (4) are driven to deflect their bodies towards the two sides outside the fuselage through a driving mechanism.

2. The five-door linked transport category aircraft aft cargo door of Claim 1, wherein, The first locking shaft (15) of the ramp assembly (1) is locked through a ramp locking mechanism (13) distributed under the side beams on the two sides of the fuselage (14), the ramp locking mechanism (13) comprises a plurality of ramp locking hooks (20), each ramp locking hook (20) is hinged to a ramp locking hook support (21), a plurality of ramp locking hooks (20) are connected in series through a torsion shaft (22), and the torsion shaft (22) is driven to rotate through a ramp locking hook electric driving device (23) installed at the end of the torsion shaft (22) to drive each ramp locking hook (20) to hook each first locking shaft (15) on the two sides of the ramp body (12).

3. The five-door linked transport category aircraft aft cargo door of Claim 1, wherein, The ramp driving mechanism (5) comprises a hydraulic actuator (16), the cylinder body of the hydraulic actuator (16) is connected to a first support (18) on the side beam of the fuselage through a universal joint (17), and the piston rod of the hydraulic actuator (16) is hinged to a second support (19) on the ramp body (12).

4. The five-door linked transport category airplane aft cargo door of Claim 1, wherein, The ramp assembly (1) further comprises an air-drop pull rod (6), a plurality of through holes are arranged on the air-drop pull rod (6), one end of the air-drop pull rod (6) is hinged to a third support (24) on the ramp body (12), and the other end is slidably arranged in a fourth support (25) on the side beam of the fuselage, after the ramp body (12) is opened to a set angle, a limiting ball (26) pre-installed in a corresponding through hole on the air-drop pull rod (6) is limited on the fourth support (25) to realize the locking of the ramp body at the set angle position.

5. The five-door linked transport category airplane aft cargo door of Claim 1, wherein, The sealing cabin door driving mechanism (28) comprises two screw drives (34) connected by a driving shaft (33) provided with an electric drive reduction assembly (32), the screw drives (34) drive a drive drive arm (36) and a sealing cabin door drive arm (37) to deflect to drive the sealing cabin door body (27) to switch between the closed state and the open state.

6. The five-door linked transport category airplane aft cargo door of Claim 1, wherein, The sealing cabin door assembly (2) further comprises a sealing cabin door upper lock (11) comprising an electric lock device (38) and a lock ring (39), the lock ring (39) is installed on the left and right sides of the bottom end of the sealing cabin door body (27), and the electric lock device (38) is fixed on the fuselage partition frame, used to connect with the lock ring (39) to fix the sealing cabin door body (27) when the sealing cabin door body (27) is in the open state.

7. The five-door linked transport category aircraft aft cargo door of Claim 1, wherein, The middle cabin door (3) comprises a middle cabin door body (40), the rear end of the middle cabin door body (40) is hinged to the tail partition frame of the fuselage by a third hinge (10), the middle cabin door body (40) is driven to deflect around the rear end by a middle cabin door driving mechanism (9), and the two sides of the middle cabin door body (40) are provided with a middle cabin door butt joint lock mechanism (41) for connecting with the side cabin door lock ring (42) on the side cabin door (4) in the closed state.

8. The five-door linked transport category airplane aft cargo door of Claim 7, wherein, The middle cabin door (3) further comprises a middle cabin door upper lock device (8) and an upper lock ring (43), the middle cabin door upper lock device (8) is installed on the fuselage partition frame, and the upper lock ring (43) is located on the middle cabin door body (40), after the middle cabin door body (40) is opened to the position, the upper lock ring (43) on the middle cabin door body (40) is locked in the open state by the middle cabin door upper lock device (8).

9. The five-door linked transport category airplane aft cargo door of Claim 1, wherein, The side cabin door (4) comprises a left side cabin door body (50) and a right side cabin door body (51), each cabin door body is driven to deflect by a side cabin door driving device (48), the side cabin door driving device (48) comprises a side cabin door driving shaft (53), each cabin door body is connected with the side cabin door driving shaft (53) through a plurality of rocker arms (54), and the side cabin door driving shaft (53) is driven to rotate by an electric drive reduction device (52).

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