A door mechanism for an aircraft with an irregular curved surface

Abstract

The present invention relates to the technical field of aircraft, and discloses a door mechanism for an aircraft with an irregular curved surface. The key points of its technical solution are that it includes a fuselage, a door, a connecting part and a limit lock; one end of the connecting part is connected to the door, and the other end is connected to the fuselage for opening the door, and the limit lock is arranged on the fuselage for locking the door from being opened by the connecting part; after the connecting part opens the door, there is a gap between one end of the door and the fuselage; the side of the door is composed of a first transition section, a second transition section and a third transition section; the first transition section is close to the top end of the fuselage, and the third transition section is close to the bottom end of the fuselage, the connecting part is arranged in the first transition section, and the limit lock is arranged in the second transition section, the length of the first transition section is greater than the length of the second transition section, and the door is designed as a whole into three transition sections.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and more particularly to a door mechanism of an aircraft with an irregular curved surface. Background Art

[0002] An aircraft is a type of drone used to transport goods through the air. Due to its large size, it is necessary to consider air resistance, so the aircraft's appearance will have certain special designs. The position of the hatch needs to be changed to match the fuselage shape to meet the requirement of reducing resistance. Therefore, the shape is mostly curved and irregular, and the hatch can be opened manually or electrically.

[0003] The problem with manual operation is that the installation structure of the curved door is complex and requires manpower to disassemble and assemble multiple fasteners. Manual disassembly of the door has high maintenance costs and a short service life. The problem with traditional electric operation is that the opening angle is not large enough. The door is easily scratched by cargo during loading and unloading, causing damage to the entire door, which in turn leads to unstable flight of the aircraft. The shape of the traditional electric door is not convenient for stable opening during the opening process. Since there are many door angles, there are more fixed positions, which makes the structure more complicated and inconvenient to maintain. There are too few fixed positions and it is difficult to improve the sealing. Summary of the Invention

[0004] In view of the shortcomings of the prior art, the purpose of the present invention is to provide a door mechanism for an aircraft with an irregular curved surface. The door is designed as a whole into three transition sections, so that the door as a whole forms three transition angles. A connecting part is used to connect one of the transition sections, and then a limit lock is used to lock one of the transition angles, so that the fixed points have two positions. The structure is simple and maintenance is convenient, and the problem of few fixed points and low sealing is avoided. In addition, the connecting part is set on one of the long transition sections, so that the force output by the connecting part will not be particularly large, thereby ensuring energy saving and extended service life, and the opening angle can be larger.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a door mechanism of an aircraft with an irregular curved surface, comprising a fuselage, a door, a connecting portion and a limit lock; one end of the connecting portion is connected to the door, and the other end is connected to the fuselage for opening the door, and the limit lock is arranged on the fuselage for locking the door from being opened by the connecting portion; after the door is opened by the connecting portion, a gap exists between one end of the door and the fuselage; the side surface of the door is composed of a first transition section, a second transition section and a third transition section; the first transition section is close to the top end of the fuselage, the third transition section is close to the bottom end of the fuselage, and the connecting portion is arranged on the first transition section The limit lock is arranged on the second transition section, and the length of the first transition section is greater than that of the second transition section. By designing the hatch as a whole into three transition sections, the hatch as a whole will form three transition angles. The connecting part is used to connect one of the transition sections, and then one of the transition angles is locked with the limit lock, so that the fixed points have two positions. The structure is simple and maintenance is convenient, avoiding the problem of few fixed points and low sealing. In addition, by setting the connecting part on one of the long transition sections, the force output by the connecting part will not be particularly large, ensuring energy saving and extension of service life, and the opening angle can be larger.

[0006] As a further improvement of the present invention, the connecting part includes a fixing part, a rotating shaft frame, a driving part, a coupling, an elastic part and a connecting part; the fixing part is fixedly connected to the fuselage, the driving part is fixedly connected to the fixing part, the rotating shaft frame is fixedly connected to the fuselage, the coupling connects the output shaft of the driving part with the driven shaft of the rotating shaft frame, the connecting part is fixedly connected to the cabin door, one end of the elastic part is fixedly connected to the driven shaft, and the other end is fixedly connected to the connecting part; when the cabin door is closed, the elastic part is in a compressed state, and the elastic part is used to assist in the process of opening the cabin door, so that the cabin door can obtain an initial velocity of popping open when opening, thereby facilitating the output of force by the driving part, avoiding no transition when outputting force, and reducing the service life.

[0007] As a further improvement of the present invention, the limit lock includes a power unit, a connector, a fixed block, a limit piece and a locking core; the power unit is fixedly connected to the fuselage, the fixed block is fixedly connected to the fuselage, the connector connects the power shaft of the power unit with the fixed shaft of the fixed block, the limit piece is fixedly connected to the fixed shaft, the locking core is fixedly connected to the cabin door, and is provided with a notch matching the limit piece. By setting the locking core at the position with the smallest transition angle, the locking force can maximize the limitation of the cabin door body.

[0008] As a further improvement of the present invention, the cabin door includes an outer door body, an inner door body and an adsorption piece; the outer door body and the inner door body are fixedly connected, the shape of the outer door body matches the fuselage, and the adsorption piece is fixedly connected to the fuselage for adsorbing the outer door body, wherein the outer door body covers the inner door body to form a stepped pattern, and the position where the adsorption piece is adsorbed is the position where the area of the outer door body exceeds the area of the inner door body. By setting the cabin door as two stepped door bodies, the sealing is improved, and the large opening of the stepped cabin door can have a larger opening angle, thereby facilitating the entry and exit of goods.

[0009] As a further improvement of the present invention, the cabin door also includes a separation structure and a manual drive unit; the separation structure is arranged in the inner door body for connecting to the outer door body, and the manual drive unit is arranged on the outer door body for manually driving the separation structure. By using a manual opening structure set between the outer door body and the inner door body, the problem of being unable to open the cabin door when the power system is paralyzed is avoided. After the outer door body is disassembled, the inner door body leaks out and the side of the fuselage is exposed, which is convenient for setting a temporary information transmission port to complete temporary command operations.

[0010] As a further improvement of the present invention, the separation structure includes a blocking member, a spline sleeve, a hollow spline rod, a nut, a belt auxiliary wheel, a transmission chamber, a belt main wheel, a rotating shaft, a rotating chamber, and a threaded rod; the transmission chamber is opened in the inner door body, the blocking member is fixedly connected to the transmission chamber, the spline sleeve is rotatably connected to the transmission chamber, the spline rod is splined with the spline sleeve, the nut is fixedly connected to the spline rod, the belt auxiliary wheel is fixedly connected to the spline sleeve, the rotating chamber is opened in the inner door body, the rotating shaft is rotatably installed in the rotating chamber, the belt main wheel is fixedly connected to the rotating shaft, and is connected to the belt auxiliary wheel through a belt, and power output is completed by rotating the belt main wheel, and then the spline sleeve drives the nut to rotate and connect with the screw rod to complete the connection between the inner and outer door bodies, and multiple separation structures are set, three in this scheme, and belt transmission is used to form a more stable connection.

[0011] As a further improvement of the present invention, the manual drive part includes a transmission groove, a coupling, a spring, an electromagnetic adsorption block, a pair of contacts, a handwheel and a transmission shaft; the transmission groove is opened in the outer door body, the handwheel is slidably installed in the transmission groove, the electromagnetic adsorption block is fixedly connected in the transmission groove, the transmission shaft is fixedly connected to the handwheel, the transmission shaft and the electromagnetic adsorption block slide together, one end of the spring abuts against the electromagnetic adsorption block, and the other end is fixedly connected to the electromagnetic adsorption block, the coupling connects the transmission shaft and the rotating shaft detachably, the transmission groove and the rotating cavity are connected, a pair of contacts are respectively connected to the fuselage for supplying power to the electromagnetic adsorption block, and the contacts are used to supply power to the electromagnetic adsorption block when the cabin door is closed. When there is a problem with the aircraft's power system, there will be no power supply at the contact position, so that the spring will pop out the handwheel, and at this time the mechanical structure serves as a reminder, informing that the power system is out of control or there is a problem with the power system, and then manual drive is performed to disengage the inner and outer doors.

[0012] As a further improvement of the present invention, at least one sliding rod is slidably installed on the outer door body; the sliding rod can be pressed against the adsorption part, and the adsorption part can continuously adsorb the hatch when the power system becomes uncontrollable by utilizing the sliding rod, and the sliding rod can be pushed to complete the separation.

[0013] As a further improvement of the present invention, the inner door body is detachably installed with a connecting plate and a connecting plate; the locking core is fixedly connected to the connecting plate, and the connecting piece is fixedly connected to the connecting plate. It is divided into three parts on the inner door body, namely the connecting plate, the connecting plate and the remaining part of the inner door body, so as to facilitate emergency disassembly when the power is completely out of control.

[0014] Beneficial effects of the present invention:

[0015] (1) The present invention designs the hatch as a whole into three transition sections, so that the hatch as a whole forms three transition angles. A connecting part is used to connect one of the transition sections, and then one of the transition angles is locked with a limit lock, so that the fixing points are at two positions. The structure is simple and maintenance is convenient, and the problem of low sealing due to a small number of fixing points is avoided. In addition, by setting the connecting part on one of the long transition sections, the force output by the connecting part will not be particularly large, thereby ensuring energy conservation and extending the service life, and the opening angle can be larger.

[0016] (2) The present invention utilizes elastic parts to assist in the process of opening the hatch door, so that the hatch door can obtain an initial velocity when it is opened, thereby facilitating the output of force by the driving part and avoiding the lack of transition when outputting force, thereby reducing the service life.

[0017] (3) The present invention sets the locking core at the position with the smallest transition angle, so that the locking force can limit the hatch body to the maximum extent. By setting the hatch as two stepped door bodies, the sealing performance is improved, and the stepped hatch opening can have a larger opening angle, thereby facilitating the entry and exit of goods.

[0018] (4) The present invention avoids the problem of being unable to open the cabin door when the power system is paralyzed by setting a manual opening structure between the outer door body and the inner door body. After the outer door body is disassembled, the inner door body leaks out and the side of the fuselage is exposed, which facilitates the setting of a temporary information transmission port and completes temporary command operations.

[0019] (5) The present invention completes power output by rotating the belt main pulley, and then the spline sleeve drives the nut to rotate and connect with the screw to complete the connection between the inner and outer door bodies. The separation structure is set to multiple, three in this solution, and the belts are used to transmit power to each other to form a more stable connection.

[0020] (6) The present invention utilizes contacts to power the electromagnetic adsorption block when the cabin door is closed. When a problem occurs in the aircraft power system, there will be no power supply at the contact position, so that the spring will pop out the hand wheel. At this time, the mechanical structure serves as a reminder, informing that the power system is out of control or there is a problem with the power system. Then, manual drive is performed to disengage the inner and outer doors.

[0021] (7) The present invention utilizes a sliding rod to continuously adsorb the hatch door by the adsorption member when the power system becomes uncontrollable, and pushes the sliding rod to complete the detachment. By dividing the inner door body into three parts, namely the connecting plate, the connecting plate and the remaining part of the inner door body, it is convenient to complete emergency disassembly when the power is completely out of control. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the main structure of the present invention;

[0023] Figure 2 This is a schematic diagram of the structure of the hatch of the present invention after it is opened;

[0024] Figure 3 It is a side structural schematic diagram of the present invention;

[0025] Figure 4 This invention Figure 3 Schematic diagram of the structure after the middle hatch is opened;

[0026] Figure 5 This invention Figure 3 An enlarged structural diagram of the middle limit lock;

[0027] Figure 6 This invention Figure 5Schematic diagram of the limit lock in the open state;

[0028] Figure 7 This invention Figure 3 A schematic diagram of the enlarged structure of the middle connection part;

[0029] Figure 8 This invention Figure 1 Schematic diagram of the cross-section structure;

[0030] Figure 9 This invention Figure 8 A schematic diagram of the enlarged structure of the separation structure;

[0031] Figure 10 This invention Figure 8 Schematic diagram of the enlarged structure of the manual drive part.

[0032] 1. Fuselage; 2. Cabin door; 21. Outer door body; 22. Inner door body; 23. Adsorption member; 24. Sliding rod; 25. Contact; 3. Connecting part; 31. Fixing member; 32. Driving member; 33. Coupling; 34. Elastic member; 35. Connecting member; 4. Limit lock; 41. Power unit; 42. Connector; 43. Fixing block; 44. Limiting member; 45. Locking core; 5. Separation structure; 51. Blocking member; 52. Spline sleeve; 53. Spline rod; 54. Nut; 55. Belt auxiliary pulley; 56. Transmission chamber; 57. Threaded rod; 6. Manual driving part; 61. Belt main pulley; 62. Rotating shaft; 63. Rotating chamber; 64. Transmission groove; 65. Coupling member; 66. Spring; 67. Electromagnetic adsorption block; 68. Handwheel; 69. Transmission shaft; 8. Connecting plate; 9. Connecting plate. DETAILED DESCRIPTION

[0033] The present invention will be described in further detail below with reference to the accompanying drawings and embodiments. Identical components are denoted by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "upper," and "lower" used in the following description refer to directions in the accompanying drawings, and the terms "bottom," "top," "inner," and "outer" refer to directions toward or away from the geometric center of a particular component, respectively.

[0034] Reference Figure 1-10As shown, a door mechanism of an aircraft with an irregular curved surface in this embodiment includes a fuselage 1, a door 2, a connecting portion 3 and a limit lock 4; one end of the connecting portion 3 is connected to the door 2, and the other end is connected to the fuselage 1, for opening the door 2, and the limit lock 4 is arranged on the fuselage 1, for locking the door 2 from being opened by the connecting portion 3; after the door 2 is opened by the connecting portion 3, there is a gap between one end of the door 2 and the fuselage 1; the side surface of the door 2 is composed of a first transition section, a second transition section and a third transition section; the first transition section is close to the top end of the fuselage 1, the third transition section is close to the bottom end of the fuselage 1, and the connecting portion 3 is arranged in the first transition section The limit lock 4 is arranged on the second transition section, and the length of the first transition section is greater than that of the second transition section. By designing the hatch 2 as a whole into three transition sections, the hatch 2 as a whole will form three transition angles, and one of the transition sections is connected by the connecting part 3, and then one of the transition angles is locked with the limit lock 4, so that the fixed points are at two positions, the structure is simple, and maintenance is convenient, avoiding the problem of few fixed points and low sealing. In addition, by setting the connecting part 3 on one of the long transition sections, the force output by the connecting part 3 will not be particularly large, ensuring energy saving and extension of service life, and the opening angle can be larger.

[0035] like Figure 1-10 As shown, the connecting part 3 includes a fixing part 31, a rotating shaft 62 frame, a driving part 32, a coupling 33, an elastic part 34 and a connecting part 35; the fixing part 31 is fixedly connected to the fuselage 1, the driving part 32 is fixedly connected to the fixing part 31, the rotating shaft 62 frame is fixedly connected to the fuselage 1, the coupling 33 connects the output shaft of the driving part 32 with the driven shaft of the rotating shaft 62 frame, the connecting part 35 is fixedly connected to the cabin door 2, one end of the elastic part 34 is fixedly connected to the driven shaft, and the other end is fixedly connected to the connecting part 35; when the cabin door 2 is closed, the elastic part 34 is in a compressed state, and the elastic part 34 is used to assist in the opening process of the cabin door 2, so that the cabin door can obtain an initial velocity of popping open, thereby facilitating the output of force by the driving part 32, avoiding no transition when outputting force, and reducing the service life.

[0036] like Figure 1-10 As shown, the limit lock 4 includes a power unit 41, a connector 42, a fixed block 43, a limit piece 44 and a locking core 45; the power unit 41 is fixedly connected to the fuselage 1, the fixed block 43 is fixedly connected to the fuselage 1, the connector 42 connects the power shaft of the power unit 41 with the fixed shaft of the fixed block 43, the limit piece 44 is fixedly connected to the fixed shaft, the locking core 45 is fixedly connected to the cabin door 2, and is provided with a notch matching the limit piece 44. By setting the locking core 45 at the position with the smallest transition angle, the locking force can maximize the limitation of the cabin door 2 body.

[0037] like Figure 1-10As shown, the cabin door 2 includes an outer door body 21, an inner door body 22 and an adsorption member 23; the outer door body 21 and the inner door body 22 are fixedly connected, the shape of the outer door body 21 matches the fuselage 1, and the adsorption member 23 is fixedly connected to the fuselage 1 for adsorbing the outer door body 21, wherein the outer door body 21 covers the inner door body 22 to form a stepped pattern, and the adsorption position of the adsorption member 23 is where the area of the outer door body 21 exceeds the area of the inner door body 22. By setting the cabin door 2 as two stepped door bodies, the sealing is improved, and the large opening of the stepped cabin door 2 can have a larger opening angle, thereby facilitating the entry and exit of goods.

[0038] like Figure 1-10 As shown, the cabin door 2 also includes a separation structure 5 and a manual drive unit 6; the separation structure 5 is arranged in the inner door body 22 for connecting to the outer door body 21, and the manual drive unit 6 is arranged on the outer door body 21 for manually driving the separation structure 5. By setting a manual opening structure between the outer door body 21 and the inner door body 22, the problem of being unable to open the cabin door 2 when the power system is paralyzed is avoided. After the outer door body 21 is disassembled, the inner door body 22 leaks out and the side of the fuselage 1 is exposed, which is convenient for setting a temporary information transmission port to complete temporary command operations.

[0039] like Figure 1-10 As shown, the separation structure 5 includes a blocking member 51, a spline sleeve 52, a hollow spline rod 53, a nut 54, a belt auxiliary pulley 55, a transmission chamber 56, a belt main pulley 61, a rotating shaft 62, a rotating chamber 63, and a threaded rod 57; the transmission chamber 56 is opened in the inner door body 22, the blocking member 51 is fixedly connected in the transmission chamber 56, the spline sleeve 52 is rotatably connected in the transmission chamber 56, the spline rod 53 is spline-connected to the spline sleeve 52, the nut 54 is fixedly connected to the spline rod 53, and the belt auxiliary pulley 55 is fixedly connected It is connected to the spline sleeve 52, the rotating chamber 63 is opened in the inner door body 22, the rotating shaft 62 is rotatably installed in the rotating chamber 63, the belt main pulley 61 is fixedly connected to the rotating shaft 62, and is connected to the belt auxiliary pulley 55 through a belt. The power output is completed by rotating the belt main pulley 61, and then the spline sleeve 52 drives the nut 54 to rotate and connect with the screw to complete the connection between the inner and outer door bodies 21. The separation structure 5 is set to multiple, three in this solution, and the belt is transmitted to each other to form a more stable connection.

[0040] like Figure 1-10As shown, the manual drive unit 6 includes a transmission groove 64, a coupling 65, a spring 66, an electromagnetic adsorption block 67, a pair of contacts 25, a hand wheel 68 and a transmission shaft 69; the transmission groove 64 is opened in the outer door body 21, the hand wheel 68 is slidably installed in the transmission groove 64, the electromagnetic adsorption block 67 is fixedly connected in the transmission groove 64, the transmission shaft 69 is fixedly connected to the hand wheel 68, the transmission shaft 69 and the electromagnetic adsorption block 67 are slidably matched, one end of the spring 66 abuts on the electromagnetic adsorption block 67, and the other end is fixedly connected to the electromagnetic adsorption block 67, and the coupling 65 connects the transmission shaft 69 is detachably connected to the rotating shaft 62, the transmission groove 64 is connected to the rotating cavity 63, and a pair of contacts 25 are respectively connected to the fuselage 1 for supplying power to the electromagnetic adsorption block 67. When the cabin door 2 is closed, the contacts 25 supply power to the electromagnetic adsorption block 67. When there is a problem with the aircraft power system, there will be no power supply at the position of the contacts 25, so that the spring 66 will pop out the handwheel 68. At this time, the mechanical structure serves as a reminder, informing that the power system is out of control or there is a problem with the power system, and then manually drive to disengage the inner and outer doors.

[0041] like Figure 1-10 As shown, at least one sliding rod 24 is slidably installed on the outer door body 21; the sliding rod 24 can be pressed against the adsorption member 23. By utilizing the sliding rod 24, when the power system becomes uncontrollable, the adsorption member 23 continuously adsorbs the hatch 2, and the sliding rod 24 is pushed to complete the separation.

[0042] like Figure 1-10 As shown, the inner door body 22 is detachably installed with a connecting plate 8 and a connecting plate 9; the locking core 45 is fixedly connected to the connecting plate 8, and the connecting piece 35 is fixedly connected to the connecting plate 9. By being divided into three parts on the inner door body 22, namely the connecting plate 8, the connecting plate 9 and the remaining part of the inner door body 22, emergency disassembly is facilitated when power is completely out of control.

[0043] Working principle: Figure 1-10 As shown, the opening process of the hatch 2 is as follows: the electric signal power device 41 is sent, the power device 41 rotates to drive the limit member 44 to rotate, the locking core 45 is not constrained, and the state of the limit lock 4 changes as shown in FIG. Figure 6 As shown, the elastic member 34 causes the driving connecting member 35 and the hatch 2 to move outward along the direction of the hatch 2 under the action of its own elastic force. This is the state in which the hatch 2 is popped up. Figure 1 ; Start the electrical signal to the drive member 32, the drive member 32 rotates to drive the coupling 33 to rotate, the coupling 33 drives the main elastic member 34 to rotate, the elastic member 3 turns to drive the connecting member 35 and the hatch 2 to flip outward, this is the hatch open state, you can see Figure 2 .

[0044] When a problem occurs in the power system, the contact 25 is no longer powered, and the electromagnetic adsorption block 67 will no longer adsorb the spring 66 and the handwheel 68, so that the handwheel 68 pops out, and then the handwheel 68 is manually pushed, so that the transmission shaft 69 pushes the coupling 65 to complete the connection, and then it can be rotated. The power is transmitted to the rotating shaft 62, so that the belt main pulley 61 transmits the power to the other belt auxiliary pulley 55 through the belt, and then the spline sleeve 52 rotates, driving the spline rod 53 and the nut 54 to rotate, so that the nut 54 disengages from the threaded rod 57, and then pushes the sliding rod 24 against the adsorption member 23, thereby facilitating disengagement. After the outer door body 21 is detached, the corresponding operation can be completed according to the situation. The temporary information transmission port can be found on the side of the outer door body 21 to complete the issuance of the power command, or when the power system is completely unusable, the connecting plate 8 and the connecting plate 9 on the inner door body 22 can be removed in sequence with tools, so that the locking position is completed. The emergency disassembly of the hatch door 2 is completed, which is convenient for cargo removal and maintenance, retains the fault point, and facilitates inspection and analysis of the cause of the fault.

[0045] The above are merely preferred embodiments of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions based on the principles of the present invention are within the scope of protection of the present invention. It should be noted that improvements and modifications that do not depart from the principles of the present invention are within the scope of protection of the present invention.

Claims

1. A door mechanism for an aircraft with an irregular curved surface, characterized by: It comprises a fuselage (1), a door (2), a connecting portion (3) and a limit lock (4); One end of the connecting portion (3) is connected to the cabin door (2), and the other end is connected to the fuselage (1), and is used to open the cabin door (2). A limit lock (4) is provided on the fuselage (1) and is used to lock the cabin door (2) so that it cannot be opened by the connecting portion (3). After the connecting portion (3) opens the cabin door (2), a gap exists between one end of the cabin door (2) and the fuselage (1); The side of the door (2) is composed of a first transition section, a second transition section, and a third transition section; the first transition section is close to the top end of the fuselage (1), the third transition section is close to the bottom end of the fuselage (1), the connecting portion (3) is arranged on the first transition section, the limit lock (4) is arranged on the second transition section, and the length of the first transition section is greater than the length of the second transition section; The connecting portion (3) includes a fixing member (31), a rotating shaft frame, a driving member (32), a coupling (33), an elastic member (34) and a connecting member (35); The fixing member (31) is fixedly connected to the fuselage (1), the driving member (32) is fixedly connected to the fixing member (31), the rotating shaft frame is fixedly connected to the fuselage (1), the coupling (33) connects the output shaft of the driving member (32) to the driven shaft of the rotating shaft frame, the connecting member (35) is fixedly connected to the cabin door (2), and one end of the elastic member (34) is fixedly connected to the driven shaft, and the other end is fixedly connected to the connecting member (35); When the hatch (2) is closed, the elastic member (34) is in a compressed state; The limit lock (4) includes a power device (41), a connector (42), a fixing block (43), a limit member (44) and a locking core (45); The power unit (41) is fixedly connected to the fuselage (1), the fixed block (43) is fixedly connected to the fuselage (1), the connector (42) connects the power shaft of the power unit (41) to the fixed shaft of the fixed block (43), the limiter (44) is fixedly connected to the fixed shaft, the locking core (45) is fixedly connected to the cabin door (2), and is provided with a notch matching the limiter (44).

2. The door mechanism of an aircraft with an irregular curved surface according to claim 1, characterized in that: The hatch (2) comprises an outer door body (21), an inner door body (22) and a suction member (23); The outer door body (21) and the inner door body (22) are fixedly connected, the shape of the outer door body (21) matches the fuselage (1), and the adsorption member (23) is fixedly connected to the fuselage (1) and is used to adsorb the outer door body (21).

3. The door mechanism of an aircraft with an irregular curved surface according to claim 2, characterized in that: The hatch (2) further includes a separation structure (5) and a manual drive unit (6); The separation structure (5) is arranged in the inner door body (22) and is used to connect to the outer door body (21); the manual driving part (6) is arranged on the outer door body (21) and is used to manually drive the separation structure (5).

4. The door mechanism of an aircraft with an irregular curved surface according to claim 3, characterized in that: The separation structure (5) includes a blocking member (51), a spline sleeve (52), a hollow spline rod (53), a nut (54), a belt auxiliary wheel (55), a transmission cavity (56), a belt main wheel (61), a rotating shaft (62), a rotating cavity (63), and a threaded rod (57); The transmission chamber (56) is opened in the inner door body (22), the blocking member (51) is fixedly connected in the transmission chamber (56), the spline sleeve (52) is rotatably connected in the transmission chamber (56), the spline rod (53) is spline-connected to the spline sleeve (52), the nut (54) is fixedly connected to the spline rod (53), the belt auxiliary wheel (55) is fixedly connected to the spline sleeve (52), the rotation chamber (63) is opened in the inner door body (22), the rotation shaft (62) is rotatably installed in the rotation chamber (63), the belt main wheel (61) is fixedly connected to the rotation shaft (62), and is connected to the belt auxiliary wheel (55) through a belt.

5. The door mechanism of an aircraft with an irregular curved surface according to claim 4, characterized in that: The manual drive unit (6) includes a transmission groove (64), a coupling member (65), a spring (66), an electromagnetic adsorption block (67), a pair of contacts (25), a hand wheel (68) and a transmission shaft (69); The transmission groove (64) is opened in the outer door body (21), the hand wheel (68) is slidably installed in the transmission groove (64), the electromagnetic adsorption block (67) is fixedly connected in the transmission groove (64), the transmission shaft (69) is fixedly connected to the hand wheel (68), the transmission shaft (69) and the electromagnetic adsorption block (67) are slidably matched, one end of the spring (66) abuts on the electromagnetic adsorption block (67), and the other end is fixedly connected to the electromagnetic adsorption block (67), the coupling (65) detachably connects the transmission shaft (69) and the rotating shaft (62), the transmission groove (64) and the rotating chamber (63) are connected, and a pair of contacts (25) are respectively connected to the fuselage (1) for supplying power to the electromagnetic adsorption block (67).

6. The door mechanism of an aircraft with an irregular curved surface according to claim 2, characterized in that: At least one sliding rod (24) is slidably mounted on the outer door body (21); the sliding rod (24) can abut against the adsorption member (23).

7. The door mechanism of an aircraft with an irregular curved surface according to claim 5, characterized in that: The inner door body (22) is detachably mounted with a connecting plate (8) and a connecting plate (9); The locking core (45) is fixedly connected to the connecting plate (8), and the connecting piece (35) is fixedly connected to the connecting plate (9).

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