Aircraft emergency door

Abstract

The invention discloses an aircraft emergency door, comprising a door shell hinged in an aircraft shell, rotatable around a hinge center and constrained by a first locking point mechanism and a second locking point mechanism; an inner door handle assembly is provided at the left side of the lower middle part of the inner side of the door shell, an outer door handle assembly is provided at the lower middle part of the outer side of the door shell, the inner door handle assembly is mechanically connected to the outer door handle assembly, the outer door handle assembly is mechanically connected to the first locking point mechanism provided at the lower right side of the door shell and the second locking point mechanism provided at the lower left side of the door shell, the first locking point mechanism is connected to the longitudinal beam of the aircraft shell, and the second locking point mechanism is connected to the beam at the lower side of the aircraft shell. The invention can be locked by using two locking points and a hinge at the top, and can be conveniently jettisoned in an emergency.

Description

[Technical field]

[0001] The invention relates to the technical field of aircraft structure design, in particular to the technical field of an aircraft emergency door. [Background technology]

[0002] The current aircraft emergency door opening method is still the old-fashioned structure, which is not very convenient to open. In addition, the aircraft emergency door requires a reliable locking safety. Therefore, a new aircraft emergency door structure is needed, which can be opened quickly and conveniently from the inside and locked safely. [Summary of the invention]

[0003] The purpose of the present invention is to solve the problems in the prior art and to provide an aircraft emergency door that can be locked using two locking points and a hinge on the top and can be conveniently jettisoned in an emergency.

[0004] To achieve the above-mentioned purpose, the present invention proposes an aircraft emergency door, comprising a door shell hinged in the aircraft shell, rotatable around a hinge center and constrained by a first locking point mechanism and a second locking point mechanism; the middle part of the upper end of the door shell is hinged to the cross beam of the aircraft shell, the door shell can rotate around the hinge center and the hinge center is a hinge rod, a hinge handle assembly is fixed on the hinge rod and the hinge handle assembly cooperates with the cross beam of the aircraft shell; the upper left end of the inner side of the door shell is hinged to the right side of the arc beam of the aircraft shell and the door shell can rotate around the hinge center The upper right end of the inner side of the door shell is connected to the longitudinal beam of the aircraft shell through a gas spring assembly; an inner door handle assembly is provided at the lower left middle part of the inner side of the door shell, and an outer door handle assembly is provided at the lower middle part of the outer side of the door shell. The inner door handle assembly is mechanically connected to the outer door handle assembly, and the outer door handle assembly is mechanically connected to a first locking point mechanism provided at the lower right side of the door shell and a second locking point mechanism at the lower left side of the door shell. The first locking point mechanism is connected to the longitudinal beam of the aircraft shell, and the second locking point mechanism is connected to the beam below the aircraft shell.

[0005] Preferably, the aircraft shell includes an outer skin and longitudinal beams, transverse beams and arc-shaped beams arranged on the inner side of the outer skin, and the longitudinal beams, transverse beams and arc-shaped beams are used to support the outer skin.

[0006] Preferably, the gas spring assembly includes a special-shaped gas spring seat, a gas spring and a longitudinal beam gas spring seat, a special-shaped gas spring seat is fixed to the upper right end of the inner side of the door shell, one end of the gas spring is hinged on the special-shaped gas spring seat and the gas spring can rotate around the hinge center, the other end of the gas spring is hinged on the longitudinal beam gas spring seat and the gas spring can rotate around the hinge center, and the longitudinal beam gas spring seat is fixed on the longitudinal beam of the aircraft shell.

[0007] Preferably, the hinge handle assembly includes a hinge handle, a handle clamp and a handle seat. The handle seat is fixed on a hinge rod at the upper end of the door shell. The hinge handle is hinged on the handle seat and can rotate around the hinge center. The upper end of the hinge handle is fitted in the handle clamp, and the handle clamp is fixed on the crossbeam.

[0008] Preferably, the inner door handle assembly comprises an inner handle, an inner handle shell, a first brake line structure, an inner handle coil spring, an inner handle main shaft, a connecting arm and a connecting arm shaft (57); the inner handle shell is fixed to the lower middle part of the outer side of the hatch shell; the inner handle main shaft is installed in the inner handle shell; the inner handle and the inner handle coil spring are mounted on the inner handle main shaft; one end of the inner handle coil spring cooperates with the inner handle and the other end cooperates with the inner handle shell; the inner handle main shaft is symmetrically installed with connecting arms in upper and lower directions; the other end of the connecting arm is fixed to the connecting arm shaft (57); one end of the first brake line structure is fixed to the upper end of the connecting arm shaft (57); the other end of the first brake line structure is connected to the outer door handle assembly.

[0009] Preferably, the first locking point mechanism comprises a longitudinal beam connecting seat, a first locking point mechanism housing, a first locking fork, a first locking fork main shaft, a first locking fork coil spring, a first dial, a first dial shaft, a first dial coil spring, an indicating sector tooth and an indicating gear shaft, the first locking point mechanism housing is installed at the lower right part of the inner side of the door housing, a first locking fork is installed inside the first locking point mechanism housing through the first locking fork main shaft, a first locking fork coil spring is mounted on the first locking fork main shaft, one end of the first locking fork coil spring is connected to the first locking fork, and the other end is connected to the first locking point mechanism housing; the first locking point mechanism housing is installed inside the first locking point mechanism housing through the first A first dial wheel is installed on the dial shaft, and a first dial wheel coil spring is mounted on the first dial shaft, one end of the first dial wheel coil spring is connected to the first dial wheel, and the other end is connected to the first locking point mechanism housing, the first dial wheel is meshed with the first locking fork, and the first dial wheel is connected to the end of the second brake line structure of the outward door handle assembly; an opening is provided on the first locking fork and the opening is used to constrain the longitudinal beam connecting seat, and the longitudinal beam connecting seat is fixed to the longitudinal beam of the aircraft housing; an indication fan tooth is fixed to the end of the first locking fork main shaft, the indication fan tooth is a fan-shaped gear and meshed with the indication gear shaft, and the indication gear shaft is fixed in the first locking point mechanism housing.

[0010] Preferably, the second locking point mechanism comprises an aircraft shell connecting assembly, a second locking point mechanism shell, a second locking fork, a second locking fork spindle, a second locking fork coil spring, a second dial wheel, a second dial wheel shaft and a second dial wheel coil spring, the second locking point mechanism shell is installed at the bottom end of the left part of the cabin door shell, the second locking fork is installed in the second locking point mechanism shell through the second locking fork spindle, the second locking fork is sleeved with the second locking fork, one end of the second locking fork coil spring is connected with the second locking fork, and the other end is connected with the second locking point mechanism shell; the second dial wheel is installed in the second locking point mechanism shell through the second dial wheel shaft, the second dial wheel shaft is sleeved with the second dial wheel coil spring, one end of the second dial wheel coil spring is connected with the second dial wheel, and the other end is connected with the second locking point mechanism shell, the second dial wheel is meshed with the second locking fork, and the second dial wheel is connected to the end of the third brake line structure of the outward opening door handle assembly; the second locking fork is provided with an opening and the opening is used to constrain the aircraft shell connecting assembly, and the aircraft shell connecting assembly is fixed to the aircraft shell.

[0011] Preferably, the outside door handle assembly comprises an outside handle, an outside handle shell, a short rod, a push rod, a spring, a push rod seat, a first gear rod, a second gear rod, a second brake line structure, a third brake line structure, an outside handle main shaft, a lock core structure and a gear rod coil spring. The outside handle shell is fixed to the lower middle part of the outer side of the hatch shell, and an outside handle is installed in the outside handle shell through the outside handle main shaft. A short rod is hinged to the upper end of the outside handle main shaft, and a push rod is hinged to the other end of the short rod. A spring is mounted on the push rod, and the other end of the push rod passes through the push rod seat fixed on the outside handle shell and is opposite to the upper end of the second gear rod; a first gear rod and a second gear rod that mesh with each other are installed on the front side of the outside handle shell, and the first gear rod is the upper A toothed rod at one end, a second brake line structure is connected to the lower end of the first gear rod, and the other end of the second brake line structure is connected to the first locking point mechanism. The second gear rod is a toothed rod in the middle part, and the upper end of the second gear rod is connected to the first brake line structure of the inner door handle assembly, and the lower end of the second gear rod is connected to the third brake line structure, and the other end of the third brake line structure is connected to the second locking point mechanism; a gear rod coil spring is coaxially fixed to the teeth of the second gear rod, one end of the gear rod coil spring is fixed to the second gear rod, and the other end is fixed to the outer handle shell; a lock core structure is fixed in the outer handle shell and the lock core structure is rotatable, and the lock tongue of the lock core structure fits in the groove on the outer handle.

[0012] Beneficial effects of the present invention: The present invention is locked through two locking points and the top hinge. When the aircraft equipped with the present structure encounters an emergency, the pilot opens the handle, the two locking points will unlock, and then pulls the top hinge handle open, the hinge shaft will automatically release from the cabin door joint, and the jettisoning function can be achieved through the thrust of the gas spring.

[0013] The features and advantages of the present invention will be described in detail through embodiments in conjunction with the accompanying drawings.

Brief Description of the Drawings

[0014] Figure 1 The invention discloses a three-dimensional structure of an aircraft emergency door applied to an aircraft shell. Figure 1 ;

[0015] Figure 2 The invention discloses a three-dimensional structure of an aircraft emergency door applied to an aircraft shell. Figure 2 ;

[0016] Figure 3 This is a bottom-up structural diagram of an aircraft emergency door of the present invention applied in an aircraft shell;

[0017] Figure 4 This is a partial view of an aircraft emergency door of the present invention applied in an aircraft shell;

[0018] Figure 5 The present invention Figure 4 A magnified view of part A in FIG.

[0019] Figure 6 The present invention Figure 4 A magnified view of part B in FIG.

[0020] Figure 7 It is a local structure of an aircraft emergency door of the present invention. Figure 1 ;

[0021] Figure 8 It is a local structure of an aircraft emergency door of the present invention. Figure 2 ;

[0022] Fig. 9 The invention is a three-dimensional diagram of an inner door handle assembly of an aircraft emergency door. Figure 1 ;

[0023] Fig.10 The invention is a three-dimensional diagram of an inner door handle assembly of an aircraft emergency door. Figure 2 ;

[0024] Fig.11 The invention is a three-dimensional diagram of an inner door handle assembly of an aircraft emergency door. Figure 3 ;

[0025] Fig.12 The present invention is a three-dimensional first locking point mechanism of an aircraft emergency door Figure 1 ;

[0026] Fig.13 The present invention is a three-dimensional first locking point mechanism of an aircraft emergency door Figure 2 ;

[0027] Fig.14The invention is a three-dimensional second locking point mechanism of an aircraft emergency door. Figure 1 ;

[0028] Fig.15 The invention is a three-dimensional second locking point mechanism of an aircraft emergency door. Figure 2 ;

[0029] Fig.16 The invention is a three-dimensional external door handle assembly of an aircraft emergency door. Figure 1 ;

[0030] Fig.17 The invention is a three-dimensional external door handle assembly of an aircraft emergency door. Figure 2 ;

[0031] Fig.18 The invention is a three-dimensional external door handle assembly of an aircraft emergency door. Figure 3 ;

[0032] Fig.19 The invention is a three-dimensional external door handle assembly of an aircraft emergency door. Figure 4 .

[0033] In the figure: 1-aircraft shell, 11-longitudinal beam, 12-cross beam, 13-arc beam, 2-cabin door shell, 21-hinged rod, 3-gas spring assembly, 31-special-shaped gas spring seat, 32-gas spring, 33-longitudinal beam gas spring seat, 4-hinge handle assembly, 41-hinge handle, 42-handle clamp, 43-handle seat, 5-inner door handle assembly, 51-inner handle, 52-inner handle shell, 53-first brake line structure, 54-inner handle coil spring, 55-inner handle spindle, 56-connecting arm, 57-connecting arm shaft, 6-first locking point mechanism, 61-longitudinal beam connecting seat, 62-first locking point mechanism shell, 63-first locking fork, 64-first locking fork spindle, 65-first locking fork coil spring, 66-first dial wheel, 6 7-first dial shaft, 68-first dial spring, 69-indicator fan teeth, 610-indicator gear shaft, 7-second locking point mechanism, 71-aircraft shell connecting assembly, 72-second locking point mechanism shell, 73-second locking fork, 74-second locking fork spindle, 75-second locking fork spring, 76-second dial, 77-second dial shaft, 78-second dial spring, 8-outside door handle assembly, 81-outside handle, 82-outside handle shell, 83-short rod, 84-throw rod, 85-spring, 86-throw rod seat, 87-first gear rod, 88-second gear rod, 89-second brake line structure, 810-third brake line structure, 811-outside handle spindle, 812-lock core structure, 813-gear rod spring. [Specific implementation method]

[0034] See also Figure 1-Figure 19The present invention comprises a door shell 2 which is hinged in an aircraft shell 1, can rotate around a hinge center and is constrained by a first locking point mechanism 6 and a second locking point mechanism 7; the middle part of the upper end of the door shell 2 is hinged to a cross beam 12 of the aircraft shell 1, the door shell 2 can rotate around a hinge center and the hinge center is a hinge rod 21, a hinge handle assembly 4 is fixed on the hinge rod 21 and the hinge handle assembly 4 is matched with the cross beam 12 of the aircraft shell 1; the upper left end of the inner side of the door shell 2 is hinged to the right side of the arc beam 13 of the aircraft shell 1 and the door shell 2 can rotate around the hinge center, the inner side of the door shell 2 is hinged to the right side of the arc beam 13 of the aircraft shell 1 and the door shell 2 can rotate around the hinge center, the inner side of the door shell 2 is hinged to the right side of the arc beam 13 of the aircraft shell 1 and the door shell 2 can rotate around the hinge center. The upper right end of the side is connected to the longitudinal beam 11 of the aircraft shell 1 through the gas spring assembly 3; an inner door handle assembly 5 is provided at the lower left middle part of the inner side of the door shell 2, and an outer door handle assembly 8 is provided at the lower middle part of the outer side of the door shell 2. The inner door handle assembly 5 is mechanically connected to the outer door handle assembly 8, and the outer door handle assembly 8 is mechanically connected to a first locking point mechanism 6 provided at the lower right side of the door shell 2 and a second locking point mechanism 7 at the lower left side of the door shell 2. The first locking point mechanism 6 is connected to the longitudinal beam 11 of the aircraft shell 1, and the second locking point mechanism 7 is connected to the beam below the aircraft shell 1.

[0035] Specifically, the aircraft shell 1 includes an outer skin and longitudinal beams 11, transverse beams 12, and curved beams 13 arranged on the inner side of the outer skin, and the longitudinal beams 11, transverse beams 12, and curved beams 13 are used to support the outer skin.

[0036] Specifically, the gas spring assembly 3 includes a special-shaped gas spring seat 31, a gas spring 32 and a longitudinal beam gas spring seat 33. The special-shaped gas spring seat 31 is fixed to the upper right end of the inner side of the door shell 2. One end of the gas spring 32 is hinged on the special-shaped gas spring seat 31 and the gas spring 32 can rotate around the hinge center. The other end of the gas spring 32 is hinged on the longitudinal beam gas spring seat 33 and the gas spring 32 can rotate around the hinge center. The longitudinal beam gas spring seat 33 is fixed on the longitudinal beam 11 of the aircraft shell 1.

[0037] Specifically, the hinge handle assembly 4 includes a hinge handle 41, a handle clamp 42 and a handle seat 43. The handle seat 43 is fixed to the hinge rod 21 at the upper end of the door shell 2. The hinge handle 41 is hinged on the handle seat 43 and the hinge handle 41 can rotate around the hinge center. The upper end of the hinge handle 41 is fitted in the handle clamp 42, and the handle clamp 42 is fixed to the crossbeam 12.

[0038] Specifically, the inner door handle assembly 5 includes an inner handle 51, an inner handle shell 52, a first brake line structure 53, an inner handle coil spring 54, an inner handle main shaft 55, a connecting arm 56 and a connecting arm shaft 57). The inner handle shell 52 is fixed to the lower middle part of the outer side of the hatch shell 2, and the inner handle main shaft 55 is installed in the inner handle shell 52. The inner handle main shaft 55 is mounted with the inner handle 51 and the inner handle coil spring 54. One end of the inner handle coil spring 54 cooperates with the inner handle 51, and the other end cooperates with the inner handle shell 52. The inner handle main shaft 55 is symmetrically installed with connecting arms 56, and the other end of the connecting arm 56 is fixed on the connecting arm shaft 57. The upper end of the connecting arm shaft 57 is fixed to one end of the first brake line structure 53, and the other end of the first brake line structure 53 is connected to the outer door handle assembly 8.

[0039] Specifically, the first locking point mechanism 6 includes a longitudinal beam connecting seat 61, a first locking point mechanism housing 62, a first locking fork 63, a first locking fork main shaft 64, a first locking fork coil spring 65, a first dial 66, a first dial shaft 67, a first dial coil spring 68, an indication sector tooth 69 and an indication gear shaft 610. The first locking point mechanism housing 62 is installed at the lower right part of the inner side of the door housing 2. The first locking fork 63 is installed inside the first locking point mechanism housing 62 through the first locking fork main shaft 64. The first locking fork coil spring 65 is mounted on the first locking fork main shaft 64. One end of the first locking fork coil spring 65 is connected to the first locking fork 63 and the other end is connected to the first locking point mechanism housing 62. The first locking point mechanism housing 62 is installed inside the first locking point mechanism housing 62 through the first dial shaft 64. The shaft 67 is installed with a first dial 66, and the first dial shaft 67 is mounted with a first dial coil spring 68, one end of the first dial coil spring 68 is connected to the first dial 66, and the other end is connected to the first locking point mechanism housing 62, the first dial 66 is meshed with the first locking fork 63, and the first dial 66 is connected to the end of the second brake line structure 89 of the outward door handle assembly 8; the first locking fork 63 is provided with an opening and the opening is used to constrain the longitudinal beam connecting seat 61, and the longitudinal beam connecting seat 61 is fixed to the longitudinal beam 11 of the aircraft housing 1; the end of the first locking fork main shaft 64 is fixed with an indicating sector tooth 69, the indicating sector tooth 69 is a sector gear and meshes with the indicating gear shaft 610, and the indicating gear shaft 610 is fixed in the first locking point mechanism housing 62.

[0040] Specifically, the second locking point mechanism 7 includes an aircraft shell connecting component 71, a second locking point mechanism shell 72, a second locking fork 73, a second locking fork spindle 74, a second locking fork coil spring 75, a second dial 76, a second dial shaft 77 and a second dial coil spring 78. The second locking point mechanism shell 72 is installed at the bottom end of the left part of the cabin door shell 2. The second locking fork 73 is installed in the second locking point mechanism shell 72 through the second locking fork spindle 74. The second locking fork 73 is sleeved with a second locking fork coil spring 75. One end of the second locking fork coil spring 75 is connected to the second locking fork 73, and the other end is connected to the second locking point mechanism The second locking fork 73 is connected to the second dial wheel 76 and the third brake line structure 810 of the outer door handle assembly 8; an opening is provided on the second locking fork 73 and the opening is used to constrain the aircraft shell connecting assembly 71, and the aircraft shell connecting assembly 71 is fixed to the aircraft shell 1.

[0041] Specifically, the outside door handle assembly 8 includes an outside handle 81, an outside handle shell 82, a short rod 83, a push rod 84, a spring 85, a push rod seat 86, a first gear rod 87, a second gear rod 88, a second brake line structure 89, a third brake line structure 810, an outside handle main shaft 811, a lock core structure 812 and a gear rod coil spring 813. The outside handle shell 82 is fixed to the lower middle part of the outer side of the hatch shell 2, and the outside handle 81 is installed in the outside handle shell 82 through the outside handle main shaft 811. The upper end of the outside handle main shaft 811 is hinged with a short rod 83, and the other end of the short rod 83 is hinged with a push rod 84. A spring 85 is mounted on the push rod 84, and the other end of the push rod 84 passes through the push rod seat 86 fixed on the outside handle shell 82 and is opposite to the upper end of the second gear rod 88; the first gear rod 87 and the second gear rod 88 that are meshed with each other are installed on the front side of the outside handle shell 82. 8. The first gear rod 87 is a rod with a toothed upper end, and the lower end of the first gear rod 87 is connected to the second brake line structure 89, and the other end of the second brake line structure 89 is connected to the first locking point mechanism 6. The second gear rod 88 is a rod with a toothed middle part, and the upper end of the second gear rod 88 is connected to the first brake line structure 53 of the inner door handle assembly 5, and the lower end of the second gear rod 88 is connected to the third brake line structure 810, and the other end of the third brake line structure 810 is connected to the second locking point mechanism 7; the gear rod coil spring 813 is coaxially fixed to the toothed portion of the second gear rod 88, and one end of the gear rod coil spring 813 is fixed to the second gear rod 88 and the other end is fixed to the outer handle shell 82; a lock core structure 812 is fixed in the outer handle shell 82 and the lock core structure 812 is rotatable, and the lock tongue of the lock core structure 812 fits in the groove on the outer handle 81.

[0042] Working process of the present invention:

[0043] The present invention is a kind of aircraft emergency door in the working process, and is described in conjunction with the accompanying drawings. The door shell 2 is locked by the first locking point mechanism 6, the second locking point mechanism 7 and the top hinge handle assembly 4. When the aircraft encounters an emergency, the pilot opens the inner handle 51, and the action of the inner handle 51 is transmitted to the second gear rod 88 of the outer door handle assembly 8 through the first brake line structure 53, thereby simultaneously making the second brake line structure 89 and the third brake line structure 810 linked, and the first locking point mechanism 6 and the second locking point mechanism 7 will be unlocked; then the top hinge handle 41 is pulled open, and the hinge handle assembly 4 will automatically be unfastened from the door joint, and the jettisoning function can be realized through the thrust of the gas spring 32.

[0044] The above embodiments are intended to illustrate the present invention, not to limit the present invention. Any solution that is a simple transformation of the present invention belongs to the protection scope of the present invention.

Claims

1. An aircraft emergency door, Features: It comprises a door shell hinged in the aircraft shell, rotatable around the hinge center and constrained by a first locking point mechanism and a second locking point mechanism; the middle part of the upper end of the door shell is hinged to the cross beam of the aircraft shell, the door shell can rotate around the hinge center and the hinge center is a hinge rod, a hinge handle assembly is fixed on the hinge rod and the hinge handle assembly cooperates with the cross beam of the aircraft shell; the upper left end of the inner side of the door shell is hinged to the right side of the arc-shaped beam of the aircraft shell and the door shell can rotate around the hinge center, and the upper right end of the inner side of the door shell is connected to the longitudinal beam of the aircraft shell through a gas spring assembly; an inner door handle assembly is provided at the lower left middle part of the inner side of the door shell, and an outer door handle assembly is provided at the lower middle part of the outer side of the door shell, the inner door handle assembly is mechanically connected to the outer door handle assembly, the outer door handle assembly is mechanically connected to the first locking point mechanism provided at the lower right side of the door shell and the second locking point mechanism provided at the lower left side of the door shell, the first locking point mechanism is connected to the longitudinal beam of the aircraft shell, and the second locking point mechanism is connected to the beam at the lower side of the aircraft shell; The inner handle main shaft of the inner opening door handle assembly is symmetrically installed with connecting arms above and below, the other end of the connecting arm is fixed on the connecting arm shaft, one end of the first brake wire structure is fixed to the upper end of the connecting arm shaft, the other end of the first brake wire structure is connected to the upper end of the second gear rod of the outer opening door handle assembly, the lower end of the second gear rod is connected to the third brake wire structure, the other end of the third brake wire structure is connected to the second dial wheel of the second locking point mechanism; the second gear rod is meshed with the first gear rod, the lower end of the first gear rod is connected to the second brake wire structure, and the other end of the second brake wire structure is connected to the first dial wheel of the first locking point mechanism.

2. An aircraft emergency door as claimed in claim 1, Features: The aircraft shell comprises an outer skin and longitudinal beams, transverse beams and arc-shaped beams arranged on the inner side of the outer skin, wherein the longitudinal beams, transverse beams and arc-shaped beams are used to support the outer skin.

3. An aircraft emergency door as claimed in claim 1, Features: The gas spring assembly includes a special-shaped gas spring seat, a gas spring and a longitudinal beam gas spring seat. The special-shaped gas spring seat is fixed to the upper right end of the inner side of the door shell. One end of the gas spring is hinged on the special-shaped gas spring seat and the gas spring can rotate around the hinge center. The other end of the gas spring is hinged on the longitudinal beam gas spring seat and the gas spring can rotate around the hinge center. The longitudinal beam gas spring seat is fixed on the longitudinal beam of the aircraft shell.

4. An aircraft emergency door as claimed in claim 1, Features: The hinge handle assembly includes a hinge handle, a handle clamp and a handle seat. The handle seat is fixed on a hinge rod at the upper end of the door shell. The hinge handle is hinged on the handle seat and can rotate around the hinge center. The upper end of the hinge handle fits in the handle clamp, and the handle clamp is fixed on the crossbeam.

5. An aircraft emergency door as claimed in claim 1, Features: The inner door handle assembly includes an inner handle, an inner handle shell, a first brake line structure, an inner handle coil spring, an inner handle main shaft, a connecting arm and a connecting arm shaft. The inner handle shell is fixed to the lower middle part of the outer side of the hatch shell, and the inner handle main shaft is installed in the inner handle shell. The inner handle main shaft is mounted with the inner handle and the inner handle coil spring. One end of the inner handle coil spring cooperates with the inner handle, and the other end cooperates with the inner handle shell.

6. An aircraft emergency door as claimed in claim 1, Features: The first locking point mechanism comprises a longitudinal beam connecting seat, a first locking point mechanism housing, a first locking fork, a first locking fork main shaft, a first locking fork coil spring, a first dial wheel, a first dial wheel shaft, a first dial wheel coil spring, an indicating sector tooth and an indicating gear shaft, the first locking point mechanism housing is installed at the lower right part of the inner side of the door housing, a first locking fork is installed inside the first locking point mechanism housing through the first locking fork main shaft, a first locking fork coil spring is mounted on the first locking fork main shaft, one end of the first locking fork coil spring is connected to the first locking fork, and the other end is connected to the first locking point mechanism housing; the first locking point mechanism housing is installed inside the first dial wheel A first dial is installed on the shaft, and a first dial coil spring is mounted on the first dial shaft, one end of the first dial coil spring is connected to the first dial, and the other end is connected to the first locking point mechanism housing, the first dial is meshed with the first locking fork, and the first dial is connected to the end of the second brake line structure of the outward door handle assembly; an opening is provided on the first locking fork and the opening is used to constrain the longitudinal beam connecting seat, and the longitudinal beam connecting seat is fixed to the longitudinal beam of the aircraft housing; an indicating sector tooth is fixed to the end of the main shaft of the first locking fork, the indicating sector tooth is a sector gear and meshed with the indicating gear shaft, and the indicating gear shaft is fixed in the first locking point mechanism housing.

7. An aircraft emergency door as claimed in claim 1, Features: The second locking point mechanism comprises an aircraft shell connecting assembly, a second locking point mechanism shell, a second locking fork, a second locking fork main shaft, a second locking fork coil spring, a second dial wheel, a second dial wheel shaft and a second dial wheel coil spring, the second locking point mechanism shell is installed at the bottom end of the left part of the cabin door shell, the second locking fork is installed in the second locking point mechanism shell through the second locking fork main shaft, the second locking fork is sleeved with the second locking fork, one end of the second locking fork coil spring is connected with the second locking fork, and the other end is connected with the second locking point mechanism shell; the second dial wheel is installed in the second locking point mechanism shell through the second dial wheel shaft, the second dial wheel shaft is sleeved with the second dial wheel coil spring, one end of the second dial wheel coil spring is connected with the second dial wheel, and the other end is connected with the second locking point mechanism shell, the second dial wheel is meshed with the second locking fork, and the second dial wheel is connected to the end of the third brake line structure of the outward opening door handle assembly; the second locking fork is provided with an opening and the opening is used to constrain the aircraft shell connecting assembly, and the aircraft shell connecting assembly is fixed to the aircraft shell.

8. An aircraft emergency door as claimed in claim 1, Features: The outside door handle assembly includes an outside handle, an outside handle shell, a short rod, a push rod, a spring, a push rod seat, a first gear rod, a second gear rod, a second brake line structure, a third brake line structure, an outside handle spindle, a lock core structure and a gear rod coil spring. The outside handle shell is fixed to the lower middle part of the outer side of the hatch shell, and an outside handle is installed in the outside handle shell through the outside handle spindle. The upper end of the outside handle spindle is hinged with a short rod, and the other end of the short rod is hinged with a push rod. A spring is mounted on the push rod, and the other end of the push rod passes through the push rod fixed on the outside handle shell. The rear of the seat is opposite to the upper end of the second gear rod; the first gear rod and the second gear rod that are meshed with each other are installed on the front side of the outer handle shell, the first gear rod is a rod with teeth on the upper end, and the second gear rod is a rod with teeth in the middle; a gear rod coil spring is coaxially fixed to the teeth of the second gear rod, one end of the gear rod coil spring is fixed to the second gear rod, and the other end is fixed to the outer handle shell; a lock core structure is fixed in the outer handle shell and the lock core structure is rotatable, and the lock tongue of the lock core structure fits in the groove on the outer handle.

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