A locking device for a lightweight composite aircraft cabin door

Abstract

The present invention relates to a locking device for a light composite aircraft cabin door, comprising an aircraft fuselage, a cockpit and a passenger cabin are arranged at the front of the fuselage, a cabin cover and a cabin door are respectively installed on the cockpit and the passenger cabin, the cabin cover comprises a cover body and a cabin cover frame, the cabin door comprises a door body and a cabin door frame, the front frame of the cabin cover frame is hinged on the fuselage, and the upper frame of the cabin door frame is hinged on the fuselage; control handles are respectively installed on the left side of the cabin door frame and the left side of the cabin cover frame, and the left and right ends of the rear frame of the cabin cover frame are embedded with cabin cover locking pins, and the cabin cover locking pins are connected to the control handle through a cable assembly; the front and rear ends of the lower frame of the cabin door frame are respectively embedded with cabin door locking pins, and the cabin door locking pins are connected to the control handle through a cabin cover locking pin through a cable assembly. The locking device on the cabin door of the aircraft has a simple and compact structure, and the operation of the locking structure is simple and convenient, which is convenient for opening and closing the cabin door, and at the same time, the cabin door has good safety in closing.

Description

Technical Field

[0001] The invention relates to the technical field of locking mechanisms for light aircraft cabin doors, and more particularly to a locking device for light composite aircraft cabin doors. Background Art

[0002] Aircraft cabin doors have a direct impact on the safety of light aircraft. Cabin doors are directly operated by pilots and passengers, and are also passages for people to enter and exit. Their ease of use and safety after closing and locking directly affect the aircraft's user experience and the safety of pilots and passengers. Therefore, the design of the cabin door's locking structure should, under the premise of meeting the requirements of the World Bank's terms, reduce the difficulty of installation, commissioning and maintenance according to the structural characteristics of the aircraft, reduce the weight of the structure, reduce the difficulty of operation, and improve safety and aesthetics. Summary of the invention

[0003] The purpose of the present invention is to address the deficiencies of the prior art and to provide a locking device for a lightweight composite aircraft cabin door. The locking device has a simple and compact structure, and the locking structure is easy and convenient to operate, making it convenient to open and close the cabin door, while having good safety when closing the cabin door.

[0004] A locking device for a cabin door of a light composite aircraft comprises a fuselage of the aircraft, wherein a cockpit and a passenger cabin are arranged at the front of the fuselage, a cabin cover is installed on the cockpit, a cabin door is installed on one side of the passenger cabin, the cabin cover comprises a cover body and a cabin cover frame fixed to an outer ring of the cover, the cabin door comprises a door body and a cabin door frame fixed to an outer ring of the door, a front frame of the cabin cover frame is hinged to the fuselage through a hinge seat, and an upper frame of the cabin door frame is hinged to the fuselage through a hinge; control handles are respectively installed on the left side of the cabin door frame and the left side of the cabin cover frame, a cabin cover locking pin is embedded at the left and right ends of the rear frame of the cabin cover frame, and the cabin cover locking pin is connected to the control handle through a cable assembly; cabin door locking pins are respectively embedded at the front and rear ends of the lower frame of the cabin door frame, and the cabin door locking pin is connected to the control handle through a cabin cover locking pin through a cable assembly;

[0005] The hatch cover lock pin includes a first positioning sleeve, which is fixed in the hatch cover frame by screws, a first locking pin is inserted in the first positioning sleeve, and the rear end of the first positioning sleeve extends out of the hatch cover frame and is inserted in the stopper; the door lock pin includes a second positioning sleeve, which is fixed to the front and rear ends of the door frame by screws, a second locking pin is inserted in the second positioning sleeve, and the second locking pins at the front and rear ends of the door frame extend out of the door frame and are inserted in the stopper, and the stopper is inserted and fixed to the fuselage;

[0006] The control handle is composed of an inner handle and an outer handle, the inner handle comprises a lock frame fixed in the hatch cover frame and the hatch door frame, the upper and lower sides of the lock frame are formed with a left-extending bracket plate, an arc-shaped wrench is inserted in the lock frame, and a limit pad opposite to the wrench is formed at the front end of the lock frame, a vertical hinge shaft is inserted and fixed at the rear end of the wrench, both ends of the hinge shaft are inserted in the bracket plate, a longitudinal guide groove is formed on the bracket plate on the front side of the hinge shaft, a support rod extending backward is formed at the rear end of the bracket plate, a vertical positioning column is inserted and fixed at the rear end of the support rod, a support ear is formed at the rear end of the support ear, a vertical pin is inserted and fixed at the rear end of the support ear, the front end of the gas spring is inserted and sleeved on the pin, and the rear end of the gas spring is inserted and sleeved on the positioning column; a support shaft is inserted and fixed in the wrench, and an inclined connecting rod is fixed on the support shaft sleeve, a guide shaft is inserted at the front end of the connecting rod, and both ends of the guide shaft are inserted in the guide groove of the bracket plate;

[0007] The hatch cover frame and the hatch door frame are formed with a downwardly concave handle groove, and the outer handle is inserted in the handle groove. The outer handle includes a horizontal L-shaped handle, and a vertical insertion shaft is fixed at one end of the handle. The upper end of the insertion shaft passes through the handle groove and is inserted and fixed in the hinge shaft;

[0008] The cable assembly includes a pull rope inserted in the hatch cover frame and the hatch door frame, one end of the pull rope is fixed with a connector, the connector is inserted into the guide shaft or pin shaft of the inner handle, and the other end of the pull rope is fixed to the second lock pin or the first lock pin.

[0009] Preferably, both ends of the pull rope on the cable assembly are plugged and fixed with screw joints, the screw joint at one end of the pull rope is screwed into the connecting head, and the screw joint at the other end is screwed onto the second locking pin or the first locking pin.

[0010] Preferably, the first locking pin and the second locking pin comprise a cylindrical shaft body, one end of the shaft body is formed with a conical guide head, and the other end of the shaft body is inserted into the first positioning sleeve or the second positioning sleeve;

[0011] The inner walls of the first positioning sleeve and the second positioning sleeve are both formed with a retaining ring, and a spring is inserted into the pull rope of the cable assembly. The spring is inserted into the first positioning sleeve and the second positioning sleeve, one end of the spring presses against the retaining ring, and the other end presses against the first locking pin and the second locking pin shaft.

[0012] Preferably, the diameters of the shaft bodies on the first locking pin and the second locking pin are respectively equal to the inner diameters of the first positioning sleeve and the second positioning sleeve.

[0013] Preferably, a gas support rod is hingedly connected to the middle portion of the rear frame of the door frame, and the upper end of the gas support rod is hingedly connected to the inner wall of the fuselage entering the cabin.

[0014] Preferably, the inner handle and the outer handle are fixedly connected in such a manner that the insertion shaft on the outer handle is inserted into the hinge shaft of the inner handle and is fixed with a cylindrical pin, and both ends of the cylindrical pin pass through the hinge shaft and are inserted into the wrench.

[0015] Preferably, a vertical buckle plate is formed on the left side of the handle on the outer handle.

[0016] The beneficial effects of the present invention are:

[0017] The locking device on the aircraft cabin door has a simple and compact structure, and the locking structure is simple and convenient to operate, which facilitates the opening and closing of the cabin door, and at the same time, the cabin door has good safety when closed. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the structure of a light aircraft;

[0019] Figure 2 It is a structural schematic diagram of the hatch cover part of the present invention;

[0020] Figure 3 It is an exploded schematic diagram of the locking components in the hatch cover of the present invention;

[0021] Figure 4 It is a structural schematic diagram of the hatch part of the present invention;

[0022] Figure 5 It is an exploded schematic diagram of the locking components in the hatch of the present invention;

[0023] Figure 6 It is a front view schematic diagram of the upper outer handle of the present invention;

[0024] Figure 7 is a side view schematic diagram of the upper outer handle of the present invention;

[0025] Figure 8 It is a three-dimensional schematic diagram of the upper inner handle of the present invention in an open state;

[0026] In the figure: 1. fuselage; 2. hatch cover; 21. cover body; 22. hatch cover frame; 3. hatch door; 31. door body; 22. hatch door frame; 4. stopper; 5. control handle; 51. inner handle; 52. outer handle; 6. hatch cover lock pin; 7. hatch door lock pin; 8. cable assembly; 9. hatch door closing micro switch; 10. hinge; 11. gas support rod. DETAILED DESCRIPTION

[0027] Example: See Figures 1 to 8As shown, a locking device for a cabin door of a lightweight composite aircraft comprises a fuselage 1 of an aircraft, wherein a cockpit and a passenger cabin are arranged at the front of the fuselage 1, a cabin cover 2 is installed on the cockpit, a cabin door 3 is installed on one side of the passenger cabin, the cabin cover 2 comprises a cover body 21 and a cabin cover frame 22 fixed to the outer circle of the cover body 21, the cabin door 3 comprises a door body 31 and a cabin door frame 32 fixed to the outer circle of the door body 31, the front frame of the cabin cover frame 22 is hinged to the fuselage 1 through a hinge seat, and the upper frame of the cabin door frame 32 is hinged to the fuselage 1 through a hinge 10; control handles 5 are respectively installed on the left side of the cabin door frame 32 and the left side of the cabin cover frame 22, and cabin cover locking pins 6 are embedded at the left and right ends of the rear frame of the cabin cover frame 22, and the cabin cover locking pins 6 are connected to the control handle 5 through a cable assembly 8; cabin door locking pins 7 are respectively embedded at the front and rear ends of the lower frame of the cabin door frame 32, and the cabin door locking pin 7 is connected to the control handle 5 through the cabin cover locking pin 6 through the cable assembly 8;

[0028] The hatch cover lock pin 6 comprises a first positioning sleeve 61, which is fixed in the hatch cover frame 22 by screws, and a first locking pin 62 is inserted in the first positioning sleeve 61, and the rear end of the first positioning sleeve 61 extends out of the hatch cover frame 22 and is inserted in the stopper 12; the door lock pin 7 comprises a second positioning sleeve 71, which is fixed to the front and rear ends of the door frame 32 by screws, and a second locking pin 72 is inserted in the second positioning sleeve 71, and the second locking pins 72 at the front and rear ends of the door frame 32 extend out of the door frame 32 and are inserted in the stopper 12, and the stopper 12 is inserted and fixed to the fuselage 1;

[0029] The control handle 5 is composed of an inner handle 51 and an outer handle 52. The inner handle 51 includes a lock frame 511 fixed in the hatch cover frame 22 and the hatch door frame 32. The upper and lower sides of the lock frame 511 are formed with a left-extending bracket plate 5111. An arc-shaped wrench 512 is inserted in the lock frame 511. The front end of the lock frame 511 is formed with a limiting pad 5113 opposite to the wrench 512. The rear end of the wrench 512 is plugged and fixed with a vertical hinge shaft 513. The two ends of the hinge shaft 513 are plugged on the bracket plate 5111. The bracket plate 5111 on the front side of the hinge shaft 513 is formed with a longitudinal guide groove 5112. The rear end of the wrench 511 is formed with a support rod 5114 extending backward, and the rear end of the support rod 5114 is plugged and fixed with a vertical positioning column 517. The rear end of the wrench 512 is formed with a support ear 5121, and the rear end of the support ear 5121 is plugged and fixed with a vertical pin shaft. The front end of the gas spring 518 is inserted and sleeved on the pin shaft, and the rear end of the gas spring 518 is inserted and sleeved on the positioning column 517; the wrench 512 is plugged and fixed with a support shaft 516, and the support shaft 516 is plugged and fixed with an inclined connecting rod 515, and the front end of the connecting rod 515 is plugged with a guide shaft 514, and both ends of the guide shaft 514 are plugged into the guide groove 5112 of the bracket plate 5111;

[0030] The hatch cover frame 22 and the hatch door frame 32 are formed with a downwardly concave handle groove, and the outer handle 52 is inserted in the handle groove. The outer handle 52 includes a horizontal L-shaped handle 521, and a vertical insertion shaft 522 is fixed at one end of the handle 521. The upper end of the insertion shaft 522 passes through the handle groove and is inserted and fixed in the hinge shaft 513.

[0031] The cable assembly 8 includes a pull rope inserted into the hatch cover frame 22 and the hatch door frame 32, one end of the pull rope is fixed with a connector 82, the connector 82 is inserted into the guide shaft 514 or the pin shaft of the inner handle 51, and the other end of the pull rope is fixed to the second locking pin 72 or the first locking pin 62.

[0032] The two ends of the pull rope on the cable assembly 8 are plugged and fixed with screw joints 81. The screw joint 81 at one end of the pull rope is screwed into the connector 82, and the screw joint 81 at the other end is screwed onto the second locking pin 72 or the first locking pin 62.

[0033] The first locking pin 62 and the second locking pin 72 include a cylindrical shaft body, one end of which is formed with a conical guide head, and the other end of which is inserted into the first positioning sleeve 61 or the second positioning sleeve 71;

[0034] The inner walls of the first positioning sleeve 61 and the second positioning sleeve 71 are both formed with retaining rings, and a spring is inserted into the pull rope of the cable assembly 8. The spring is inserted into the first positioning sleeve 61 and the second positioning sleeve 71, and one end of the spring presses against the retaining ring and the other end presses against the shaft of the first locking pin 62 and the second locking pin 72.

[0035] The diameters of the shafts on the first locking pin 62 and the second locking pin 72 are respectively equal to the inner diameters of the first positioning sleeve 61 and the second positioning sleeve 71 .

[0036] A gas support rod 11 is hinged to the middle of the rear frame of the door frame 32 , and the upper end of the gas support rod 11 is hinged to the inner wall of the fuselage 1 entering the cabin.

[0037] The inner handle 51 and the outer handle 52 are fixedly connected in such a manner that the insertion shaft 522 on the outer handle 52 is inserted into the hinge shaft 513 of the inner handle 51 and is fixed with a cylindrical pin, and both ends of the cylindrical pin pass through the hinge shaft 513 and are inserted into the wrench 512 .

[0038] A vertical buckle plate 523 is formed on the left side of the upper handle 521 of the outer handle 52 .

[0039] A door closing micro switch 9 opposite to the first lock pin 62 and the second lock pin 72 is fixed in the fuselage 1 between the cabin cover 2 and the cabin door 3. The door closing micro switch 9 can detect whether the first lock pin 62 and the second lock pin 72 are inserted into the fuselage 1. When the first lock pin 62 and the second lock pin 72 are not inserted into the fuselage 1, feedback is given to the driving system for alarm.

[0040] The door 3 and the fuselage 1 are provided with child locks; the four corners of the lock frame 511 are formed with screw holes 5115 .

[0041] Guide wheels are inserted and fixed at both ends of the guide shaft 514 , and the guide wheels are inserted in the guide grooves 5112 of the bracket plate 5111 .

[0042] Tooling principle: The present invention is a locking device for a cabin door of a light composite aircraft. The light aircraft is provided with a cockpit and a passenger cabin. The cockpit is designed with a hatch cover 2 that flips forward and upward, and the passenger cabin is provided with a hatch door 3 that flips upward and leftward. The locking connection part between the hatch cover 2 and the fuselage 1 is arranged at the rear side of the hatch cover 2, and a first locking pin 62 that can control forward and backward movement is designed; and the locking connection part between the cabin door 3 and the fuselage 1 is arranged at the front and rear ends of the lower side thereof, and a second locking pin 72 that can control forward and backward movement is designed. The movement of the first locking pin 62 and the second locking pin 72 are both controlled by the control handle 5;

[0043] The control handle 5 is divided into an inner handle 51 and an outer handle 52. The inner handle 51 is used to release the locking structure of the hatch cover 2 or the hatch door 3 in the cabin, and the outer handle 52 is used to release the locking structure of the hatch cover 2 or the hatch door 3 outside the cabin. Both the inner handle 51 and the outer handle 52 drive the wrench 512 in the inner handle 51 to rotate around the hinge shaft 513, and the lug 5121 on the wrench 512 moves forward. At the same time, the wrench 512 drives the guide shaft 514 to move backward through the connecting rod 515, thereby driving the pull rope on the front side of the control handle 5 to move backward and the pull rope on the rear side of the control handle 5 to move forward, so that the first lock pin 62 is retracted into the first positioning sleeve 61, and the second lock pin 72 is retracted into the second positioning sleeve 71, which is convenient for operation.

[0044] When there is no external force, the gas spring 518 will drive the wrench 512 of the inner handle 51 to reset and release the pull rope. The first locking pin 62 and the second locking pin 72 are in an extended state under the action of the springs in the first positioning sleeve 61 and the second positioning sleeve 71, thereby ensuring that the hatch 2 and the hatch door 3 are in a locked state when closed.

[0045] The embodiments are used to illustrate the present invention, but not to limit the present invention. Any person skilled in the art may modify the embodiments without violating the spirit and scope of the present invention, and therefore, the scope of protection of the present invention shall be as set forth in the claims of the present invention.

Claims

1. A locking device for a lightweight composite aircraft cabin door, comprising an aircraft fuselage (1), wherein a cockpit and a passenger cabin are provided at the front of the fuselage (1), a cabin cover (2) is installed on the cockpit, and a cabin door (3) is installed on one side of the passenger cabin, characterized in that: The hatch cover (2) comprises a cover body (21) and a hatch cover frame (22) fixed to the outer ring of the cover body (21); the hatch door (3) comprises a door body (31) and a hatch door frame (32) fixed to the outer ring of the door body (31); the front frame of the hatch cover frame (22) is hinged to the fuselage (1) through a hinge seat; the upper frame of the hatch door frame (32) is hinged to the fuselage (1) through a hinge (10); control handles (5) are respectively installed on the left side of the door frame (32) and the left side of the hatch cover frame (22); hatch cover lock pins (6) are embedded at the left and right ends of the rear frame of the hatch cover frame (22); the hatch cover lock pins (6) are connected to the control handle (5) through a cable assembly (8); hatch door lock pins (7) are respectively embedded at the front and rear ends of the lower frame of the door frame (32); the hatch door lock pin (7) and the hatch cover lock pin (6) are connected to the control handle (5) through a cable assembly (8); The hatch cover lock pin (6) comprises a first positioning sleeve (61), the first positioning sleeve (61) is fixed to the hatch cover frame (22) by screws, the first locking pin (62) is inserted into the first positioning sleeve (61), and the rear end of the first positioning sleeve (61) extends out of the hatch cover frame (22) and is inserted into the stopper (12); the door lock pin (7) comprises a second positioning sleeve (71), the second positioning sleeve (71) is fixed to the front and rear ends of the door frame (32) by screws, the second locking pin (72) is inserted into the second positioning sleeve (71), the second locking pins (72) at the front and rear ends of the door frame (32) extend out of the door frame (32) and are inserted into the stopper (12), and the stopper (12) is inserted and fixed to the fuselage (1); The control handle (5) is composed of an inner handle (51) and an outer handle (52), wherein the inner handle (51) comprises a lock frame (511) fixed in the hatch cover frame (22) and the hatch door frame (32), the upper and lower sides of the lock frame (511) are formed with a left-extending bracket plate (5111), an arc-shaped wrench (512) is inserted into the lock frame (511), a limiting pad (5113) opposite to the wrench (512) is formed at the front end of the lock frame (511), a vertical hinge shaft (513) is inserted and fixed at the rear end of the wrench (512), both ends of the hinge shaft (513) are inserted into the bracket plate (5111), a longitudinal guide groove (5112) is formed on the bracket plate (5111) on the front side of the hinge shaft (513), and the bracket plate (5111) on the front side of the hinge shaft (513) is provided with a longitudinal guide groove (5112). The rear end of the plate (5111) is formed with a support rod (5114) extending backward, the rear end of the support rod (5114) is plugged and fixed with a vertical positioning column (517), the rear end of the wrench (512) is formed with a support ear (5121), the rear end of the support ear (5121) is plugged and fixed with a vertical pin shaft, the front end of the gas spring (518) is plugged and sleeved on the pin shaft, and the rear end of the gas spring (518) is plugged and sleeved on the positioning column (517); a support shaft (516) is plugged and fixed in the wrench (512), an inclined connecting rod (515) is plugged and fixed in the support shaft (516), a guide shaft (514) is plugged at the front end of the connecting rod (515), and both ends of the guide shaft (514) are plugged in the guide groove (5112) of the bracket plate (5111); The hatch cover frame (22) and the hatch door frame (32) are formed with a downwardly recessed handle groove, and the outer handle (52) is inserted into the handle groove. The outer handle (52) includes a horizontal L-shaped handle (521), and a vertical insertion shaft (522) is fixed to one end of the handle (521). The upper end of the insertion shaft (522) passes through the handle groove and is inserted and fixed in the hinge shaft (513); The cable assembly (8) comprises a pull rope inserted into the hatch cover frame (22) and the hatch door frame (32), one end of the pull rope is fixed with a connector (82), the connector (82) is inserted into the guide shaft (514) or the pin shaft of the inner handle (51), and the other end of the pull rope is fixed to the second lock pin (72) or the first lock pin (62); The two ends of the pull rope on the cable assembly (8) are plugged and fixed with screw joints (81), the screw joint (81) at one end of the pull rope is screwed into the connector (82), and the screw joint (81) at the other end is screwed onto the second locking pin (72) or the first locking pin (62); The first locking pin (62) and the second locking pin (72) comprise a cylindrical shaft body, one end of the shaft body is formed with a conical guide head, and the other end of the shaft body is inserted into the first positioning sleeve (61) or the second positioning sleeve (71); The inner walls of the first positioning sleeve (61) and the second positioning sleeve (71) are both formed with retaining rings, and a spring is inserted into the pull rope of the cable assembly (8). The spring is inserted into the first positioning sleeve (61) and the second positioning sleeve (71), and one end of the spring is pressed against the retaining ring, and the other end is pressed against the shaft of the first locking pin (62) and the second locking pin (72).

2. The locking device for a lightweight composite aircraft cabin door according to claim 1, characterized in that: The diameters of the shaft bodies on the first locking pin (62) and the second locking pin (72) are respectively equal to the inner diameters of the first positioning sleeve (61) and the second positioning sleeve (71).

3. The locking device for a lightweight composite aircraft cabin door according to claim 1, characterized in that: A gas support rod (11) is hingedly connected to the middle portion of the rear frame of the door frame (32), and the upper end of the gas support rod (11) is hingedly connected to the inner wall of the fuselage (1) entering the passenger cabin.

4. The locking device for a lightweight composite aircraft cabin door according to claim 1, characterized in that: The inner handle (51) and the outer handle (52) are fixedly connected in such a manner that the insertion shaft (522) on the outer handle (52) is inserted into the hinge shaft (513) of the inner handle (51) and is fixed with a cylindrical pin, and both ends of the cylindrical pin pass through the hinge shaft (513) and are inserted into the wrench (512).

5. The locking device for a lightweight composite aircraft cabin door according to claim 4, characterized in that: A vertical buckle plate (523) is formed on the left side of the upper handle (521) of the outer handle (52).

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