JP3964702B2 - Aircraft cockpit door latching device - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a latch device used for a cockpit door (cockpit door) or the like provided between a cabin (cabin) and a cockpit (cockpit) of an aircraft.
[0002]
[Prior art]
FIG. 1 shows an outline of a cockpit door. The cockpit door 1 is required to be kept closed during flight or the like and cannot be opened and closed easily from the viewpoint of security. For this purpose, for example, an electronic lock mechanism or the like is used, and the latch device 2 is electrically released by driving a password into the keypad 3.
During the flight, the aircraft is preloaded inside and adjusted to an internal pressure higher than the external pressure.
[0003]
[Problems to be solved by the invention]
However, if a depressurization occurs on the cockpit side 4 for some reason, a differential pressure is generated with respect to the pressure on the cabin 5 side. In order to release this differential pressure, it is necessary to open the cockpit door 1 to the cockpit 4 side and decompress the cabin 5.
The present invention provides a latch device effective for the above-described measures.
[0004]
[Means for Solving the Problems]
The cockpit door latch device of the present invention includes, as basic means, a handle provided on the cockpit side of the door panel, a handle unit having a bolt that is operated by the handle and is engaged with and disengaged from a catch provided on the door frame, A bolt disengagement mechanism is provided that detects the air pressure in the passenger compartment and forcibly disengages the bolt from the catch when the air pressure in the cockpit decreases.
[0005]
The housing is fixed to the door panel, the base is pivotably attached to the housing around the end on the catch side of the housing, the handle is pivotally attached to the base, and the handle is interlocked with the handle. Bolts, a stopper attached to the housing and engaged / disengaged at an end opposite to the fulcrum of the base, a cylinder portion provided in the housing, a piston member inserted into the cylinder portion, and an operation of the piston member A bolt release mechanism for releasing the engagement of the stopper base is provided.
[0006]
The stopper is rotatably supported by a pin with respect to the housing. One end of the stopper is engaged with and disengaged from the base, and the other end is engaged and disengaged with a link arm interlocking with the piston member.
[0007]
DETAILED DESCRIPTION OF THE INVENTION
2 is a front view of the latch device of the present invention, FIG. 3 is a right side view, FIG. 4 is a bottom view, FIG. 5 is a top view, and FIG.
[0008]
A latch device generally indicated by reference numeral 10 has a housing 12 fixed to a cockpit door. A handle unit 20 is attached to the inside of the housing 12. The handle unit 20 includes a base 22 and a handle 24 that is rotatably attached to the base 22.
A cam 26 is attached to the handle 24, and the bolt 28 supported in the base 22 slides as the cam 26 rotates. The bolt 28 is engaged and disengaged with respect to a catch provided on the frame side of the opening of the door.
[0009]
The base 22 is supported by a pin 30 so as to be rotatable in the vicinity of the catch side end.
A groove 23 is provided at the end of the base 22 opposite to the bolt, and one end 60 a of the stopper 60 is normally engaged with this groove, and the base 22 is stored in the housing 12. Keep.
[0010]
The stopper 60 is supported by a pin 62 so as to be pivotable with respect to the housing 12. A cylinder portion 14 is provided on the surface of the housing 12 facing the cabin 5 side. A piston member 40 is inserted into the cylinder portion 14, and the open end of the cylinder portion 14 is sealed with a cap 15. The cap 15 has a suitably shaped opening 15a.
[0011]
A piston rod 42 is erected at the center of the piston member 40, and the tip of the piston rod 42 abuts on one end of the link arm 50.
The piston member 40 is constantly biased toward the cap 15 by a spring 44. The link arm 50 rotates about the pin 52 but is urged by a spring 44 in a direction in which the link arm 50 is always in contact with the piston rod 42.
Therefore, the link arm 50 is engaged with the stopper 60, and the stopper 60 is engaged with the base 22 of the handle unit to keep the base 22 at a position in the housing 12.
[0012]
In this state, it is possible to open the cockpit door by operating the handle 24 only from the cockpit 4 side to remove the bolt 28 from the catch.
When pressure is reduced on the cockpit 4 side for some reason in a state where the cockpit door is closed, a differential pressure is generated between the preloaded cabin 5 side.
When this differential pressure is generated, the piston member 40 is pushed into the cylinder portion 14 against the spring 44 by the pressure of the cabin on the high pressure side.
[0013]
This operation is transmitted to the link arm 50 via the piston rod 42 and pushes the link arm 50. By this operation, the link arm 50 rotates around the pin 52 and disengages from the stopper member 60.
By this operation, the stopper member rotates about the pin 62 to release the base member 22.
[0014]
The base member 22 is rotated about the pin 30 by the cam of the spring 34, and is rotated to the position of the two-dot chain line in FIG. 2 by the pressure acting on the cockpit door.
By this action, the tip of the bolt 28 is released from the catch, the cockpit door is opened to the cockpit side, and the cabin is decompressed.
[0015]
Hereinafter, the main members constituting the latch device of the present invention will be described in detail.
7A and 7B show details of the bolt, in which FIG. 7A shows a planar shape of the bolt 28 and FIG. 7B shows a side shape. The bolt 28 has a small width at the front end and a large width at the rear half, and is formed in a bifurcated shape. A member 28a made of a hard material is driven into the tip, and the bottomed hole 28c receives a spring for extrusion.
The slit portion 28 b has a function of guiding the bolt 28.
[0016]
FIG. 8 shows details of the stopper, wherein (a) shows the planar shape of the stopper 60 and (b) shows the side surface shape.
The stopper 60 swings with respect to the housing around the pin 62. A small-diameter roller 64a is attached to the end portion 64 that contacts the link arm, and a small-diameter roller 66a is attached to the end portion 66 that engages the base side of the handle unit to reduce friction with the mating member. ing.
[0017]
FIG. 9 shows details of the link arm, (a) shows the planar shape of the link arm 50, and (b) shows the side surface shape.
The link arm 50 is rotatably supported with respect to the housing by a pin 52, and a spring force is applied by a spring 54 in a direction in which the tip end portion 50a of the link arm 50 is always in contact with the piston rod.
A claw 56 is formed in the vicinity of the pin 52 of the link arm, and this claw 56 engages with one end of the stopper 60.
[0018]
In a state where the bolt is engaged with the catch, even if the cockpit door is pushed from the cabin side, the stopper 60 tries to rotate around the pin 62 and is more firmly engaged with the base that supports the bolt. Inadvertently, the cockpit door is prevented from opening.
[0019]
That is, when a force is applied to the bolt 28, the link arm 50 rotates in a direction in which the engagement increases due to a shift in the position of the pin 52 that is the center of rotation and the position of the claw 56 that is the point of action of the force from the stopper 60. Therefore, the base 22 is not opened due to an increase in the load on the bolt 28. The base 22, the stopper 60, and the link arm 50 each have a force point, a reaction force point, and a rotation center, and the load entering the bolt 28 becomes the final reaction force of the link arm 50 and balances. In this system, the final reaction force at the link arm 50 is reduced to an expected magnitude in three stages. As a result, even when the differential pressure to be sensed is very small, the whole can be set in accordance with the thrust of the piston member 40.
When the link arm 50 releases the base 22 by the piston member 40, the base 22 rotates and opens without any restriction.
[0020]
【The invention's effect】
The latch device for a cockpit door according to the present invention is configured as described above. Since the latch operation handle is provided only on the cockpit side, the cockpit door is opened and closed only from the cockpit side.
When decompression occurs in the cockpit, the piston operates to quickly and smoothly remove the bolt from the catch, open the cockpit door to the cockpit side, and decompress the cabin.
Since this latch device is composed of only mechanical parts and no electrical parts are used, it has a long life and does not require maintenance.
It has also been confirmed that the time from when the pressure difference occurs until the opening is short enough to satisfy the request.
[Brief description of the drawings]
FIG. 1 is a perspective view of a cockpit door to which the present invention is applied.
FIG. 2 is a front view of the latch device of the present invention.
FIG. 3 is a right side view of the latch device of the present invention.
FIG. 4 is a bottom view of the latch device of the present invention.
FIG. 5 is a top view of the latch device of the present invention.
6 is an AA arrow view of FIG. 5;
FIG. 7 is a detailed view of a bolt.
FIG. 8 is a detailed view of a stopper.
FIG. 9 is a detailed view of a link arm.
[Explanation of symbols]
1 Cockpit door 10 Latch device 12 Housing 20 Handle unit 22 Base 24 Handle 26 Cam 30 Pin 40 Piston member 42 Piston rod 50 Link arm 60 Stopper

Claims (2)

A hinge-type cockpit door latch device that is provided between an aircraft cabin and a cockpit and opens to the cockpit side. The handle is provided on the cockpit side of the door panel, and is operated by the handle to the door frame. A handle unit having a bolt engaged with and disengaged from a catch provided , and a bolt disengagement mechanism for forcibly removing the bolt from the catch by detecting the air pressure in the cabin when the air pressure in the cockpit decreases. The detachment mechanism includes a housing fixed to the door panel, a base that is pivotably attached to the housing around a catch side end of the housing, a handle that is pivotally attached to the base, and a handle. A bolt that is linked to the housing, a stopper that is attached to the housing and is engaged with and disengaged from the end opposite to the fulcrum of the base, and a housing. A cylinder portion that is, a piston member which is inserted into the cylinder portion, the latch device of the cockpit door having the function of releasing the base of the engagement of the stopper by movement of the piston member. Stopper is rotatably supported by a pin to the housing, one end is disengaged relative to the base, the other end is an aircraft according to claim 1 wherein the disengaged to the link arm interlocked with the piston member Cockpit door latch device.

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