JPH0871169A - Automatic detaching device of oxygen mask for aircraft - Google Patents

Abstract

PURPOSE: To provide an automatic detaching device which is an automatic detaching device for an oxygen mask to be worn by the crew of aircraft, such as fighter, at the time of high-altitude flying and is capable of automatically detaching the oxygen mask connected and fixed to the helmet of the crew during wearing at the time of landing on water, such as sea, in the event of emergency. CONSTITUTION: Cover plates 9 constituting a part of sheath-shaped parts of at least one of socket parts of the right and left socket parts 6 of the oxygen mask for aircraft designed to freely detachably stopper and detain spigot parts 4 mounted at the right and left of the oxygen mask 1 by inserting these spigot parts into the sheath-shaped socket parts 6 mounted at the right and left of the helmet 5 are separably composed. These cover plates 9 are automatically separated and expelled at the time of landing on the water, such as sea, by which the state of stoppering and detaining the spigot parts 4 into the socket parts 6 is released and the oxygen mask 1 is automatically detached from the helmet 5.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for automatically removing an oxygen mask worn by an occupant of an aircraft such as a fighter during high altitude flight. More specifically, the present invention relates to an automatic detaching device for automatically detaching an oxygen mask, which is connected and fixed to a crew member's helmet when worn, from the helmet when the water hits the sea or the like in an emergency.

[0002]

2. Description of the Related Art In general, an oxygen mask for an aircraft as described above is detachably connected and fixed to a helmet through a so-called bayonet type fixing device so that the oxygen mask can be easily and quickly attached and detached. There is known a fixing device for inserting and fixing the insertion parts attached to the left and right of the oxygen mask into the sheath-shaped receiving parts attached to the left and right of the helmet to prevent them from coming off (for example, a book. Applicant's previous proposal of fairness 4-1668
(See Japanese Patent Publication No. 4).

On the other hand, in the above-mentioned aircraft, when the flight becomes impossible for some reason in an emergency, the escape device is manually or automatically operated so that the crew can escape from the aircraft and escape. After that, the parachute is opened manually or automatically and the life jacket is automatically charged.

However, when the oxygen mask is worn, that is, when the oxygen mask is connected and fixed to the helmet and descends to the sea or the like, the hose connected to the oxygen mask is submerged in water and cannot breathe. It is necessary to remove the oxygen mask, but if you get injured when you escape or if you are faint, you cannot remove it and you may be suffocated.

[0005]

SUMMARY OF THE INVENTION The present invention has been proposed in view of the above problems, and an oxygen mask can be used even when an occupant is injured or falls to the sea or the like in a faint state. It is an object of the present invention to provide an aircraft oxygen mask automatic detachment device capable of automatically detaching an aircraft from a helmet.

[0006]

In order to achieve the above object, an aircraft oxygen mask automatic release device according to the present invention has the following configuration.

That is, in the oxygen mask for an aircraft in which the insertion parts attached to the left and right of the oxygen mask are inserted into the sheath-shaped receiving parts installed on the left and right of the helmet so as to be detachably retained and locked. By constructing a separable cover plate that constitutes a part of the sheath portion of at least one of the left and right receiving parts, and automatically removing the cover plate when landing on the sea etc. It is characterized in that the retaining state of the insertion part with respect to the receiving part is released and the oxygen mask is automatically separated from the helmet.

[0008]

As described above, at least one cover plate forming a part of the sheath portion of the sheath receiving part is configured to be separable, and the cover plate is automatically detached when landing on the sea or the like. By eliminating the retaining lock of the insertion part with respect to the receiving part by removing it and automatically releasing the oxygen mask from the helmet, the crew member is injured or fainted. It is possible to prevent the oxygen mask from being automatically detached and suffocating as described above even when the oxygen mask is dropped to the sea or the like.

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An aircraft oxygen mask automatic removal device according to the present invention will be specifically described below with reference to the embodiments shown in the drawings. 1 is a perspective view of an aircraft oxygen mask and helmet equipped with an automatic release device according to the present invention, FIG. 2 is a partially cutaway front view of the automatic release device, FIG. 3 is a partially cutaway plan view thereof, and FIG. It is a right and left side view.

In FIG. 1, reference numeral 1 is an oxygen mask, and the oxygen mask 1 is connected via a hose 2 to an oxygen cylinder or the like in an aircraft (not shown). The oxygen mask 1 is attached to the occupant's face (not shown),
Inserting parts 4 attached on both left and right sides of the
The helmet 5 is configured to be detachably connected and held by being inserted into the socket parts 6 provided on both the left and right sides of the helmet 5.

As shown in FIGS. 2 and 3, the receiving part 6 has a pedestal 7 provided on the outer surface of the helmet 5, and a pair of left and right racks 8A arranged on the surface of the pedestal 7 opposite to the helmet 5. 8B and the pedestal 7 of the racks 8A and 8B
And a cover plate 9 that covers the surface on the opposite side are formed into a sheath shape,
The plug-in component 4 is inserted into the sheath-shaped receptacle component 6. In the figure, 10 is a mounting screw for the pedestal 7 of the racks 8A and 8B, 11 is a screw hole formed in the racks 8A and 8B, and the mounting screw is screwed into the screw hole 11 from the inside of the helmet 5 to make the rack. 8A
8B and the pedestal 7 are fixed to the helmet 5 together, but not shown in the figure.

On the other hand, each of the racks 8A is attached to the insertion part 4.
A pair of rocking locking claws 12 that selectively engage with the plurality of teeth 8a of 8B are provided on both side surfaces of the insertion part 4 so as to be retractable, and both rocking locking claws 12 are constantly twisted by the coil spring 13 Is urged to rotate in a direction projecting from the side surface of the insertion part 4.
The ratchet rack mechanism of the swing locking claw 12 and the racks 8A and 8B locks the insertion part 4 to the receiving part 6 so as not to slip out. In the figure, 14 is a pair of release levers for releasing the engagement of the swinging locking claws 12 with the racks 8A and 8B, and both release levers 14 are pressed against each other against the torsion coil spring 15 in a direction to approach each other. As a result, the rocking locking claw 12 is retracted into the insertion part 4 against the spring 13 via the seesaw lever 16 and the rack 8 is moved.
The engagement with A and 8B can be released. The above configuration is almost the same as the above-mentioned conventional one.

According to the present invention, at least one of the left and right receptacle parts, in the case of the figure, the cover plate 9 forming a part of the sheath portion of the receptacle part 6 on the right side of the helmet wearer can be separated. The oxygen mask is automatically detached from the helmet by separating and removing it when landing on the sea, etc. In particular, the illustrated example is constructed so that the cover plate 9 can be freely inserted into and removed from the receptacle part 6. In addition, an example in which the shear pin 17 is retained and retained by the shear pin 17, and the shear pin 17 is sheared by the explosive force of the explosive to separate and remove the cover plate 9 from the receiving part 6.

That is, the illustrated example shows one end 9 of the cover plate 9.
a is inserted into and locked by a locking plate 18 provided on one rack 8A, and the other rack 8B is inserted into the hole 19a of the connecting block 19 integrally provided on the other end 9b of the cover plate 9
By fitting a support pin 20 integrally provided on the outer surface of the cover plate 9, the cover plate 9 can be retained in the lateral direction (left and right direction in FIG. 2) so as to be detachably inserted, and the block 19 and the support pin 20 can be held. Sharp pin 1 penetrated through
It is retained by 7 and retained. 21 is an O-ring.

As shown in FIG. 4A, the locking plate 18 is formed in a substantially U shape, and both end portions 18a thereof are bent inward to form an L shape on the upper and lower surfaces of the rack 8A. The block 19 is configured to be engaged with the recessed groove 8b of the cover plate 9 as shown in FIG. 4 (b).
The other end portion 9b is formed in a U-shape, and the opposing piece is engaged with the groove 19b formed in the upper and lower surfaces of the block 19, and the both end portions 9c are bent inward to prevent coming off. is there.

The hole 19a of the block 19 is filled with the detonation capsule 22 containing the detonator and the explosive 23, and the ignition device 24 for igniting the detonation capsule 22 and the water detection sensor 25 as the water landing detection means. Are stored in a storage chamber 26 formed on the back surface of the pedestal 7. In the figure, 27 is a powder sealant, 28 is a lead wire connecting the detonation capsule 22 and the igniter 24, and the connecting block 1 is in the state of being wound into a coil as shown in FIG.
It is arranged in the concave portion 19c formed in 9. Reference numeral 29 is a cover plate that closes the opening on the side surface of the recess 19c, and 30 is a lead wire insertion opening formed in the pedestal 7.

The ignition device 24 comprises a power source, a power circuit, etc., and the water detection sensor 25 functioning as a switch of the power circuit is disposed in the accommodation chamber 26 in the vicinity of the lead wire insertion opening 30. The lead wire insertion opening 30 is provided so as to be exposed from 24.
From the sea to the inside of the storage chamber 26 from the water detection sensor 25
When is submerged in water, the power supply circuit is closed, and the detonation capsule 22 is energized via the lead wire 28 to ignite the detonation agent in the capsule.

In the above-mentioned structure, when the crew member is discharged outside the aircraft by the escape device with the oxygen mask 1 attached and lands on the sea or the like, the lead wire insertion opening 30 formed in the pedestal 7 causes the accommodation chamber 26 to enter. Water intrudes into the water and water detection sensor 2
The ignition device 24 is activated by detecting that the water 5 has landed, the detonation capsule 22 ignites, and the explosive powder 23 explodes. Then, the connecting block 19 and the cover plate 9 are instantly moved to the position shown in FIG.
3 and moves to the right in FIG. 3, the shear pin 17 is sheared at the boundary between the hole 19a of the block 19 and the support pin 20, and the block 19 and the cover plate 9 are removed and inserted into the socket component 6. One side surface of the insertion part 4 is largely opened.

At this time, the insertion part 4 tends to be constantly pushed out to the side opposite to the helmet 5, that is, the cover plate 9 side by the tension of the band 3 in the state of being inserted into the receiving part 6, so that the cover plate 9 is removed. By being removed, the insertion part 4 loses its support and moves to the opposite side of the socket part 6 from the helmet 5, and the swinging locking claws 8 provided on the insertion part 4 also move in the above-mentioned direction with respect to the rack 7. Since the insertion part 4 is disengaged from the receiving part 6 and the engagement state of the insertion part 4 with respect to the receiving part 6 is released, the oxygen mask 1 is automatically released from the helmet 5. However, the above series of actions are performed instantaneously at the same time when the crew member lands on the surface of the sea, etc., and suffocates even when the crew member is injured or falls to the sea or the like with faintness. It is possible to prevent it.

The structure for attaching the cover plate 9 to the receiving part 6 is appropriate, and in the embodiment, explosive was used as a means for removing the cover plate 9, but for example, electric means such as an electromagnetic solenoid or a compression coil. Mechanical means such as a spring may be used. Further, in the illustrated example, one of the left and right receptacle parts 6,
In the case of the figure, the occupant's right side receiving part is provided with the automatic releasing device according to the present invention, but the left side or both sides of the receiving part may be provided with the automatic releasing device.

[0021]

As described above, according to the present invention, the insertion parts 4, 4 mounted on the left and right of the oxygen mask 1 are attached to the helmet 5
In an oxygen mask for an aircraft, which is inserted into the sheath-shaped receptacle parts 6, 6 attached to the left and right sides of the left and right so as to be detachably retained and locked, the sheath in at least one of the left and right receptacle parts 6 The cover plate 9 forming a part of the groove-like portion is configured to be separable, and the cover plate 9 is automatically separated and removed when landing on the sea or the like to prevent the insertion part 4 from slipping off from the receptacle part 6. Since the oxygen mask 1 is automatically released from the helmet 5 by releasing the locked state, even if the crew member is injured or falls to the sea or the like in a faint state, the oxygen mask 1 It is possible to prevent suffocation from coming off automatically, and it is possible to achieve the intended purpose well.

[Brief description of drawings]

FIG. 1 is a perspective view of an oxygen mask and a helmet equipped with an automatic release device according to the present invention.

FIG. 2 is a partially cutaway front view of the automatic release device.

FIG. 3 is a partially cutaway plan view of the automatic disengagement device.

4A and 4B are left and right side views of the automatic disengagement device.

[Explanation of symbols]

 1 Oxygen Mask 2 Hose 3 Band 4 Plug-in Parts 5 Helmet 6 Receptacle Parts 9 Cover Plate

Claims (2)

[Claims] 1. An oxygen mask for an aircraft, wherein insertion parts attached to the left and right of an oxygen mask are inserted into sheath-shaped receiving parts attached to the left and right of a helmet so as to be detachably retained and locked. By constructing a separable cover plate that constitutes a part of the sheath portion of at least one of the left and right receiving parts, and automatically removing the cover plate when landing on the sea etc. An automatic release device for an oxygen mask for an aircraft, characterized in that the retaining state of the insertion part with respect to the receiving part is released and the oxygen mask is automatically released from the helmet. 2. The aircraft according to claim 1, wherein the cover plate is configured to be detachable and attachable, and the shear pin is retained and retained by the shear pin, and the shear pin is sheared by the explosive force of the explosive to separate and remove the cover plate. Oxygen mask automatic removal device.