CN117184431A - Explosive treatment device, aircraft and explosive treatment method - Google Patents

Abstract

The invention relates to an explosive treatment device, which is arranged on an aircraft and comprises: the accommodating box encloses the accommodating space and is provided with a first opening communicated with the accommodating space; a flap forming part of the panel of the aircraft and closing the first opening of the containing box; a first attachment means for releasably attaching the flap to the wall panel; a second attachment means for attaching the containing box to the wall plate; and an actuating mechanism to first attach the device to allow the flap to move relative to the panel to communicate the receiving space of the receiving box to the exterior of the aircraft. The device can create a storage space on the aircraft, throw explosives out of the cabin by utilizing the space, solve the influence of pressure difference between the inside and the outside of the cabin, avoid the pressure loss of the cabin and avoid the damage of the aircraft caused by the pressure difference between the inside and the outside. Furthermore, the invention relates to an aircraft comprising such an explosive treatment device and to a method for treating explosives.

Description

Explosive treatment device, aircraft and explosive treatment method

Technical Field

The invention belongs to the field of passenger cabin equipment, and relates to an explosive treatment device. Furthermore, the invention relates to an aircraft comprising such an explosive treatment device and to an explosive treatment method.

Background

During airliner operations, aircraft such as commercial aircraft may encounter explosive materials on the aircraft, the presence of which can seriously threaten passenger safety and aircraft flight. In order to cope with such emergency, the aircraft needs to make corresponding design consideration, and an emergency program is formulated to cope with such situation, so that the aircraft can be ensured to continue to fly until safe landing.

The federal aviation administration issued the 127 amendment in 2008, and the chinese civil aviation administration issued the relevant special conditions and requirements in 2012, indicating that a location should be specified on the aircraft where a bomb or other explosive device could be placed that would optimally protect the aircraft critical structures and systems from damage during a deflagration event.

As new materials, new technologies mature, related designs for bomb containment systems have emerged to meet the objectives of reducing the impact of explosions, thereby minimizing the risk of bomb explosions on the aircraft. In this context, the ideas of explosion proof boxes, bags, and toilets as bomb containment systems are constantly being studied. The above-mentioned mode can reduce the influence of explosion on the aircraft, but the explosive is still on the aircraft, still exists and is probably because of the explosive equivalent is too big, special setting, personnel mishandling etc. causes great damage to aircraft and/or passenger.

Accordingly, there is a great need to optimize the construction of prior art explosives processing devices in order to provide an improved explosives processing device that overcomes one or more of the shortcomings of the prior art.

Disclosure of Invention

The invention aims to provide an explosive treatment device which avoids the traditional method for treating explosives on an aircraft to the landing of the aircraft, and designs an improved explosive treatment device and an improved explosive treatment method, wherein the device can treat the explosives outside the aircraft, and meanwhile, the pressure of a passenger cabin is not released due to throwing the explosives outside the aircraft, so that the damage of the aircraft caused by the pressure difference between the inside and the outside of the cabin is avoided.

According to one aspect of the present invention, an explosive treatment device is presented, which may be provided on an aircraft, and may comprise:

a housing box which can enclose the housing space and has a first opening communicating to the housing space;

a flap which may form part of a panel of the aircraft and which covers the first opening of the receiving box;

a first attachment means operable to releasably attach the flap to the wall panel;

a second attachment means which may be used to attach the containing box to the wall plate; and

and an actuating mechanism which can control the first attachment device to allow the flap to move relative to the wall plate, so that the accommodating space of the accommodating box is communicated to the outside of the aircraft.

The explosive treatment device can create a storage space which is physically separated (for example, hermetically separated) from the interior and the exterior of the cabin on the aircraft, so that three spaces which are separated from each other, namely, an in-cabin space, a storage space and an out-cabin space, are formed, and can be used for throwing out explosives to the outside of the cabin, so that the influence of pressure difference between the interior and the outside of the cabin of the aircraft is well solved. In this way, the cabin/cabin pressure loss can be avoided while the explosives are processed outside the cabin, and the damage to the aircraft caused by the pressure difference between the inside and the outside of the cabin can be avoided.

It will be appreciated that the explosive handling device allows for the active release of explosives to an off-board space, i.e. rather than being passively released from the interior of the cabin to the outside due to the energy generated by the explosion of the explosives, the explosives are actively released or handled to the off-board space, whether or not the explosives have exploded, and preferably are released to the outside of the cabin prior to the explosion of the explosives.

In addition, the explosive treatment device is small in modification to aircrafts such as airplanes, small in occupied space, high in adaptability and capable of being installed on most inner wall positions inside a cabin, and modification and maintenance cost can be remarkably reduced.

According to the above aspect of the invention, preferably, the first attachment means may comprise pneumatic locking means and the actuating mechanism may comprise pneumatic actuating means capable of unlocking the pneumatic locking means by means of high pressure gas to allow the flap to be detached from the panel.

By this arrangement it is possible to ensure the reliability of the explosive treatment device while ensuring the locking of the flap and to allow the flap to be actuated in a contactless manner, i.e. to manoeuvre the locking device arranged inside the storage space from outside the storage space and to allow the flap to be completely detached from the wall plate, ensuring a safe and reliable treatment of the explosive to the outside of the cabin.

According to the above aspect of the present invention, preferably, the pneumatic locking device may include a pneumatic locker, a first joint and a first line connected between the pneumatic locker and the first joint, and the pneumatic actuating device may include a high pressure gas cylinder and a valve switch provided outside the housing case, a second joint provided inside the housing case and a second line connected between the high pressure gas cylinder and the second joint, wherein the first joint and the second joint cooperate to fluidly connect the high pressure gas cylinder to the pneumatic locker.

The pneumatic locker according to the present invention is compact and can be installed in a narrow place and a place where an operator's hand or a hand tool is difficult to reach, without worrying about an installation space. By means of the pneumatic locker, the operation time required for connection or disconnection can be shortened by instantaneously locking or releasing by using air pressure, and the pneumatic locker provided inside the accommodating box can be rapidly and reliably actuated by operating the valve switch at the outside, so that rapid contactless release of explosives can be achieved.

According to the above aspect of the invention, preferably, the first attachment means may comprise mechanical locking means and the actuating mechanism may comprise mechanical actuating means cooperating with the mechanical locking means to allow the flap to be transferred from the closed state to the open state relative to the panel.

The device has the advantages of simple and reliable structure, low modification and maintenance cost, easy realization, simple and convenient operation and convenient release operation under emergency.

According to the above aspect of the invention, preferably, the mechanical locking device may include a hinge for hinging the flap to the wall plate, a biasing member for biasing the flap relative to the wall plate toward the open state, and a flap flange secured to the flap opposite the hinge, and the mechanical actuating device may include a slide rail handle and a slide rail attached to the slide rail handle, wherein the slide rail is displaceable relative to the flap flange between a blocking position and a release position, and in the release position, the flap is biased to the open state relative to the wall plate by the biasing member.

By this arrangement, on the one hand, the holding force for holding the flap in the closed position can be increased and the explosive can be released outside the cabin of the aircraft by pivotally opening the flap and the flap in the storage space can be operated (e.g. released) by means of the slide rail handle provided in the cabin space, so that the explosive is released to the cabin space via the opened flap.

According to the above aspect of the present invention, preferably, the second attaching means may include:

a bracket including a first leg and a second leg angled from each other;

a first fastener securing the first leg relative to the wall panel;

and a second fastener securing the second leg relative to the circumferential wall of the receiving box.

With this arrangement, it can be convenient to quickly and securely attach the containment box to the wall panel of the aircraft, allowing a crew or operator to quickly dispose of the explosives outside the cabin of the aircraft.

According to the above aspect of the present invention, preferably, the bracket may be disposed circumferentially around the periphery of the flap, and may further include a first seal disposed between the first leg and the wall plate and the flap, and a second seal disposed between the second leg and the circumferential wall of the housing case.

By this arrangement an airtight seal of the cabin space, the cargo space and the cabin exterior space with respect to each other is ensured, so that it is ensured that the cabin interior space is always kept at a constant pressure before handling the explosives and after releasing the explosives outside the cabin of the aircraft, maintaining the respiration of the passengers in the cabin unaffected.

According to the above aspect of the invention, preferably, the accommodation box may be attached to the wall panel at a side of the aircraft, and a support is provided in the accommodation box, the support being positioned on a circumferential wall below the accommodation box and having a bearing slope inclined downward in a direction toward the wall panel to allow an object on the bearing slope to move from the accommodation space of the accommodation box toward the outside of the aircraft.

By this arrangement it can be ensured that the explosive can be actively moved outside the cabin of the aircraft, for example under the influence of gravity and/or pressure differences, quickly and reliably. In particular, at the moment of the opening of the flap, the air pressure in the storage space is greater than the air pressure in the space outside the cabin, so that a strong air flow is established from the storage space towards the space outside the cabin, forcing the explosives out of the storage space inside the container.

According to another aspect of the invention, an aircraft is presented comprising an explosive treatment device according to the above aspect.

According to another aspect of the invention, an explosive treatment method for treating an explosive on an aircraft is presented, which method may comprise the steps of:

providing an explosive treatment device according to the above aspect;

placing explosives into the accommodating space of the accommodating box;

attaching the housing box to the wall plate by means of a second attachment means;

manipulating the actuation mechanism to allow the flap to move relative to the panel to thereby communicate the receiving space of the receiving box to the exterior of the aircraft; and

allowing the explosive to move from the receiving space of the container to the exterior of the aircraft.

Advantageous technical effects that may be provided by an explosive treatment device according to the present invention may include, but are not limited to, the following:

1) The explosive treatment device solves the problem of pressure difference between the inside and the outside of the cabin by creating a storage space. By creating a closed storage space, an intra-cabin space, a storage space and an extra-cabin space are formed which are isolated from each other, in particular hermetically isolated. The storage space is utilized to throw out the explosives outwards (particularly actively throw or release), so that the influence of the pressure difference between the interior and the exterior of the passenger cabin is well solved. The design method of outer throw is creatively proposed, and the traditional solution of seeking to minimize the explosion effect inside the cabin is skipped.

2) The explosive treatment device according to the present invention subtly contemplates a release mechanism for the outer throw of the explosive. An independent treatment device is designed, so that the explosive can be thrown outwards conveniently, and the flap can be opened or released under the condition that the sealing isolation among the space in the cabin, the object placing space and the space outside the cabin is ensured.

3) The explosive treatment device according to the invention proposes a method of casting explosives outwards by creating a storage space, which is not only superior but also easy to implement compared to the prior art. The treatment device in the prior art is still in technical research of reducing the explosion influence in the cabin, the protection of the prior art can still generate certain damage to the cabin interior, the development technology difficulty is high, and the maturity realized on the machine is insufficient.

4) Compared with the explosive treatment device in the prior art, the explosive treatment device has the advantages of operation and cost, so that the competitive model provided with the explosive treatment device is more advanced, and the explosive treatment device is beneficial to driving the sales market of the whole machine through the technical advantages.

5) The installation of the explosive treatment device has small modification to aircrafts such as commercial airliners, small occupied space, no adverse effect on passenger space, and high suitability, and can be installed in most inner wall positions of a passenger cabin.

Therefore, the explosive treatment device can meet the use requirement, overcomes the defects of the prior art and achieves the preset aim.

Drawings

For a further clarity in describing the explosive treatment device according to the present invention, the present invention will be described in detail with reference to the accompanying drawings and detailed description, in which:

fig. 1 shows a schematic view of three spaces separated from each other, formed in the vicinity of a cabin of an aircraft, after installation of an explosive treatment device according to the invention;

FIG. 2 is a schematic illustration of a first example arrangement of an explosive treatment device according to the present invention;

FIG. 3 is a schematic view of a portion of the explosives processing device shown in FIG. 2;

FIG. 4 is a schematic view of another portion of the explosives processing device shown in FIG. 2;

FIG. 5 is a schematic view of the explosives processing device shown in FIG. 2, as viewed from outside the cabin of the aircraft;

FIG. 6 is a schematic view of a second example arrangement of an explosives processing device in accordance with the invention, showing a slide rail in a stop position;

FIG. 7 is another schematic view of a second example arrangement of an explosives processing device in accordance with the invention, showing a slide rail in a released position; and

fig. 8 is another schematic view of a second example arrangement of an explosive treatment device according to the present invention.

The figures are merely schematic and are not drawn to scale.

List of reference numerals in the figures and examples:

a 100-explosives processing device comprising:

10-a holding tank comprising:

11-a first opening;

12-a second opening;

20-opening cover;

30-a first attachment device comprising:

310-pneumatic locking device, comprising:

311-pneumatic locker;

312-first joint;

313-first line;

320-mechanical locking device comprising:

321-hinges;

322-biasing member;

323-flap flange;

40-a second attachment means comprising:

a stent, comprising:

41A-a first leg;

41B-a second leg;

41C-a third opening;

42-a first fastener;

43-a second fastener;

44-a first seal;

45-a second seal;

a 50-actuation mechanism comprising:

510-pneumatic actuation means comprising:

511-high pressure gas cylinders;

512-valve switch;

513-a second linker;

514-a second line;

520-mechanical actuation device, comprising:

521-slide rail handles;

522-a slide rail;

200-wallboard;

300-explosives;

400c a support;

a-an area within the nacelle;

b-an area within the containment box;

the area outside the nacelle.

Detailed Description

It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It should be further understood that the specific devices illustrated in the accompanying drawings and described in the specification are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, unless explicitly stated otherwise, the particular orientations, directions, or other physical characteristics to which the various embodiments disclosed relate should not be considered limiting.

When an aircraft such as a commercial aircraft flies to high-altitude cruising, the air outside the aircraft is lean and the air pressure is small. In order to protect the normal breathing of passengers in the cabin, a minimum cabin pressure is usually maintained in the cabin, which pressure value is set differently depending on the specific model. Common pressure values include a pressure value at 6000 feet (approximately 1828.8 meters) or 8000 feet (2438.4 meters) at altitude. In general, the pressure in the cabin of an aircraft is higher than that outside the cabin, and if the cabin door or other sealing parts of the cabin wall plate are opened during the flight, a great amount of air flow is instantaneously generated due to the air pressure difference between the inside and the outside of the cabin, and meanwhile, the pressure in the cabin is released, so that the normal breathing of passengers cannot be met in severe cases.

The invention improves the traditional method for treating explosives on an aircraft to the landing of the aircraft, and provides an explosive treatment device and an explosive treatment method, which can treat the explosives outside the cabin of the aircraft, and meanwhile, the pressure release of a passenger cabin caused by throwing or releasing objects outside the cabin is avoided, the poor comfort or unsafe of passengers caused by internal and external pressure difference is avoided, and the damage of the aircraft is avoided.

Fig. 1 shows a schematic view of three spaces separated from each other formed in the vicinity of a cabin of an aircraft after installation of an explosive treatment device 100 according to the present invention.

As shown in the drawing, according to the inventive concept, an explosive treatment device 100 is provided near a wall panel 200 of a cabin of an aircraft, and the explosive treatment device 100 may include at least a receiving box 10 and a flap 20.

The area in the vicinity of the cabin of the aircraft can be formed into at least three areas that are sealed off from one another by means of the receiving box 10 and the flap 20: an area a inside the nacelle, an area B inside the housing box and an area C outside the nacelle, wherein the area a inside the nacelle and the area B inside the housing box can be separated by the housing box 10 (in particular by its circumferential wall), and the area B inside the housing box 10 and the area C outside the nacelle can be separated by the flap 20.

Fig. 2 is a schematic diagram of a first example arrangement of an explosives processing device 100 in accordance with the invention.

As shown and as a non-limiting example, an explosive treatment device 100 according to the present invention may be provided on an aircraft. In addition to the above-mentioned containment case 10 and flap 20, the explosive treatment device 100 may further include: the first attachment means 30, the second attachment means 40, and the actuation mechanism 50, etc.

As an example, the containment tank 10 may enclose a containment space, i.e., region B within the containment tank, in which explosives 300 and/or supports 400, etc. may be placed. The housing box 10 may have a first opening 11 communicating to the housing space.

In the embodiment shown in the drawings, the receiving box 10 has a bottom side arranged on the left side in the view shown in fig. 2, and a circumferential wall portion arranged around the bottom side. The circumferential wall may form a circumferential wall having a plurality of sides or a circumferential wall integrally formed as a cylindrical shape or a truncated conical shape.

In the view shown in fig. 2, a bearing slope extending in a direction toward the wall plate 200 and inclined downward (e.g., downward right in fig. 2) is provided on the lower circumferential wall of the housing box 10. The carrier ramp allows objects on the carrier ramp to move from the receiving space of the receiving box 10 towards the outside of the aircraft, for example by means of gravity or an air flow due to an air pressure difference or the like.

In use, according to the invention, the containing box 10 may need to act as a separating interface for the cabin space and the bunk space, i.e. form part of the wall panels of the cabin. Accordingly, the housing case 10 may be preferably made of a material having high strength, for example, various metals such as aluminum alloy or various composite materials such as carbon fiber. Preferably, the material of the receiving box 10 may be the same as that of the wall plate 200.

The flap 20 may form part of a wall panel 200 of the aircraft and cover the first opening 11 of the receiving box 10. For example, the flap 20 may be shaped to conform to the shape of the portion of the panel 200 of the aircraft to which it is mounted (e.g., the exterior side of the panel 200) to form a smooth and complete aerodynamic surface. Under normal conditions, i.e. when handling explosives on an aircraft is not required, the flap 20 acts as a panel 200 for the aircraft. Thus, the material of the flap 20 may preferably be the same as the material of the wall panel 200.

In the embodiment shown in fig. 2, the flap 20 may be attached to the wall plate 200 by means of the first attachment means 30, for example, by making the flap 20 air-tight and releasable attached to the wall plate 200, so that the cabin can be selectively closed or the accommodation space can be communicated to the cabin space.

It will be appreciated that when the flap 20 is closed, the region B inside the containment box 10 is hermetically separated from the region C outside the nacelle to ensure that the air pressure inside the nacelle remains within the desired range, i.e. at this point there is no air flow path between the flap 20 and its surrounding wall panel 200 and a certain pressure differential can be experienced. Embodiments of the first attachment device 30 of the present invention may include a pneumatic locking device 310 or a mechanical locking device 320 to cooperate with a pneumatic or mechanical actuation mechanism, respectively, described in detail below, to effect opening or closing of the flap 20.

Fig. 3 and 4 are schematic views of a portion of explosive treatment device 100 shown in fig. 2, respectively.

In the embodiment shown in connection with fig. 2-5, the first attachment means 30 may comprise a pneumatic locking means 310 and, in this case, the actuating mechanism 50 may comprise a pneumatic actuating means 510. The pneumatic actuation device 510 is capable of unlocking the pneumatic locking device 30 by means of high pressure gas to allow the flap 20 to be disengaged from the wall panel 200.

As shown in detail in fig. 3, the pneumatic locker 310 may include a pneumatic locker 311, a first joint 312, and a first line 313 connected between the pneumatic locker 311 and the first joint 312.

The pneumatic latch 311 may be used to secure the flap 20 to the wall panel 200 such that the flap 20, together with the surrounding wall panel 200, forms a smooth and continuous aerodynamic surface of the aircraft cabin.

Pneumatic locker 311 may be various types of pneumatic locking devices known in the art including, but not limited to, pneumatic ball-type lockers, pneumatic taper pin grasping lockers, and the like. When the pneumatic locking device is locked, the steel balls are ejected out of the compression block by the piston, the exposed part of the compression block can not move, when the high-pressure gas flowing out of the high-pressure gas source is introduced into the small hole on one side of the shell, the piston is stressed to compress the spring, a certain displacement is generated integrally, and the steel balls acting on the piston lose supporting force and fall into the supporting seat. In this way, two or more components can be selectively attached together or released from each other by means of high pressure gas.

As a non-limiting example, the pneumatic locker 311 may be the following type of locker commercially available from japan corporation, tail to tail: a PBLC pneumatic ball-type locker, a PPHC-S pneumatic taper pin grasping type locker, a PPHC-D pneumatic taper pin grasping type locker and the like.

With continued reference to fig. 2, the containing box 10 may be attached to the wall panel 200 by a second attachment means 40, such as by having the containing box 10 be air-tightly attached to the wall panel 200 (e.g., inside the wall panel 200). The containment box 10 may not be attached to the wall panel 200 during normal flight of the aircraft. For example, the storage case 10 may be placed on a luggage rack or in the remaining storage space near the flap 20 and attached to the wall panel 200 along with the explosives 300 only when it is desired to dispose of the explosives 300 found on the aircraft. For example, the explosive 300 is placed into the accommodation space of the accommodation box 10 via the first opening 11, and the support 400 may be optionally placed at the lower side of the circumferential wall thereof, and the explosive 300 is rested on the support 400.

The support 400 may be a custom-made component specifically for carrying explosives 300, such as custom-made with a smooth carrying surface, or may be an existing support within the cabin of an aircraft such as a temporary acquired clothing, blanket, pallet, etc., to facilitate release of explosives 300 from region B within the containment bin 10 to region C outside the cabin, i.e., into the space outside the cabin.

As shown in fig. 3 and 4 and as a non-limiting example, the second attachment device 40 may include a bracket 41, a first fastener 42, a second fastener 43, a first seal 44, and a second seal 45.

As an example, the bracket 41 may be disposed circumferentially about the periphery of the flap 20, such as extending continuously about the periphery of the flap 20, and have a generally L-shaped cross-sectional shape (as shown in fig. 3). The bracket 41 may include a first leg 41A and a second leg 41B that are angled (e.g., approximately 90 degrees) from each other.

The first leg 41A may extend generally parallel to the wall 200 and the flap 20, such as extending against the wall 200 and the flap 20, forming a continuous circumferential closed shape around the flap 20, such as a generally square shape with a hollow area, or a hollow annular shape.

The first leg 41A can be secured to the wall panel 200 by the first fastener 42 and releasably secured to the flap 20 by the pneumatic ball lock 311 described above, i.e., the first leg 41A is secured to both the wall panel 200 and the flap 20, thereby releasably retaining the flap 20 to the wall panel 200 by the first leg 41A.

Preferably, seals may be provided between the first leg 41A and the wall panel 200, and between the first leg 41A and the flap 20, such as the first seal 44 shown in the drawings extending from the wall panel 200 to the flap 20.

The second leg 41B may extend towards the circumferential wall of the housing box 10, for example at an angle of about 90 degrees to the first leg 41A, for fixing to the circumferential wall of the housing box 10 by means of the second fastener 43. Preferably, a second seal 45 may be provided between the second leg 41B and the circumferential wall of the containing box 10.

According to the invention, in the initial state of the aircraft, the first leg 41A remains fixed to the wall panel 200 and the flap 20, while the containing box 10 is fixed to the second leg 41B, with the explosives 300 or the like contained therein, only when it is necessary to dispose of the explosives 300 or the like found on the aircraft, thereby fixing the containing box 10 to the wall panel 200.

The actuation mechanism 50 can control the first attachment device 30 to allow the flap 20 to move relative to the wall panel 200, thereby communicating the receiving space of the receiving box 10 to the exterior of the aircraft. Embodiments of the actuation mechanism 50 of the present invention may include a pneumatic actuation device 510 or a mechanical actuation device 520.

As shown in more detail in fig. 4, the pneumatic actuation device 510 may include a high pressure gas cylinder 511 and a valve switch 512 disposed outside the housing tank 10, a second connection 513 disposed inside the housing tank 10, and a second line 514 connected between the high pressure gas cylinder 511 and the second connection 513.

The high pressure gas cylinder 511 may contain high pressure nitrogen or a mixed gas of nitrogen and carbon dioxide and is fixed to the housing case 10, for example, to the bottom thereof (the left bottom shown in fig. 4), and the valve switch 512 may be provided on the gas outlet passage of the high pressure gas cylinder 511 to control the release of the high pressure gas and thus the operation of the pneumatic locker 311.

The first connector 312 and the second connector 513 may be complementary connectors, for example, the first connector 312 may be a socket and the second connector 513 may be a plug, thereby hermetically connecting the first line 313 connected to the first connector 312 to the second line 514 connected to the second connector 513, thereby fluidly connecting the high pressure gas cylinder 511 to the pneumatic locker 311. At this time, a second opening 12 may be provided at the bottom or circumferential wall of the receiving tank 10, the second line 514 extending between the outside and the inside of the receiving tank 10 through the second opening 12, and the second line 514 being hermetically sealed with the second opening 12.

It should be appreciated that the first line 313 and the second line 514 described above are flexible hoses capable of withstanding a predetermined air pressure. In this arrangement, locking or release of the pneumatic locker 311 can be controlled via the valve switch 512. For example, upon opening the valve switch 512, the piston of the pneumatic locker 311 may be actuated, thereby releasing the flap 20 from the wall plate 200, thereby allowing the area B within the containing box 10 to communicate to the area C outside the nacelle.

Fig. 5 is a schematic view of the explosives processing device 100 shown in fig. 2, as viewed from outside the cabin of the aircraft.

As shown, the flap 20 of the explosive treatment device 100 is shaped in a generally rectangular shape and has 4 corners, each of which may be provided with a pneumatic locker 311, each pneumatic locker 311 being connected to a first line 313.

It should be appreciated that while a generally rectangular flap 20 is shown in the figures, those skilled in the art will envision other shapes, e.g., circular, oval, etc., without departing from the scope of the invention. In addition, accordingly, the person skilled in the art may arrange the remaining number of pneumatic lockers 311, and instead of connecting the pneumatic lockers 311 together in series as shown in the drawings, it is also possible to connect the pneumatic lockers 311 to the first joint 312 or the high-pressure gas cylinder 511 in parallel, respectively.

In the embodiment shown in connection with fig. 2 to 5, after the installation of the housing box 10, the high-pressure gas cylinder 511 and the valve switch 512 are arranged in a region a in the cabin physically separated from a region B in the housing box, and the pneumatic locker 311 is enclosed in the region B in the housing box. However, at the time of installation, a quick and reliable connection of the first line 313 to the second line 514 can be achieved by means of the first joint 312 and the second joint 513, whereby the operation of the pneumatic lock 311 provided in the area B within the accommodation box is controlled in the area a within the cabin, whereby the release of the flap 20 is achieved, whereby the release of the explosive 300 contained therein to the outside of the cabin of the aircraft via the gap formed by the fall-off of the flap 20 is allowed, i.e. the displacement of the area B within the accommodation box 10 to the area C outside the cabin is enabled.

Fig. 6 is a schematic diagram of a second example arrangement of an explosives processing device 100 in accordance with the invention; and figures 7 and 8 are additional schematic views of a second example arrangement of an explosive treatment device 100 according to the present invention. Wherein fig. 6 and 8 show the flap 20 in a closed condition relative to the wall panel 200, and fig. 7 shows the flap 20 in an open condition relative to the wall panel 200.

The explosives processing device 100 described in connection with fig. 6-8 differs from the explosives processing device 100 described in connection with fig. 2-5 only in the manner of attachment and actuation.

In particular, in the embodiment shown in fig. 6-8, the first attachment means 30 comprises a mechanical locking means 320, and the actuation mechanism 50 comprises a mechanical actuation means 520. The mechanical actuation device 320 can cooperate with the mechanical locking device 520 to allow the flap 20 to transition from a closed state to an open state relative to the panel 200.

As shown in detail in fig. 8, the mechanical locking device 320 may generally include a hinge 321, a biasing member 322, and a flap flange 323.

The hinges 321 may be used to hinge the flap 20 to the wall plate 200, such as three hinges 321 disposed at the left edge of the flap 20 in fig. 8. The hinge 321 may allow the flap 20 to pivot to different angles relative to the wall panel 200.

The biasing member 322 can be used to bias the flap 20 toward the open state relative to the wall panel 200. In the example of fig. 8, two biasing members 322 are provided and are disposed spaced apart from the hinge 321. As an example, the biasing member 322 may be an elastic member such as a torsion spring.

The flap flange 323 can be adapted to cooperate with the slide rails 522 to allow the flap 20 to be in different states, such as a closed state or an open state.

In the example shown in fig. 8, a flap flange 323 may be fixed to the flap 20 and disposed opposite the hinge 321 to increase the holding moment, for example, at the right side edge of the flap 20 of fig. 8. In alternative embodiments, the flap flange 323 can also be arranged at the upper or lower edge of the flap 20 or elsewhere.

Preferably, this hinge 321 may be provided on the rear side of the flap, i.e. allowing the front side of the flap 20 to pivot open, in the direction of flight of the aircraft or in the longitudinal direction of the fuselage, so that the opened flap 20 is kept in an open state by the ram air inflow experienced by the aircraft in flight, in particular in cooperation with the biasing member 322, ensuring that the explosives 300 can be released from the cabin via this opened flap 20.

With continued reference to fig. 8, the mechanical actuation device 520 may include a slide rail handle 521 and a slide rail 522 attached to the slide rail handle 521. The slide rails 522 are displaceable relative to the flap flange 323 between a stop position and a release position, and in the release position, the flap 20 is biased to an open state relative to the wall panel 200 by the biasing member 322.

As shown in fig. 6 and 7, the slide rail 522 may extend between an area a within the nacelle and an area B within the housing box 10 to control the release mechanism inside the housing space, i.e., the engagement relationship of the slide rail 522 with the flap flange 323, by means of a slide rail handle 521 disposed outside the housing space.

A third opening 41C is also provided on the bracket 41, via which third opening 41C the slide rail 522 extends in the space on both sides of the circumferential wall of the receiving box 10, and the slide rail 522 is hermetically sealed connected to the third opening 41C. In particular, after the flap 20 has been opened, additional auxiliary sealing means (not shown in the figures) can be provided between the slide rail 522 and the third opening 41C.

In the initial state, the slide rail 522 can be in a stop position relative to the flap flange 323, i.e., in the position shown in fig. 6. At this point, it may be used to secure the flap 20 to the wall panel 200 such that the flap 20, together with the surrounding wall panel 200, forms a smooth and continuous aerodynamic surface of the aircraft cabin.

As described above with respect to fig. 2-5, when it is desired to dispose of explosives 300 on an aircraft, the containment box 10 is attached to the wall panel 200, such as to the inside of the wall panel 200, along with the explosives 300. Then, by pulling the slide rail handle 521, the slide rail handle 521 can be moved from the stop position shown in fig. 6 to the release position shown in fig. 7, which can be used to open the flap 20. This allows the area B within the containment tank 10 to communicate to the area C outside the cabin, thereby allowing the explosives 300 contained therein to be released to the cabin exterior of the aircraft via the pivoting opening of the flap 20, i.e., to be displaced from the area B within the containment tank 10 to the area C outside the cabin.

According to a non-limiting embodiment of the present invention, an explosives processing method for processing explosives 300 on an aircraft may optionally include the steps of:

an explosive treatment device 100 according to the present invention may be provided or provided on an aircraft, and the explosive treatment device 100 may include components of the container 10, the flap 20, the first attachment device 30, the second attachment device 40, and the actuation mechanism 50. In a default state, the pod 10 may not be attached to the wall panel 200, but rather stored within the cabin of the aircraft.

When explosives or the like to be treated are found on the aircraft, the accommodation box 10 may be taken out, and the explosives 300 may be placed into the accommodation space of the accommodation box 10. Preferably, a support 400 or other containment or safety device may be placed under explosives 300.

Once explosives 300 have been placed into the containment tank 10, the containment tank 10 is attached (e.g., hermetically attached) to the wall panel 200 by means of the second attachment device 40, where the region a within the timing pod achieves a hermetic seal from the region B within the containment tank.

The actuating mechanism 50 is then manipulated to permit the flap 20 to move relative to the wall panel 200, thereby communicating the receiving space of the receiving box 10 to the exterior of the aircraft.

Thereafter, under the influence of gravity and a pressure difference, the explosive 300 will be allowed to move from the accommodation space of the accommodation box 10 to the outside of the aircraft. Where permitted, the crew may first maneuver the aircraft to a location where it is scarce or remote and then release the explosives 300 to minimize damage to ground personnel or buildings, etc.

The terms "front," "rear," "above" and "below," as well as the terms "first," "second," etc. used to indicate sequences, as used herein, are merely intended to enable one of ordinary skill in the art to better understand the inventive concepts illustrated in the preferred embodiment, and are not intended to limit the invention. Unless otherwise indicated, all orders, orientations, or orientations are used solely for the purpose of distinguishing one element/component/structure from another element/component/structure, and do not denote any particular order, order of operation, direction, or orientation unless otherwise indicated. For example, in alternative embodiments, the "first leg" may be the "second leg" and the "first joint" may alternatively refer to the "second joint".

In view of the foregoing, an explosives processing device 100 in accordance with embodiments of the invention overcomes the shortcomings of the prior art and achieves the intended objects.

While the explosive treatment device of the present invention has been described in connection with preferred embodiments, those of ordinary skill in the art will recognize that the above examples are for illustrative purposes only and are not intended to be limiting. Accordingly, the present invention may be variously modified and changed within the spirit of the claims, and all such modifications and changes are intended to fall within the scope of the claims of the present invention.

Claims (10)

1. An explosive treatment device (100) disposed on an aircraft and comprising:

a housing box (10) enclosing a housing space and having a first opening (11) communicating to the housing space;

a flap (20) forming part of a wall panel (200) of the aircraft and closing the first opening (11) of the containing box (10);

-first attachment means (30) for releasably attaching said flap (20) to said wall panel (200);

-second attachment means (40) for attaching the containing box (10) to the wall plate (200); and

-an actuation mechanism (50) controlling the first attachment means (30) to allow the flap (20) to move with respect to the wall panel (200) so as to communicate the accommodation space of the accommodation box (10) to the outside of the aircraft.

2. The explosives processing device (100) of claim 1, wherein the first attachment device (30) includes a pneumatic locking device (310) and the actuation mechanism (50) includes a pneumatic actuation device (510) that is capable of unlocking the pneumatic locking device by means of high pressure gas to allow the flap (20) to be disengaged from the wall panel (200).

3. The explosives processing device (100) of claim 2, wherein the pneumatic locking device (310) comprises a pneumatic locker (311), a first connector (312) and a first line (313) connected between the pneumatic locker and the first connector, and the pneumatic actuation device (510) comprises a high pressure gas cylinder (511) and a valve switch (512) disposed outside the containment tank (10), a second connector (513) disposed inside the containment tank (10) and a second line (514) connected between the high pressure gas cylinder and the second connector, wherein the first connector (312) and the second connector (513) cooperate to fluidly connect the high pressure gas cylinder (511) to the pneumatic locker (311).

4. The explosives processing device (100) of claim 1, wherein the first attachment device (30) includes a mechanical locking device (320) and the actuation mechanism (50) includes a mechanical actuation device (520) that cooperates with the mechanical locking device to allow the flap (20) to transition from a closed state to an open state relative to the panel (200).

5. The explosives treatment device (100) of claim 4, wherein the mechanical locking device (320) includes a hinge (321) for articulating the flap (20) to the wall plate (200), a biasing member (322) for biasing the flap (20) relative to the wall plate (200) toward the open state, and a flap flange (323) secured to the flap (20) opposite the hinge (321), and the mechanical actuation device (520) includes a slide rail handle (521) and a slide rail (522) attached to the slide rail handle, wherein the slide rail (522) is displaceable relative to the flap flange (323) between a stop position and a release position, and in the release position, the flap (20) is biased to the open state relative to the wall plate (200) by the biasing member (322).

6. The explosives processing device (100) of any of claims 1-5, wherein the second attachment device (40) comprises:

a bracket (41) comprising a first leg (41A) and a second leg (41B) angled to each other;

-a first fastener (42) securing the first leg (41A) relative to the wall plate (200); and

-a second fastener (43) which secures the second leg (41B) with respect to the circumferential wall of the containing box (10).

7. The explosives treatment device (100) of claim 6, characterized in that the bracket (41) is circumferentially arranged around the perimeter of the flap (20) and further comprising a first seal (44) disposed between the first leg (41A) and the wall plate (200) and the flap (20) and a second seal (45) disposed between the second leg (41B) and a circumferential wall of the container (10).

8. An explosive treatment device (100) according to any one of claims 1-5, characterized in that the accommodation box (10) is attached to the wall panel (200) at the side of the aircraft, and that a support (400) is provided in the accommodation box (10), which support is positioned on the circumferential wall below the accommodation box (10) and has a downwardly sloping carrying slope in the direction towards the wall panel (200), to allow objects on the carrying slope to move from the accommodation space of the accommodation box (10) towards the outside of the aircraft.

9. An aircraft comprising an explosive treatment device (100) according to any one of claims 1-8.

10. An explosives processing method for processing explosives (300) on an aircraft, the method comprising the steps of:

-providing an explosive treatment device (100) according to any one of claims 1-8;

-placing the explosives (300) into the accommodation space of the accommodation box (10);

-attaching the containing box (10) to the wall plate (200) by means of the second attachment means (40);

-manipulating the actuation mechanism (50) to allow the flap (20) to move with respect to the wall panel (200) so as to communicate the accommodation space of the accommodation box (10) to the outside of the aircraft; and

-allowing the explosive (300) to move from the accommodation space of the accommodation box (10) to the outside of the aircraft.