CN113624090A - Explosion-proof device and aircraft - Google Patents
Explosion-proof device and aircraft Download PDFInfo
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- CN113624090A CN113624090A CN202110979582.2A CN202110979582A CN113624090A CN 113624090 A CN113624090 A CN 113624090A CN 202110979582 A CN202110979582 A CN 202110979582A CN 113624090 A CN113624090 A CN 113624090A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42D—BLASTING
- F42D5/00—Safety arrangements
- F42D5/04—Rendering explosive charges harmless, e.g. destroying ammunition; Rendering detonation of explosive charges harmless
- F42D5/045—Detonation-wave absorbing or damping means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pressure Vessels And Lids Thereof (AREA)
Abstract
The invention relates to an explosion-proof device, comprising: an explosion proof device body including an explosion proof cylinder, an end cap, an impact end and a stop mechanism, wherein the end cap covers a first end of the explosion proof cylinder, the impact end is received in a second end of the explosion proof cylinder to cover the second end, and the stop mechanism interacts with the impact end and the explosion proof cylinder such that when a force acting on the stop mechanism is less than a predetermined threshold, the stop mechanism limits relative movement between the impact end and the explosion proof cylinder, and when the force acting on the stop mechanism is greater than or equal to the predetermined threshold, the stop mechanism is disabled such that the impact end is able to move in an axial direction relative to the explosion proof cylinder. The explosion-proof device can keep the integrity from structural damage when the equivalent weight of the explosive is lower than a preset threshold value, and realize the directional blasting of the weakening structure when the equivalent weight of the explosive is higher than or equal to the preset threshold value. The invention also relates to an aircraft comprising the explosion-proof device.
Description
Technical Field
The invention relates to an explosion-proof device which is applied to a passenger cabin of a civil aircraft and is used as an explosion emergency treatment device for handling dangerous goods such as explosives in the passenger cabin in the flying process of the aircraft and improving the flying safety.
The invention also relates to an aircraft comprising such an explosion protection device.
Background
Aircraft such as modern large civil aircraft, due to their high cruising altitude, all employ a cabin design of pressurized cabin. Because the space in the passenger cabin is limited and is a closed space, the explosives in the passenger cabin can pose a great threat to the flight safety. The characteristic that the pressurization and the inner space of the passenger cabin are small causes that the emergency treatment of the explosive in the passenger cabin is limited by the treatment mode of adopting the explosion-proof bag for the common explosive.
In the event of an explosive explosion of the aircraft during flight, the damage to the aviation safety is enormous.
In the past decades, aviation management agencies, scientific research institutes, aircraft manufacturers, and the like in various countries of the world have actively explored ways to reduce the impact of explosives explosion on aviation safety during flight. The destructive effect of explosives on the aircraft mainly comes from high-speed and high-pressure air shock waves generated after explosives are exploded, particularly, the explosion occurs in a closed cabin, and due to the superposition effect of the shock waves caused by the limitation of a closed space, the overpressure peak value of the shock waves is multiplied, so that the threat to the civil aviation safety is great.
In 1997, the international civil aviation organization issued relevant requirements specifically in the convention to cope with terrorist attacks and hijacking, directing aircraft design and how the aircraft operators handled.
In 2008, this content was formally a law that the Least Risk Bomb Location (LRBL) was explicitly written into FAA (Federal Aviation Administration) regulations.
Currently, it is specified in FAA 25.795(c) clause that an aircraft with a maximum approved passenger seat size greater than 60 or a maximum approved gross takeoff weight in excess of 100,000 pounds (45,359 kilograms) must meet the following specifications:
(1) minimum risk bomb position aircraft designs must have a designated location for the placement of bombs or other explosive devices to provide optimal protection of flight critical structures and systems from damage in the event of an explosion.
The applicant finds that the design of an explosion-proof device for a passenger cabin of a civil passenger plane in foreign countries mostly adopts a box type, and the energy absorption protection is carried out completely by depending on the structural strength of the explosion-proof box, so that the problems of heavy structure, inconvenience in movement, time consumption in locking and the like exist. In 2016, the research problem of the position of the minimum risk bomb of the civil aircraft begins to be concerned, for example, by analyzing the influence of explosion of explosives on the safety of the aircraft structure by the terro and the like of the Shanghai aircraft design research institute where the applicant of the application is located, the airworthiness conformance verification method of the LRBL is proposed.
In order to match with LRBL, Korea celluloid and the like of the national institute of chemistry of Western Ann, in patent summary of invention, which is filed in 03.06.2019, and has the application number of CN201910168298.X, and is entitled "energy-gathering and pressure-releasing civil aircraft cabin directional explosion-proof device", an energy-gathering and pressure-releasing civil aircraft cabin directional explosion-proof device is provided, and the energy-gathering and pressure-releasing civil aircraft cabin directional explosion-proof device comprises a cylindrical tank main body 1, a front-end conical energy-gathering and pressure-releasing steel thin plate 2, a rear-end-face edge reinforcing panel 3, two mounting bases 4 and a three-groove-type rear end cover 5. The explosion-proof device utilizes the conical panel to carry out energy gathering orientation on the shock wave after explosion, and the shock wave and the energy generated after explosion are released to the outside of the passenger cabin. However, the explosion-proof device utilizes the conical panel to carry out energy-gathering orientation on the shock wave after explosion, so as to realize explosion, the influence of the explosion-proof device on the airplane body is uncertain, when the equivalent of the explosive is small, high-pressure airflow, fragments and the like generated by the explosion still can leak out of the cylindrical tank body, and the structure is not reliable due to the fact that the installation position is arranged on a sliding rail of the cabin floor. In addition, the position of the bomb with the minimum risk selected in the patent is a side wall plate of a passenger cabin, and the influence on the structural integrity of the whole airplane body is large.
Among the invention patents filed on 2016, 08, 01 and entitled "a portable directional explosion-proof device for civil aircraft cabin", issued by CN201610620278.8 and entitled "a portable directional explosion-proof device for civil aircraft cabin" at north west university of industry, seaweeds, etc., a portable directional explosion-proof device for civil aircraft cabin is proposed.
Accordingly, there remains a need for an explosion protection arrangement that overcomes one or more of the disadvantages of the prior art to ensure aircraft safety or at least to increase the survival probability of an aircraft, such as a commercial passenger aircraft, in the event of a suspicious explosive situation in the passenger cabin of the aircraft.
Disclosure of Invention
It is an object of the present invention to provide an explosion proof device for use in conjunction with the minimum risk bomb position as specified under FAA 25.795 (c). For example, when the rear gate structure is selected as the minimum risk bomb position on an aircraft such as a commercial airliner produced in a certain country, and the explosion-proof device breaks through the weakened structure on the rear gate structure, only the rear gate structure is damaged, so that the integrity of the main body structure of the aircraft can be ensured not to be damaged.
According to one aspect of the present invention, there is provided an explosion-proof device, comprising: an explosion proof device body including an explosion proof cylinder, an end cap, an impact end and a stop mechanism, wherein the end cap covers a first end of the explosion proof cylinder, the impact end is received in a second end of the explosion proof cylinder to cover the second end, and the stop mechanism interacts with the impact end and the explosion proof cylinder such that when a force acting on the stop mechanism is less than a predetermined threshold, the stop mechanism limits relative movement between the impact end and the explosion proof cylinder, and when the force acting on the stop mechanism is greater than or equal to the predetermined threshold, the stop mechanism is disabled such that the impact end is able to move in an axial direction relative to the explosion proof cylinder.
When an explosive or suspected explosive is found on an aircraft, it is placed in an explosion-proof canister, and if the equivalent weight of the explosive is below a predetermined threshold, the explosion-proof device is able to maintain structural integrity without structural failure. When the equivalent weight of the explosive is higher than or equal to the preset threshold value, the clamping and stopping mechanism in the explosion-proof device is invalid, so that the impact end head can be pushed out of the explosion-proof barrel under the action of the explosive force of the explosive, the explosion-proof device can realize directional explosion, the impact force generated by explosion is released to the outside of the aircraft, the influence of the explosion on the aircraft structure is reduced, and the safety of the aircraft and passengers is further ensured.
According to the above aspect of the present invention, preferably, the explosion-proof apparatus may further include a support base including a bracket attached to the base and a holding portion securely supporting the explosion-proof apparatus body.
By providing the support seat, the explosion-proof device according to the invention can be used in combination with the minimum risk bomb position specified in FAA 25.795(c), for example, the rear gate structure can be selected as the minimum risk bomb position on the aircraft, and when the impact tip breaks through the weakened structure on the rear gate structure, only the rear gate structure is broken, so that the integrity of the main body structure of the aircraft can be ensured not to be broken, and the influence of explosion on the aircraft structure can be further reduced.
According to the above aspect of the invention, preferably, the explosion proof cartridge may comprise a cylindrical internal cavity, and the impact tip comprises a cylindrical base portion and a conical portion having a tip, wherein the cylindrical base portion is received in the internal cavity with a clearance fit and the tip faces the outside of the internal cavity. By means of this construction, it is better ensured that the impact tip breaks through the corresponding weakening structure without damaging the basic structure of the remaining aircraft. And the clearance fit is such that the impact force from the explosion is released to the maximum extent in the event that the equivalent of the explosive is below a predetermined threshold without the impact tip rushing out of the explosion proof barrel.
According to the above aspect of the present invention, preferably, the inner cavity of the explosion-proof cylinder may be provided with a guide portion on an inner surface near the second end, which is guided in the axial direction of the explosion-proof cylinder, and the cylindrical base portion of the impact tip includes an engagement portion cooperating with the guide portion. The impact end head is accelerated through the guide part, and the deviation direction after the explosion-proof barrel body is punched is avoided, so that the impact end head is ensured to be aligned with the weakening part, and the expected explosion effect is realized. Furthermore, the guide part can be used as an acceleration section of the explosion-proof cylinder body and used for realizing the directional acceleration effect on the impact end head, so that the speed of the impact end head reaches the speed required by the specific position of the gate structure after the impact.
According to the above aspect of the present invention, preferably, the guide portion may be formed in the form of a flat boss protruding radially inward from the inner cavity, and the engagement portion may be formed in the form of a truncated flat. Through the matched boss planes, the impact head is easier to align and install in the explosion-proof cylinder, and the corresponding parts are easy to process, so that the manufacturing cost is reduced.
According to the above aspect of the present invention, preferably, the catching mechanism may include a shear pin, the explosion-proof cylinder includes a cylinder through-hole provided on the circumferential surface, and the impact tip includes a tip through-hole provided on the cylindrical base, and the cylinder through-hole and the tip through-hole are aligned such that the shear pin passes through the cylinder through-hole and the tip through-hole to attach the explosion-proof cylinder and the impact tip together. Therefore, when the equivalent of the explosive is lower than a certain specific range, the shearing pin cannot be sheared and disconnected, so that the structural integrity of the explosion-proof cylinder is ensured, and when the equivalent of the explosive is higher than or equal to the certain specific range, the shearing pin is sheared, so that the impact end head can be pushed out of the explosion-proof cylinder under the action of the explosive force of the explosive, and the explosion-proof device can realize directional explosion.
In accordance with the above aspect of the invention, preferably, the shear pin includes a weakened portion at the first and second ends, and the location of the weakened portion is disposed at an interface corresponding to the engagement of the explosion proof barrel and the impact tip. By virtue of the design of the weakened portion, when the equivalent weight of the explosive substance is higher than or equal to a certain specific range, the fracture of the shear pin only occurs at the interface where the explosion-proof cylinder and the impact tip are joined, thereby facilitating smooth punching-out of the impact tip.
According to the above aspect of the present invention, preferably, the first end of the explosion-proof cylinder may be provided with outwardly convex L-shaped stoppers arranged at intervals in the circumferential direction, and the end cap may be provided with inwardly convex blocking teeth at the open end, the blocking teeth and the L-shaped stoppers cooperating with each other to form a stopping structure for limiting the relative movement between the explosion-proof cylinder and the end cap. Through this kind of card structure for the connected form between end cover and the explosion-proof barrel is simple effective, avoids using a large amount of fasteners, can realize opening fast and closing of end cover, satisfies intensity and the fixed requirement of end cover simultaneously. Generally, the time interval from the discovery of suspicious explosives to the emergency disposal is very short, and the structure can meet the requirement of emergency placement time and ensure the structural locking between the end cover and the explosion-proof cylinder body.
In other preferred embodiments, the explosion proof device according to the invention may further comprise a locking screw which may be provided on the end cap, for example, and which is locked to the explosion proof cylinder through a side portion of the end cap to restrict circumferential movement of the end cap relative to the explosion proof cylinder.
According to the above aspect of the present invention, preferably, the explosion-proof cylinder may further include a raised strip disposed around a circumferential direction of the explosion-proof cylinder, and the holding portion of the support base includes a collar disposed adjacent to the raised strip on a side of the raised strip near the first end of the explosion-proof cylinder. Through the structure, the connection form between the supporting seat and the explosion-proof cylinder body is simple, the actual operation is simple, the fixation of the explosion-proof cylinder body can be quickly realized, and meanwhile, the radial movement of the explosion-proof cylinder body in the explosion process can be effectively prevented; in addition, the connection form between the supporting seat and the explosion-proof body avoids welding the supporting seat on the explosion-proof cylinder body, so that the occupied space of each structural component is relatively small; the clamp can strengthen the structure of the anti-explosion barrel from the outside, so that the anti-explosion barrel is protected, the anti-explosion barrel can bear larger explosion load, the thickness of the structure of the anti-explosion barrel is prevented from being increased, and the weight of the structure can be reduced;
in other preferred embodiments, the clamp may further include cooperating first and second halves pivotally connected at one end via a pivot and removably connected at the other end via a fastener. A faster and reliable attachment of the explosion-proof cylinder to the bearing block and thus to a base structure, such as an aircraft floor beam, is thereby achieved.
According to another aspect of the invention, the invention relates to an aircraft comprising an explosion protection arrangement of the above aspect, the aircraft further comprising a floor cross-member and a rear gate structure attached to the aircraft frame, wherein the explosion protection arrangement is attached to the floor cross-member via a bracket such that the impact end of the explosion protection arrangement body faces towards the structurally weakened portion of the rear gate structure.
In summary, the explosion-proof device according to the present invention can implement different operation modes according to the equivalent of explosives, so that when the equivalent of explosives is lower than a predetermined threshold value, the explosion-proof device can maintain structural integrity without structural damage, and when the equivalent of explosives is higher than or equal to the predetermined threshold value, the directional blasting of the weakened structure on the aircraft is implemented, thereby protecting passengers and the safety of the aircraft to the maximum extent.
Drawings
For further explanation of the explosion protection arrangement according to the invention, the invention will be explained in detail below with reference to the accompanying drawings and specific embodiments, in which:
FIG. 1 is a schematic perspective view of an explosion vent in accordance with a non-limiting embodiment of the present invention;
FIG. 2 is a schematic perspective view of an explosion vent body of an explosion vent in accordance with a non-limiting embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of an explosion vent body of an explosion vent in accordance with a non-limiting embodiment of the present invention;
FIG. 4 is a schematic perspective view of an explosion proof cartridge of an explosion proof device body according to a non-limiting embodiment of the present invention;
FIG. 5 is a schematic perspective view of an end cap of an explosion vent body in accordance with a non-limiting embodiment of the present invention;
FIG. 6 is a schematic perspective view of an impact tip of an explosion vent body in accordance with a non-limiting embodiment of the present invention;
FIG. 7 is a schematic perspective view of a shear pin of the explosion vent in accordance with a non-limiting embodiment of the present invention;
FIG. 8 is a schematic perspective view of a backup pad of an explosion vent in accordance with a non-limiting embodiment of the present invention in an open state;
FIG. 9 is a schematic perspective view of a backup pad of an explosion vent in a closed state in accordance with a non-limiting embodiment of the present invention;
FIG. 10 is a schematic perspective view of a connection joint of a bearing block according to a non-limiting embodiment of the present invention;
FIG. 11 is a schematic perspective view illustrating the installation location of an explosion vent in an aircraft passenger cabin, according to a non-limiting embodiment of the present invention; and
FIG. 12 illustrates the air pressure relationship as the impact tip punches out a structurally weakened portion of the rear gate structure of an aircraft, in accordance with a non-limiting embodiment of the present invention.
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 is also to be understood that the specific devices illustrated in the attached drawings, and described in the specification are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, unless otherwise expressly stated, specific paths of motion, directions, or other physical characteristics relating to the various embodiments disclosed should not be considered as limiting.
In 11.2008, the U.S. Federal aviation administration added more airworthiness requirements for civil aircraft security work in FAR 25-127 amendment "Security considerations in the design and operation of transportation aircraft" and reflected these requirements in a modified 25.795 "Security issue" where for minimum risk bomb position work it was required that the requirements of the amendment, including the LRBL must be set, must be met for aircraft with certified passenger seat volumes in excess of 60 people or a maximum gross takeoff weight in excess of 100,000lb (45,359 kg). Meanwhile, the implementation of AC 25.795-6< blast Risk Bomb Location > aiming at LRBL in civil aircraft design work according to the term 25.795 can minimize the damage of explosion or deflagration events to the aircraft and passengers in the flight process, and greatly improve the safety of aviation operation. Meanwhile, the domestic civil aviation administration also puts forward relevant airworthiness requirements for some accidental situations which are harmful to flight safety, such as finding explosives and the like in aviation flight, for example, in CCAR121, 121.422: the security training of the crew members and the twenty-third requirement of the CCAR332 part, namely the handling method for finding the bomb when the aircraft is turned off, all require that the civil aircraft must provide a coping procedure and a coping method for finding the explosive on the aircraft, and the civil passenger aircraft can be put into airline operation formally by airworthiness examination of the terms.
The design of the minimum risk bomb position is necessary in the aircraft such as a civil passenger plane, and the damage to the aircraft and passengers caused by the explosion of explosives at the position can be minimized through the design work of the minimum risk bomb position, so that the operation safety of the civil aircraft is guaranteed to the maximum extent. The position of the minimum risk bomb is basically arranged in the rear half section of the passenger cabin, and the models are different. Away from the aircraft core control area (cockpit and front), away from the fuel tanks (wings) and engines, and also away from the tail (rudder, horizontal tail). However, designing only the minimum risk bomb position is still insufficient, and in order to minimize the impact of explosives on the aircraft, an explosion protection device is also typically required to be used in conjunction with the minimum risk bomb position.
The explosion-proof device 100 according to a non-limiting embodiment of the present invention will be described in detail with reference to the accompanying drawings. In the following description of the preferred embodiment in conjunction with the drawings, the explosion protection device 100 is used in conjunction with the minimum risk bomb position of clause FAA 25.795 (c). In the preferred embodiment of the present application, rear gate structure 202 of aircraft 200 is selected as the location for a low risk bomb to ensure that the structural integrity of the aircraft 200 fuselage is not significantly compromised when rear gate structure 202 is compromised. It should be understood that in other embodiments, the explosion proof device 100 may be used with other minimum risk bomb locations that meet the requirements.
Fig. 1 is a schematic perspective view of an explosion vent 100 according to a non-limiting embodiment of the present invention.
As shown in fig. 1, the explosion proof device 100 may include an explosion proof device body 10 and a support base 20, wherein the explosion proof device body 10 may have a hollow interior cavity for containing suspected explosives or other dangerous objects; and cradle 20 is adapted to cooperate with explosion proof device body 10 for securing explosion proof device body 10 to the aircraft at the minimum risk bomb position and maintaining proper orientation of explosion proof device body 10. It should be understood that while the preferred embodiment of the present invention shows the explosion vent body 10 and seat 20 used in combination to fixedly hold the explosion vent body 10 in a desired position, in an alternative embodiment or in a crisis situation, the explosion vent body 10 may be snapped or secured by means of structures inherent on the aircraft and held in a desired orientation, and in some cases, held and held in a fixed orientation by a robot/arm or crew, for example.
Fig. 2 and 3 are a schematic perspective view and a sectional view, respectively, of an explosion proof device body 10 of an explosion proof device 100 according to a non-limiting embodiment of the present invention.
As shown, the explosion proof device body 10 may include an explosion proof cylinder 11, an end cap 12, an impact tip 13, and a shear pin 14. The explosion proof cylinder 11 may include a cylindrical interior cavity, the end cap 12 may removably cover a first end 111 of the explosion proof cylinder 11, and the impact tip 13 may be received in a form fit in a second end 112 of the explosion proof cylinder 11 to cover the second end 112, such that the end cap 12, the explosion proof cylinder 11, and the impact tip 13 form a closed cavity/space to contain suspected explosives or other hazardous materials.
Fig. 4-6 are schematic perspective views of the explosion proof cylinder 11, end cap 12 and impact tip 13, respectively, of the explosion proof device body 10 according to a non-limiting embodiment of the present invention.
As shown and by way of non-limiting example of the invention, the explosion proof cylinder 11, end cap 12 and impact tip 13 may be formed by casting, for example, from an aluminum alloy, titanium alloy or stainless steel, etc., to provide sufficient burst strength to the explosion proof device body 10 and may be machined to desired final dimensions to provide the desired precision of the various parts. And each part can also be provided with a multi-layer energy-absorbing structure, such as a porous foamed aluminum interlayer, a corrugated lining layer or a composite material layer, so that the explosion-proof device body 10 has the characteristics of high strength and good elastic-plastic effect, and can better play roles in explosion protection and explosion energy absorption.
As shown in more detail in fig. 3 and 4, the explosion proof cylinder 11 may be integrally formed as a cylindrical structure and may include a raised band 113 disposed about the circumferential (hoop) direction of the explosion proof cylinder 11 on the circumferential outer surface, such as two spaced raised bands 113 shown in fig. 4, the raised bands 113 may serve to further enhance the strength of the explosion proof cylinder 11 on the one hand and to support and retain the explosion proof cylinder 11 on the other hand, as will be described in more detail later in connection with the structure of the backup pad 20.
The inner cavity of the explosion-proof cylinder 11 is provided on the inner surface near the second end 112 with a guide 114 which is guided in the axial direction of the explosion-proof cylinder 11, for example in the form of a planar boss which extends from a distance near the second end 112 to the end of the second end 112, which planar boss can be symmetrically formed to project radially inwards from the inner cavity, so that the planar boss can be used for mounting positioning of the impact tip 13 on the one hand and for guiding and accelerating the impact tip 13 when the equivalent of an explosive is greater than or equal to a predetermined threshold value. For example, the portion of the explosion-proof cylinder 11 having the guide portion 114 may be referred to as a tip acceleration section, and the rest of the explosion-proof cylinder 11 is used to place explosives.
As shown in more detail in fig. 3 and 6, the impact tip 13 may include a cylindrical base 131 and a tapered portion having a tip 134, wherein the cylindrical base 131 is received in the internal cavity with a clearance fit and includes a mating portion 132 that cooperates with the guide portion 114, and the tip 134 faces outside of the internal cavity. The fitting portion 132 may be formed in a truncated planar form so as to fit with a planar boss of the guide portion 114.
It should be understood that while the guide portion 114 and mating portion 132 shown in connection with the figures are shown in the form of a boss flat mating, other types of guide structures, such as rail runners or guide pin slide mating, etc., may be envisioned by those skilled in the art without departing from the scope of the present invention. Also, while cylindrical base 131 is received in the internal cavity with a clearance fit here, cylindrical base 131 may also be received in the internal cavity with an interference fit, and in some embodiments, the frictional force that such interference fit creates between the inner surface of explosion proof barrel 11 and the outer surface of impact tip 13 may act as a detent mechanism so that impact tip 13 does not punch out of explosion proof barrel 11 when the explosive force is less than the frictional force.
As shown in more detail in fig. 4 and 6, the explosion proof cartridge 11 may include a cartridge through hole 115 disposed on a circumferential surface, such as on the raised band 113, while the impact tip 13 includes a tip through hole 133 disposed on a cylindrical base, with the cartridge through hole 115 and the tip through hole 133 being aligned such that the shear pin 14 passes through the cartridge through hole 115 and the tip through hole 133 to attach the explosion proof cartridge 11 and the impact tip 13 together. These structures cooperate to form another detent mechanism in accordance with the concepts of the present invention, and the details of construction and principles of operation thereof will be further described below.
Fig. 7 is a schematic perspective view of shear pin 14 of explosion vent apparatus 100 in accordance with a non-limiting embodiment of the present invention.
As shown, the shear pin 14 may be included at a first end 141 and a second end 142, the first end 141 may be formed as a retaining head with an increased diameter and may be shaped with a suitable gripping structure to facilitate installation, while the second end may include a threaded fastener, such as a nut and stud fit, to secure the shear pin 14 in the desired installation location. In addition, as shown in fig. 7, the shear pin 14 may further include two weakened portions 143 at circumferentially inner portions of the first and second ends 141 and 142, and the positions of the weakened portions 143 are set at the interfaces corresponding to the engagement of the explosion proof cylinder 11 and the impact tip 13. The weakened portion 143 may be formed in the form of a circumferential groove such that the weakened portion 143 breaks first when subjected to the impact of a shear force. The breaking strength requirement of the weakened portion 143 may be set in accordance with the explosive equivalent, for example, designed in conjunction with case specifications of airports, explosive compositions, the blast strength of the explosion-proof cylinder 11, and the like, such that when the explosive equivalent is greater than or equal to a predetermined threshold value, the weakened portion 143 is completely broken (broken), and when the explosive equivalent is lower than the predetermined threshold value, the weakened portion 143 is not completely broken. The structure of the weakened portion 143 may also be designed such that, once the weakened portion 143 is completely broken (broken), its cross section (axial end face at the broken portion) is smooth without forming a concavo-convex or burr-like structure to facilitate smooth punch-out and impact direction positioning of the impact tip 13.
The shear pin 14 is a selectively detented detenting mechanism for interacting with the impact tip 13 and the explosion proof barrel 11 such that the shear pin 14 limits relative movement between the impact tip 13 and the explosion proof barrel 11, e.g., axial movement of the impact tip 13 away from the explosion proof barrel 11, when the force acting on the shear pin 14 is less than a predetermined threshold; and when the force acting on the shear pin 14 is greater than or equal to the predetermined threshold value, the shear pin 14 fails, e.g., the two weakenings 143 break simultaneously, and the shear pin 14 no longer restricts relative movement between the impact tip 13 and the explosion proof cylinder 11, thereby enabling the impact tip 13 to move in the axial direction relative to the explosion proof cylinder 11, thereby punching out the explosion proof cylinder 11.
It should be understood that while the preferred embodiment described in connection with the drawings describes the principle of operation of the catch mechanism by way of shear pin 14, it should be understood that the catch mechanism is not limited to shear pin 14, but may include any structure capable of selectively limiting relative movement, particularly axial movement, between impact tip 13 and explosion proof cylinder 11, such as, but not limited to: the impact end head 13 and the anti-explosion barrel body 11 are in interference fit; a projection provided on the circumferential surfaces of the impact tip 13 and the explosion-proof cylinder 11, such as the outer surface of the cylindrical portion of the impact tip 13 or the inner surface of the cylinder of the explosion-proof cylinder 11; or stop structures or the like provided at the end of the second end 112 of the explosion proof cylinder 11, provided that these structures are such that when the force acting thereon is less than a predetermined threshold, it limits relative movement between the impact tip 13 and the explosion proof cylinder 11, e.g. axial movement of the impact tip 13 away from the explosion proof cylinder 11; and when the force acting thereon is greater than or equal to a predetermined threshold value, it fails (e.g., breaks) to enable the impact tip 13 to move in the axial direction relative to the explosion proof cylinder 11, thereby punching out the explosion proof cylinder 11. And a plurality of these structures may be used in combination to achieve the desired selective retention performance.
In addition, although in the preferred embodiment described in connection with the drawings, the shear pin 14 is provided with a weakened portion 143, alternatively, the breaking strength may be sufficient to break at a predetermined threshold over the entire length of the shear pin 14.
As shown in more detail in fig. 4 and 5, the first end 111 of the vent cartridge 11 may be provided with circumferentially spaced outwardly projecting L-shaped stops 116, for example the L-shaped stops 116 may be evenly spaced axially along the distal end of the first end 111, with the larger dimension base of the L-shaped stops 116 aligned with the distal end of the first end 111 and the smaller dimension upper portion of the L-shaped stops 116 extending in an axial direction towards the second end 112. Accordingly, the end cap 12 is provided at the open end with inwardly projecting catch teeth 121, e.g., the catch teeth 121 may be evenly spaced circumferentially along the end cap 12 at the open end such that the catch teeth 121 are interfitted with the L-shaped stoppers 116, e.g., the catch teeth 121 may be of a generally square configuration having a width in the circumferential direction that is less than the spacing of the bases of the L-shaped stoppers 116 in the circumferential direction such that the catch teeth 121 pass through the bases through the gaps between the bases of the L-shaped stoppers 116 and rotate toward the upper portion of the L-shaped stoppers 116 to latch to the L-shaped stoppers 116, thereby forming a latching structure that limits relative movement between the explosion proof cylinder 11 and the end cap 12.
According to a preferred embodiment of the present invention and by way of non-limiting example, the explosion proof device body 10 may further include a locking screw 15, the locking screw 15 being threadably compressed to the explosion proof cylinder 11 through, for example, an opening on the side of the end cap 12, such that once the end cap 12 is snap fitted to the explosion proof cylinder 11, the explosion proof cylinder 11 is locked in place by the locking screw 15, thereby limiting circumferential rotational movement therebetween.
Figures 8 and 9 are schematic perspective views of the supporting seat 20 of the explosion-protection device 100 according to a non-limiting embodiment of the invention, in an open condition and in a closed condition, respectively.
As shown, the bearing block 20 may comprise a bracket 21, a holding portion 22 and a connecting joint 23, the bracket 21 may be used to attach the bearing block 20 to a foundation, such as a floor beam 201 near a rear gate structure 202 of the aircraft 200, by means of the connecting joint 23; while the retainer 22 serves to securely support the vent body 10 so that the impact tip 13 of the vent body 10 is always aligned with the weakened structure of the rear gate structure 202 and the recoil that it generates when the impact tip 13 is punched out of the vent barrel 11 does not cause significant displacement of the vent barrel 11 in the opposite direction, or at least its displacement does not cause structural damage to other structures within the passenger compartment.
As shown in fig. 8 and 9, the retaining portion 22 of the support block 20 comprises a clip that is disposed adjacent the raised strip 113 on the side of the raised strip 113 that is adjacent the first end 111 of the vent cartridge 11. In a preferred embodiment, the clamp may include cooperating first and second half rings 221, 222, the first and second half rings 221, 222 being pivotably connected at one end via a pivot 223 and detachably connected at the other end via a fastener 224, to achieve a quick and secure coupling of the explosion proof device body 10.
When the holding portion 22 is in the open state as shown in fig. 8, the explosion-proof device body 10 is placed on the first half ring 221, then the second half ring 222 is pivoted about the pivot 223 to close the holding portion 22, and then the first half ring 221 and the second half ring 222 are fastened together by the fastener 224, thereby firmly holding the explosion-proof device body 10 on the support base 20 and thus firmly attached to the floor cross member 201 near the rear boarding gate structure 202.
Referring back to fig. 1, the first half ring 221 and the second half ring 222 can reinforce the exterior of the explosion-proof cavity to prevent the explosion from damaging the wall of the barrel, and at the same time, the two annular raised bands 113 on the explosion-proof barrel 11 cooperate with the supporting seat 20 to prevent the explosion-proof device body 10 from moving axially due to the recoil of the explosion, so that the impact tip 13 cannot be punched out of the weakened structure of the rear boarding gate structure 202, or the explosion-proof device body 10 can cause undesired damage to other structures in the passenger cabin.
It should be noted that the cradles 20 shown in fig. 8 and 9 are shown only in a single piece for simplicity, but in the preferred embodiment the cradles 20 are used in pairs (e.g., shown in detail in fig. 1) to cooperate with the two raised strips 113 of the explosion proof device body 10 to better support and retain the explosion proof device body 10.
Figure 10 is a schematic perspective view of the connection joint 23 of the bearing block according to a non-limiting embodiment of the present invention.
As shown, the connector lug 23 may be formed as an L-shaped structure with reinforcing ribs, the upper portion of which is provided with threaded holes for securing with fasteners to the bracket 21, while the side portions are likewise provided with threaded holes for securing with fasteners to the floor cross member 201 adjacent the rear gate structure 202, thereby facilitating the removable fastening of the support base 20 to the structure of the aircraft 200 for adjusting the mounting position and orientation of the blast apparatus body 10 according to the location of the minimum risk bomb.
Fig. 11 is a schematic perspective view illustrating an installation position of the explosion vent 100 in a passenger compartment of an aircraft 200 according to a non-limiting embodiment of the present invention.
As shown in fig. 11, the aircraft 200 may further include a floor cross member 201 attached to the aircraft frame and a rear gate structure 202, wherein the vent 100 is attached to the floor cross member 201, for example via brackets 21, such that the impact tip 13 of the vent body 10 faces the structurally weakened portion of the rear gate structure 202. Thus, when the equivalent weight of the explosive is higher than or equal to the predetermined threshold value, the shear pin 14 is broken, the impact tip 13 is accelerated to a certain speed through the acceleration section, and the structural weakening part of the post-impact gate structure 202 is broken, so that the directional blasting is realized. Because only the rear boarding gate structure is damaged, the integrity of the main body structure of the aircraft can be ensured not to be damaged.
Fig. 12 illustrates the air pressure relationship as impact tip 13 impacts the structurally weakened portion of rear gate structure 202 of aircraft 200, in accordance with a non-limiting embodiment of the present invention.
As shown, second end 112 of vent apparatus 100 and impact tip 13 face aft gate structure 202. If the explosive equivalent is below the predetermined threshold, the latching mechanism in the vent 100 does not fail (e.g., the shear pin 14 does not break), and the high pressure created by the explosion will be borne by the entire vent 100 and no structural failure will occur. When the equivalent weight of the explosive is greater than or equal to the predetermined threshold, the catch mechanism fails (e.g., the shear pin 14 is completely broken), and the impact tip 13 breaks through the rear gate structure 202. For convenience, the air pressure outside the aircraft is denoted by P1, the air pressure in the aircraft cabin is denoted by P2, and the air pressure at the breach port is denoted by P3. For example, when the explosive explodes and the shear pin 14 is not broken, the pressure in the passenger cabin does not change significantly when P1 < P2 is P3; when the shear pin 14 is completely broken and the impact end 13 does not rush out of the explosion-proof cylinder 11, the pressure in the passenger cabin does not change obviously when P1 is more than P2 and P3 is less than the total pressure; after the impact end 13 is flushed out of the explosion-proof cylinder 11 and breaks the rear boarding gate structure 202, in a short time, P1 is greater than P2 and is greater than P3, and P3 is much greater than P2 and P1, most of high-pressure airflow generated by explosion diffuses to the outside of the aircraft 200 through a pressure relief port formed in the rear boarding gate structure 202, and only a small part of airflow flows into a passenger cabin to complete pressure relief, so that the body structure of the aircraft 200 is protected from being damaged, and the safety of the aircraft 200 and passengers or goods is ensured.
As used herein, the terms "first" or "second", etc., used to indicate a sequence, are only for the purpose of making the concept of the present invention shown in the form of preferred embodiments better understood by those of ordinary skill in the art, and are not intended to limit the present invention. Unless otherwise specified, all sequences, orientations, or orientations are used for the purpose of distinguishing one element/component/structure from another element/component/structure only, and do not imply any particular sequence, order of installation, direction, or orientation, unless otherwise specified. For example, in an alternative embodiment, "first end" may be used to represent "second end".
It should be understood that while the present invention describes explosion suppression apparatus 100 in conjunction with aircraft 200 and a minimum risk bomb location, explosion suppression apparatus 100 may alternatively not be used in conjunction with a minimum risk bomb location, but may be mounted to other suitable locations on aircraft 200.
In addition, the explosion proof apparatus 100 according to a non-limiting embodiment of the present invention may also be applied to transportation means such as trains such as high speed trains or subways, ships such as cruise ships or long distance buses, and may also be applied to public places such as airports, train stations, long distance stations or subway stations, or other places that may be susceptible to terrorist activities. And depending on the application scenario, the vent body 10 of vent 100 may be used separately from backup pad 20 or in conjunction with the specific structure of a building or vehicle on site without departing from the scope of the present invention.
In summary, the explosion-proof device 100 according to the embodiment of the present invention overcomes the disadvantages of the prior art and achieves the intended purpose.
While the explosion protection device of the present invention has been described in connection with the preferred embodiments thereof, it will be understood by those skilled in the art that the foregoing examples are illustrative only and are not to be construed as limiting the invention. Therefore, various modifications and changes can be made to the present invention within the spirit and scope of the claims, and these modifications and changes will fall within the scope of the claims of the present invention.
Claims (10)
1. Explosion protection device (100), characterized in that it comprises: an explosion-proof device body (10) which comprises an explosion-proof cylinder body (11), an end cover (12), an impact end head (13) and a clamping and stopping mechanism, wherein the end cap (12) covers the first end (111) of the explosion-proof cylinder (11), the impact tip (13) being received in the second end (112) of the explosion proof cylinder (11) to cover the second end (112), and the catch means interacting with the impact tip (13) and the explosion-proof cylinder (11) such that, when the force acting on the catch means is less than a predetermined threshold value, the clamping and stopping mechanism limits the relative movement between the impact end head (13) and the explosion-proof cylinder body (11), and when a force acting on the detent mechanism is greater than or equal to the predetermined threshold, the detent mechanism is disabled, so that the impact tip (13) can be moved in the axial direction relative to the explosion-proof cylinder (11).
2. Explosion vent (100) according to claim 1, characterized in that it further comprises a support seat (20) comprising a bracket (21) attached to the foundation and a retaining part (22) firmly supporting the body (10) of the explosion vent.
3. An explosion proof device (100) as claimed in claim 2, wherein the explosion proof cartridge (11) comprises a cylindrical internal cavity and the impact tip (13) comprises a cylindrical base (131) and a conical portion with a point (134), wherein the cylindrical base (131) is received in the internal cavity with a clearance fit and the point (134) is directed towards the outside of the internal cavity.
4. Explosion-proof device (100) according to claim 3, characterized in that the internal cavity of the explosion-proof cartridge (11) is provided on the inner surface close to the second end (112) with a guide (114) which is guided in the axial direction of the explosion-proof cartridge (11), while the cylindrical base of the impact tip (13) comprises a mating portion (132) which cooperates with the guide (114).
5. Explosion vent (100) according to claim 4, characterized in that the guide part (114) is formed in the form of a planar boss projecting radially inwards from the inner cavity, while the mating part (132) is formed in the form of a truncated plane.
6. The explosion vent apparatus (100) of claim 3, wherein said catch mechanism comprises a shear pin (14), said explosion vent cartridge (11) includes a cartridge through hole (115) disposed on a circumferential surface, and said impact tip (13) includes a tip through hole (133) disposed on said cylindrical base, and said cartridge through hole (115) and said tip through hole (133) are disposed in alignment such that said shear pin (14) passes through said cartridge through hole (115) and said tip through hole (133) to attach said explosion vent cartridge (11) and said impact tip (13) together.
7. The explosion vent apparatus (100) of claim 6, wherein the shear pin (14) includes a weakened portion (143) at a first end (141) and a second end (142), and the weakened portion is located at a location corresponding to an interface at which the explosion vent barrel (11) and the impact tip (13) engage.
8. Explosion vent apparatus (100) as set forth in any of claims 1 to 7, wherein the first end (111) of the vent cartridge (11) is provided with outwardly projecting L-shaped stops (116) arranged in circumferentially spaced apart relation, and the end cap (12) is provided at the open end with inwardly projecting catches (121), the catches (121) and the L-shaped stops (116) cooperating to form a catch structure that limits relative movement between the vent cartridge (11) and the end cap (12).
9. Explosion vent device (100) according to any one of claims 2 to 7, wherein the explosion vent cylinder (11) further comprises a raised strip (113) arranged around the circumference of the explosion vent cylinder (11), and the retaining portion (22) of the bearing block (20) comprises a collar arranged adjacent to the raised strip (113) on the side of the raised strip (113) which is adjacent to the first end (111) of the explosion vent cylinder (11).
10. An aircraft (200) comprising an explosion vent device (100) according to any one of claims 2 to 7, further comprising a floor cross member (201) attached to an aircraft frame and a rear gate structure (202), wherein the explosion vent device (100) is attached to the floor cross member (201) via the bracket (21) such that the impact tip (13) of the explosion vent body (10) faces a structurally weakened portion of the rear gate structure (202).
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| CN202110979582.2A CN113624090B (en) | 2021-08-24 | 2021-08-24 | Explosion-proof device and aircraft |
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| CN202110979582.2A CN113624090B (en) | 2021-08-24 | 2021-08-24 | Explosion-proof device and aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116164607A (en) * | 2022-10-25 | 2023-05-26 | 北京理工大学 | Non-inclusive airborne antiknock device |
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| CN113624090B (en) | 2022-09-23 |
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