CN101018709B - Reinforced door - Google Patents
Reinforced door Download PDFInfo
- Publication number
- CN101018709B CN101018709B CN2005800261532A CN200580026153A CN101018709B CN 101018709 B CN101018709 B CN 101018709B CN 2005800261532 A CN2005800261532 A CN 2005800261532A CN 200580026153 A CN200580026153 A CN 200580026153A CN 101018709 B CN101018709 B CN 101018709B
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- plate
- reinforced door
- framework
- attaching parts
- door
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- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 6
- 239000004917 carbon fiber Substances 0.000 claims abstract description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 6
- 210000000078 claw Anatomy 0.000 claims description 16
- 238000009434 installation Methods 0.000 claims description 4
- 229920002994 synthetic fiber Polymers 0.000 claims description 2
- 210000001364 upper extremity Anatomy 0.000 claims description 2
- 238000005728 strengthening Methods 0.000 claims 1
- 230000006837 decompression Effects 0.000 description 22
- 230000004888 barrier function Effects 0.000 description 8
- 230000003014 reinforcing effect Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000007789 sealing Methods 0.000 description 3
- 238000005054 agglomeration Methods 0.000 description 2
- 230000002776 aggregation Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 230000009545 invasion Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 210000001050 stape Anatomy 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 240000006829 Ficus sundaica Species 0.000 description 1
- 241000863032 Trieres Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 239000002131 composite material Substances 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 244000144985 peep Species 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
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Images
Classifications
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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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1469—Doors between cockpit and cabin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0015—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems
- B64D45/0021—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems means for restricting access to flight deck
- B64D45/0026—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems means for restricting access to flight deck by creating a secure space between the flight deck and cabin
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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
- B64C2001/009—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising decompression panels or valves for pressure equalisation in fuselages or floors
Abstract
The invention concerns a door comprising elements (20, 21, 22, 24) forming an inner structure (16). Said inner structure (16) is reinforced by a system (82) of straps connecting most of the elements forming the inner structure. Said straps are for example carbon fiber ribbons bonded on the inner structure.
Description
Technical field
The present invention relates to be used for the internal security door of aerocraft.
Background technology
After terror attacks of 11 September 2001, taken measures to strengthen the safety of aerocraft driving compartment.These measures are especially at the door that aerocraft driving compartment and its main cabin are separated.According to new standard, this door must form a barrier, stoping any intrusion driving compartment, and enters driving compartment and only limits to bus attendant now.
But, as in the past, be in the main cabin one side or when decompression appearred in driving compartment one side, cockpit door should self-opening when no matter.
The objective of the invention is to strengthen safety on the machine of aerocraft by making invasion and attack person be difficult to enter driving compartment more.
Although should be pointed out that to dispose is used to prevent the safety system of opening the door,, door will be opened, so that for example allow chaufeur or copilot pass through, and invasion and attack person can utilize this chance of opening the door to slip into driving compartment, because safety device is invalid at this moment.Therefore, the weakness of present cockpit door is: they especially during the distance flight, are opened during flying sometimes.Innovation thinking as basis of the present invention is: prevent that those passengers that are under an embargo the discrepancy driving compartment from knowing when cockpit door is opened.
In some aerocraft, cockpit door is positioned at the end in passageway, and a space of using for bus attendant is basically led in this passageway, and the lavatory generally is located in this space.Some airline company allows the passenger to use described lavatory.
Innovation thinking of the present invention is that one side adopts one second this passageway of sealing in the main cabin.This second to be main purpose as one visual barrier, finds out to prevent the passenger whether cockpit door opens or closes.
A solution is: at passageway tip placement one door curtain relative with cockpit door.This solution may be fit to, but obviously it does not have interception to the attacker.
Therefore, the present invention aims to provide a rigid barrier, and the form that it is is used to seal the passageway that is positioned at the cockpit door back, but also can be used for other position on the machine of aerocraft.
What be fit to is to take place under the situation of decompression at this a side or opposite side, and this door still keeps being connected as a single entity.In fact, if it is broken into the polylith fragment, the personnel that these fragments thereby can endanger with regard to formation are on the aerocraft launch thing.Advantageously, this door is light.In fact, the same with all parts on being loaded in aerocraft, make every effort to limit loading mass.At last, when this door was used to seal the passageway of driving compartment back, advantageously, this also formed one barrier that the attacker is difficult to cross.
Summary of the invention
For this reason, the present invention proposes a reinforced door, and it is used for aerocraft, and has the member that forms an inner structure.
According to the present invention, inner structure is strengthened by a tape net, and described tape net connects the most of member that forms described inner structure.
At first, this tape net can be reinforced the structure of described door.This reinforcing can allow significantly to alleviate the weight of door, and makes it to have the mechanical strength that the conventional confguration with door is equal to.Secondly, under the situation of framework place fracture, tape can keep the broken segment of door, and thereby guarantees the agglomeration (coh é sion) of described door.At last, under situation about being attacked, tape forms one additional barrier that the attacker must cross.
In a preferred embodiment, tape is the form that is bonded in the band on the inner structure.This solution is easy to implement, and can make the tape net be connected in inner structure well.
Advantageously, tape use based on high strength synthetic fibre for example the material of carbon fiber make.The preceence of this material is to have fabulous mechanical specialities on the one hand, is light on the other hand.
In order to increase the effect of net, especially Men agglomeration and tackle the attacker and the effect of the barrier that forms, preferably, tape is arranged on the inner structure, and is connected to each other, to form a net.
In one embodiment, reinforced door according to the present invention is such: its inner structure has at least three vertical pillars, and described vertical pillars is connected by the attaching parts of horizontal arrangement.In this embodiment, tape is arranged on their the whole length along vertical pillars and horizontal connector.Therefore, tape does not enter in the lattice that is formed by the clearance envelope between column and the attaching parts.Therefore, these lattices can be furnished with " can eject " plate, and the tape net can not interfere with the ejection of described plate.
Description of drawings
From the description that hereinafter the appended scheme drawing of reference carries out, details of the present invention and advantage will be embodied better, and accompanying drawing is as follows:
Fig. 1 is the local section birds-eye view of aerocraft front portion;
Fig. 2 is the front elevation according to door of the present invention;
Fig. 3 is the horizontal sectional drawing by magnification ratio along Fig. 2 section line III-III;
Fig. 4 is the detail drawing of releasing mechanism, and described releasing mechanism is in locked position on Fig. 3;
Fig. 5 illustrates the mechanism of Fig. 4, and this mechanism is in the unlocked position;
Fig. 6 to Fig. 8 is such view: when decompression occurring in the aerocraft driving compartment, they are corresponding with Fig. 3;
Fig. 9 is the front elevation of the structure of supporting door shown in Figure 2;
Figure 10 is the section-drawing along Figure 11 section line X-X;
Figure 11 is the front elevation corresponding to Fig. 2, and it illustrates a structure reinforcement, and this structure reinforcement can be equipped on door shown in Figure 2;
Figure 12 and 13 is ratio enlarged drawings, and it is corresponding to Fig. 3, and the improvements according to the plate of door of the present invention are shown; And
Figure 14 illustrates assembly parts of two plates shown in Figure 12 and 13 in the mode of front elevation.
The specific embodiment
Fig. 1 illustrates the driving compartment 2 of long-range aircraft, long-haul aircraft.Just in time, the space more specifically to the crew is arranged in the back of driving compartment.This space has the regional 4--of a rest in a side, and it for example has the bunk, and has sanitary fixture at opposite side---and it for example has lavatory, a wash tub and a shower.One passageway 8 is arranged on has a rest between zone 4 and the sanitary fixture 6, so that allow the driving compartment 2 of coming in and going out.Traditionally, one 10 sealing driving compartment 2, and allow the described driving compartment 2 of door 10 discrepancy from then on.
The door 10 of driving compartment is this passageway 8 of sealing one of in the end in described passageway.Innovation be to propose in the passageway the other end of 8 and arrange one second 12.
Have two radical functions for second 12.First function is to make cockpit door 10 hidden in passenger's sight line.For this first function, described second 12 midway location that can be installed in the passageway 8 perhaps just is installed in the relative end of this passageway 8 and cockpit door 10.This another function of second is to make the zone that gives over to crew's special use have privacy.Should second function, preferably, second 12 is positioned at passageway 8 ends relative with cockpit door 10, as shown in Figure 1.
For safety, cockpit door 10 is locked during flying, and takes certain methods (come in and go out password, badge reader etc.) to attempt to prevent any unauthorized personnel driving compartment of coming in and going out.This cockpit door 10 also is ball proof.But when decompression occurring in the main cabin 14 at aerocraft, some devices can make this self-opening, so that the pressure between balance main cabin 14 and the driving compartment 2, and avoid the structure of aircraft is produced too big stress.
Especially when occurring decompression in the driving compartment 2, second 12 work that should not disturb cockpit door 10.
Fig. 2 illustrates with front elevation and is used to implement a preferred implementation of second 12 shown in Figure 1.This door has an inner structure, hereinafter is called framework 16.Eight plates 18 are installed in this framework 16.
Next, for describing second 12, can assert that this door is in its off position.Thereby can assert: when being in its as shown in figures 1 and 3 off position for second 12, this front surface is this surface towards driving compartment 2 orientations, and the rear surface of this door is 14 surfaces that are orientated towards the main cabin.Adjective " in-to-in " is relevant with second 12 with " exterior ".
Each plate 18 has two plates: a front panel plate 26 and a back plate 28.
In side direction column 20 1 sides, front panel 26 is kept by a distance piece 38 as mentioned below.Side direction column 20 has one the 3rd flange 40, and described the 3rd flange 40 is facing to first flange 30.Back plate 28 can be bearing on the inside face of the 3rd flange 40.Distance piece 38 can make front panel 26 and back plate 28 be held against the first and the 3rd flange 30,40 respectively.One cushion block 39 is arranged between back plate 28 and the distance piece 38.The shape of this cushion block 39 adapts to the shape that is the plane basically of back plate 28 in a side, and adapts to the shape of distance piece 38 at opposite side.
Therefore, separately two flanges 38 and 40 distance add the thickness of back plate 28 corresponding to the thickness of front panel 26, add the height of the assembly that is formed by distance piece 38 and cushion block 39.Distance piece 38 for example has the shape of a stapes (é trier), and its base portion is fixed on the inside face of front panel 26.The branching portion of this stapes shape body is bearing on the cushion block 39 that is connected with back plate 28.
The front is addressed, and how the vertical edge of back plate 28 is kept along side direction column 20.In gin pole 21 1 sides, the edge of back plate 28 can rest on the outside face of the 4th flange on one the 4th flange 42.This edge of back plate 28 is held against on the 4th flange 42 by means of a pin 44, and described pin 44 can be locked on the gin pole 21.Figure 4 and 5 illustrate a chamber 46, and it is used to lock pin 44 (see figure 3)s.Fig. 3 and Fig. 6 to Fig. 8 also illustrate, and back plate 28 is furnished with the bar 45 of finger, and these plates are remained on the flange 42.
Fig. 5 to Fig. 8 illustrates when at the aircraft forward i.e. state of plate 18 when decompression appears in second 12 front surface one side in driving compartment 2 for example.
In this case, when closing for second 12, it is in (aspir é e) passageway 8 in-to-in states that are attracted to.Second 12 framework 16 is rigidity, and is adapted to and can resists this decompression.Be designed to for second 12: plate 18 is removed, and is attracted to the inside in described passageway 8.
At first, the front panel 26 of each plate 18 is attracted to the inside in passageway 8.First flange 30 is fixed.On the contrary, corresponding claw 34 pivots.When the power that a claw 34 is applied is enough (each claw 34 is by a spring prestress), described claw 34 pivots, and the front panel 26 of unclamping plate 18.Therefore, this plate pivots around first flange 30, and drives distance piece 38 in company with this plate.So distance piece 38 can be on cushion block 39 " rolling ", the shape of described cushion block 39 is adapted to be beneficial to described distance piece 38 is broken away from.So the edge that back plate 28 rests on the 3rd flange 40 breaks away from, and described back plate 28 begins pivot (Fig. 7) with respect to the 4th flange 42.Refer to this pivoting action of bar 45 may command, and make the edge of back plate 28 keep being bearing on the 4th flange 42.A connection piece 48, for example a cable, a tape, a belt or analogue are connected in back plate 28 with front panel 26.This attaching parts 48 for example is fixed on the distance piece 38 in a side, and is fixed on the cushion block 39 at opposite side.
Fig. 8 illustrates two plates 18 of complete opening.It may be noted that this illustrates one second attaching parts 50 (for example it is similar to attaching parts 48), its back plate 28 with each plate 18 is connected in gin pole 21.Therefore plate 26 and 28 is kept, and does not constitute the thing that launches that may injure (and might cause death) crew.
Eight plates 18 are opened simultaneously.In fact, these plates stand identical decompression, therefore should react in a similar fashion.When the plate complete opening (Fig. 8), the framework 16 that has second 12 only stops back to front the air-flow relevant with the decompression that causes at driving compartment 2 places.This framework 16 has little resistance to flow, and corresponding loss of pressure can ignore (also can ignore to the stress that aircaft configuration produces).Therefore, in driving compartment 2, produce under the situation of decompression above-mentioned second 12 work that can not disturb cockpit door 10 at aircraft forward.
Show that from aforesaid explanation and corresponding Fig. 3 to Fig. 8 being used to of proposition, the system of unclamping plate 18 was one can self-contained again system.In fact, in a single day plate breaks away from its lattice, and these plates can be reinstalled in place without difficulty.As long as make plate 28 flange 42 and 40 of abutting against in place in its lattice, back at first again, then, reinstall corresponding front panel 26, make it against flange 30 and 32, the claw 34 that pivots again again, thus make corresponding spring (not shown) self-contained again.
The application force that applies the spring of the claw 34 that is used to pivot is determined according to second 12 acceptable load.Can calculate that the maximum decompression at this second 12 place is about 150hPa.When this decompression existed, plate unclamped.Be applied to the area that application force on second 12 is equivalent to framework this moment and multiply by institute's applied pressure.In order to limit the application force that is applied on second 12, can suppose that this application force is acceptable maximum force.If P
Unclamp() be and unclamp plate 18 cooresponding pressure relief value, so, and P
UnclampThe gross area that multiply by second 12 is then less than being applied on the described door and maximum force that calculate previously.Apply the spring of the claw 34 that is used to pivot, this moment is according to selected P
UnclampThe quantity of the area of value, corresponding plate 18 and the pivot claw 34 of every plate is regulated.
In a single day above stated specification shows that plate unclamps in gin pole 21 1 sides, and unclamps, these plates are in the middle part in passageway 8 basically again owing to the structure of described proposition.At first, plate is gathered, and can be avoided plate being arranged at two avris in passageway.But the plate major cause that 8 central authorities assemble towards the passageway but is other.When decompression appearred in driving compartment 2 places, it is 8 diffusions towards the passageway.Owing to reduce pressure, be positioned at the assembly of 8 both sides, passageway---be also referred to as " large-sized object (monument) ", be tending towards close to each other, thereby make the width in passageway 8 become narrow.At this moment, distortion may appear in these large-sized objects, so that they cover second 12 vertical edge.If this moment, plate 18 should unclamp at side direction column 20 places, so, this unclamping may be owing to large-sized object be hindered, even is prevented from.Form a barrier second 12 this moment, stops the balance of pressure in the aircraft.As mentioned above, this obviously will be avoided.Therefore, according to large-sized object position with respect to second in passageway 8, may should avoid on vertical side direction column, arranging claw (or other loose components), and select the central authorities of their propylaeums are arranged.
Take place at aircraft passenger compartment 14 places for example can consider to open second 12 under the situation of decompression.This unlatching can cause the load that causes because of centnifugal force, and described centnifugal force is produced by the motion on the point of connection up and down of the described aboard door of described door.
As mentioned above, in case decompression occurs in driving compartment 2 one sides, the structure of described plate 18 can be by front panel, be unclamping in succession of back plate then, and allows air to pass through.But described structure but makes: when from main cabin 14 towards driving compartment promptly from after when pushing plate 18 forward, described plate stands up to, and does not unclamp from framework 16.
In fact, as shown in Figure 3, it may be noted that to need only corresponding front panel 26 installation in position that each back plate 28 is just kept by stationary member.It may be noted that in described figure that in a side each back plate 28 can rest on one the 4th holding flange 42, and at opposite side, described back plate 28 can be bearing on one first holding flange 30 by a cushion block 39 and a distance piece 38.Therefore, if to one the back plate 28 from after apply an application force forward, this application force is then accepted by flange 42 and 30 fully.The application force that applies can not act on the described pivot claw that unclamps corresponding plate 18.
Fig. 9 illustrates a kind of possible installation method of described door on aircaft configuration as embodiment.This illustrates a upper beam 52 and one underbeam 54.Also illustrating one---described door pivots around described axle, and top board 58 described main cabin 14 and passageway 8 is shown.This axle is implemented as two parts: managing 56, one cylindrical arms 57 once can telescopically slide in described pipe 56.One fastening system---for example an inserting type system design is used for relative another ground locking of these members is especially locked it aspect translation.
The bottom of the axle of door is formed by pipe 56, is installed on the automatic aligning formula bearing.This bearing has a supporting member 64 that is fixed on the underbeam 54.This supporting member 64 has a chamber, and described seat chamber has a spherical continuing surface 66.One its diameter of spheroid 68--is equivalent to the diameter of spherical continuing surface 66 and has a plat part 70--for example is fixed on described pipe 56 by being spirally connected bottom alternatively.In a preferred embodiment, pipe 56 has a spherical continuing surface, is used to admit spheroid 68.When described spheroid 68 was installed in the spherical continuing surface 66 of supporting member 64, described spheroid 68 can be on the underbeam 54 time on described supporting member 64 is installed in the basal plane of aerocraft, aims at door-hinge automatically.
Second 12 telescopic shaft can make this Assembly ﹠Disassembly very easy.In order to install, arm 57 slides in pipe 56.Be installed on the spheroid 68 in case manage 56, the axle of door is oriented, and faces so that be in substantially with described bearing 60.Arm stretches out for 57 this moments, is locked at its extended position then.Dismounting can be implemented the mode of described installation procedure in reverse order and easily carry out.
Figure 12 to 14 illustrates air and how to pass second 12 front portion from aircraft and flow towards the rear portion.These accompanying drawings illustrate the front panel 26 of plate 18 and the structure of back plate 28 in more detail.
For air is passed through, in preferred embodiment shown in the drawings, back plate 28 is the form of net grid, for example as shown in figure 14.Hole 72 is distributed on the whole surface of back plate 28 (edge near except) alternatively, well-balancedly.
Figure 13 illustrates boiler check valve and is in its off position.When air-flow arrives from the outside, promptly when flow in the front portion, shift elastic memberance 76 on the front panel 26 onto, thereby seal corresponding cutting mouth 74 by this air-flow from the rear portion of aircraft for air-flow.On the contrary, as shown in figure 12, when air-flow arrives internally, promptly air-flow is when flow in (main cabin 14) towards the rear portion from the front portion (passageway 8) of aircraft, and elastic memberance 76 breaks away from the inside face of front panel 26, and is pushed to and covers 78.At this moment, air can pass free edge, the opening in lid 78 of cutting mouth 74, elastic memberance 76, passes through the hole 72 of back plate 28 then.
These boiler check valve be particularly useful for making give over to the crew, via the sensible zonal ventilation in passageway 8.They also are used to avoid making passageway superpressure, this superpressure obviously to cause this second 12 closes when closing for second 12.When suddenly decompression taking place in the main cabin 14, these valves also can play a role.At this moment, air can be from the passageway 8 flows to main cabin 14.
Through calculating, when decompression occurring in main cabin 14, the pressure at second 12 place changes basically less than cockpit door 10 places.In addition, this difference of pressure reduces fast, so that can be in main cabin 14 keep closing under the situation for decompression for second 12, and disturb the work of cockpit door 10.
In a preferred embodiment, also can consider the air by boiler check valve is filtered.Therefore, for example a foam plastic filter can cover the lid 78 of each valve.Also can the back plate 28 inside face on (rather than on the outer surface) set a filter, therefore, described filter covers the hole 72 of this plate.
Figure 10 and 11 illustrates and can strengthen a spare system of second 12.This system constitutes the structure of reinforced frame 16 by a reinforcing member (armure) 82.The main composition part of these reinforcing member 82 connecting frames makes it further to be connected to each other.This reinforcing member 82 for example is made of tape, and described tape is bonded on the member of framework, makes it to connect.Preferably, these tapes are made with carbon fiber.They are arranged on the framework 16, with form can with a tape net that is similar to screen.For this reason, attaching parts is provided between the different tapes.Described tape is along the shape of the band of column 20,21, torsion case 22 and crosspiece 24 layouts, does not influence plate 18 and upsprings under the situation of decompression so that take place in driving compartment.
Preferably, reinforcing member 82 is made based on carbon fiber.Here, this material has many preceences.At first, its mechanical strength can be strengthened the structure of second 12 framework 16.Secondly, low weight with the tape that this material is made, therefore, can not increase the weight of second 12 structure.The tape made from carbon fiber also is very difficult to cut off.Like this, just in case attacked, if there is the people to attempt firmly to crash through
12, so, reinforcing member 82 formation one are unfavorable for attacker's screen very much.The existence of this screen can increase the time that this attacker crosses second 12.Should the additional time may be valuable for the crew, under the situation of being attacked, the crew can hide in the driving compartment 2 of safety.
Above-mentioned second 12 can form one and be used for crew's the private space in its preferred implementation, and prevent that the passenger from seeing cockpit door.This second 12 by means of its double-walled plate structure, also makes the private space sound insulation of bus attendant.Clearance envelope between two plates of each plate can be realized good sound insulation.
Also form barrier one for second 12, retardance wants the terrorist who controls aircraft to enter driving compartment.Be suddenly under the situation of decompression in aircraft passenger compartment or its driving compartment, this second work of not disturbing cockpit door.
As mentioned above, this second 12 can be made into lightweight construction--light alloy door frame, composite plates etc., and it is acceptable overweight therefore aerocraft to be had.
Obviously, this door is furnished with the parts that make it to remain on its off position and open position thereof.Advantageously, this also is furnished with the parts that reset towards its off position.Therefore, in a single day described door is in the midway location between its open position and the off position thereof, just close automatically again.This base part is known in those skilled in the art, no longer describes here.For the purpose of safety more, also can set a discrepancy password of opening this.Also can set other means of identification (badge reader etc.).This door also can be furnished with monitoring device, thereby the crew who allows to be positioned at a side of the door of closing controls the main cabin.
Be furnished with to make the valve that air passes through the time when second, can see that the back plate 28 of plate 18 has the hole.These holes can be used to beautify described door.In fact, back plate 28 is positioned at aircraft passenger compartment one side, and the passenger sees.For example, can between two plates that form each plate, set an illumination equipment, with the reverse hole of illuminating the back plate.Therefore, these holes can be arranged by a special decoration pattern (figure, airline company's sign, explanatory note etc.).
By afore-mentioned as seen, above-mentioned door can adapt to many standards:
-under the situation of driving compartment place for decompression, it can carry out equilibrium of pressure,
-under the situation of place, main cabin for decompression, it also can make pressure balanced mutually,
-this door is designed under the very large situation of mechanical strees, still keeps being connected as a single entity,
-this weight is less relatively,
-this can be furnished with traditional closing appliance,
-can set supervisory system (peep hole, pick up camera etc.),
But-this door is SELF CL also,
But-this door is auto lock also,
-this private space that bus attendant acquisition is separated with the remainder in main cabin,
-can implement one from angle attractive in appearance, this remainder with the main cabin combines together.
The present invention is not limited to the above-mentioned preferred embodiment of being described as non-limiting example.The present invention also relates to all enforcement modification claims scope, in the scope of those skilled in the art's within the reach hereinafter.
Claims (9)
1. reinforced door, it is used for aerocraft, comprising:
One framework, described framework has vertical column, and described vertical pillars is connected by the attaching parts of horizontal arrangement;
A plurality of lattices, these lattices form and are equipped with plate by the clearance envelope between described column and the described attaching parts; With
A plurality of tapes, it connects the most described vertical column and the attaching parts of level, and described a plurality of tape is in place on the attaching parts of described vertical column and level, strengthening described framework, and is not in contact with a plurality of plates of installation site,
Wherein, between different described bands, be equipped with attaching parts.
2. reinforced door according to claim 1 is characterized in that, described tape is the form of the band on the attaching parts that is bonded in described vertical column and level.
3. reinforced door according to claim 1 is characterized in that described tape comprises high strength synthetic fibre.
4. reinforced door according to claim 3 is characterized in that described tape comprises carbon fiber.
5. reinforced door according to claim 1 is characterized in that, described framework has at least three vertical columns, and each described column extends to the lower edge of described reinforced door from the upper limb of described reinforced door; And described at least three vertical columns are connected by the attaching parts of horizontal arrangement.
6. reinforced door according to claim 5 is characterized in that, described tape is arranged on their the whole length along the described vertical column and the attaching parts of described level.
7. reinforced door according to claim 1 is characterized in that, described plate is configured to: during reducing pressure, described plate discharges from described framework, thereby contacts with described framework without any plate.
8. reinforced door according to claim 1 also comprises: claw, it is configured to described plate is remained in described framework, and discharges described plate during described aerocraft partly reduces pressure.
9. reinforced door according to claim 8 also comprises: link, it is connected to described plate, be formed at described plate discharge from described framework before and afterwards described plate is connected to described framework.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0408580A FR2873980B1 (en) | 2004-08-03 | 2004-08-03 | REINFORCED DOOR |
| FR0408580 | 2004-08-03 | ||
| US60652904P | 2004-09-02 | 2004-09-02 | |
| US60/606,529 | 2004-09-02 | ||
| PCT/FR2005/001823 WO2006024727A1 (en) | 2004-08-03 | 2005-07-18 | Reinforced door |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101018709A CN101018709A (en) | 2007-08-15 |
| CN101018709B true CN101018709B (en) | 2011-05-11 |
Family
ID=34947995
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2005800261532A Expired - Fee Related CN101018709B (en) | 2004-08-03 | 2005-07-18 | Reinforced door |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JP4809344B2 (en) |
| CN (1) | CN101018709B (en) |
| FR (1) | FR2873980B1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3165447B1 (en) * | 2015-11-09 | 2019-07-17 | Airbus Operations GmbH | Aircraft fuselage structure |
| US10766597B2 (en) * | 2018-02-08 | 2020-09-08 | The Boeing Company | Aircraft privacy door and door frame assembly |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19801842A1 (en) * | 1998-01-13 | 1999-07-22 | Sommer Allibert Lignotock Gmbh | Door of motor vehicle, providing better side impact resistance and more room for interior equipping |
| DE19931189A1 (en) * | 1999-07-07 | 2001-01-25 | Meritor Automotive Gmbh | Process for the production of components with electrical conductor tracks arranged therein, and components manufactured according to them, in particular as door modules for motor vehicles |
| JP2002359915A (en) * | 2001-05-31 | 2002-12-13 | Calsonic Kansei Corp | Wiring structure using fpc |
| GB2381551A (en) * | 2001-10-31 | 2003-05-07 | Michael James Wingrave Hall | Security system for a flight deck door |
| JP3999006B2 (en) * | 2002-03-12 | 2007-10-31 | 三ツ星ベルト株式会社 | Guide member for harness |
| EP1576248B1 (en) * | 2002-06-14 | 2017-03-01 | Hartwell Corporation | Pressure responsive blowout latch with reservoir |
| JP4012790B2 (en) * | 2002-09-06 | 2007-11-21 | 矢崎総業株式会社 | Power supply harness protector mounting structure |
| JP4045916B2 (en) * | 2002-10-08 | 2008-02-13 | 住友電装株式会社 | Car body fixing structure of wire harness |
| JP2004136711A (en) * | 2002-10-15 | 2004-05-13 | Sumitomo Wiring Syst Ltd | Fixing structure of wire harness to car body |
| JP3969276B2 (en) * | 2002-10-15 | 2007-09-05 | 住友電装株式会社 | Automotive wire harness |
| FR2848179B1 (en) * | 2002-12-09 | 2005-11-11 | Airbus France | DOOR TO BE INTERPOSED BETWEEN A COCKPIT AND A CABIN OF AN AIRCRAFT |
-
2004
- 2004-08-03 FR FR0408580A patent/FR2873980B1/en not_active Expired - Fee Related
-
2005
- 2005-07-18 JP JP2007524364A patent/JP4809344B2/en not_active Expired - Fee Related
- 2005-07-18 CN CN2005800261532A patent/CN101018709B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JP4809344B2 (en) | 2011-11-09 |
| FR2873980B1 (en) | 2006-10-13 |
| JP2008509039A (en) | 2008-03-27 |
| FR2873980A1 (en) | 2006-02-10 |
| CN101018709A (en) | 2007-08-15 |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: France Blagnac Co-patentee after: Airbus GMBH (DE) Patentee after: Airbus Address before: France Blagnac Co-patentee before: Airbus GmbH Patentee before: Airbus |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110511 Termination date: 20200718 |