CN101018708A - Door for closing an opening inside an aircraft - Google Patents
Door for closing an opening inside an aircraft Download PDFInfo
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- CN101018708A CN101018708A CNA2005800260652A CN200580026065A CN101018708A CN 101018708 A CN101018708 A CN 101018708A CN A2005800260652 A CNA2005800260652 A CN A2005800260652A CN 200580026065 A CN200580026065 A CN 200580026065A CN 101018708 A CN101018708 A CN 101018708A
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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; ARRANGEMENT 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
- B64D45/0028—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems means for restricting access to flight deck doors or door arrangements specially adapted to restrict unauthorized access
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Power-Operated Mechanisms For Wings (AREA)
- Special Wing (AREA)
Abstract
本发明涉及门，所述门具有使空气沿一方向穿过所述门但防止在相反方向的这种通过的装置。如附图所示，所述门具有至少一使空气通过的窗口(74)、以及一覆盖所述窗口(74)的弹性膜片(76)。所述弹性膜片(76)一方面具有一气密区域——其面对窗口(74)且能完全覆盖所述窗口(74)，另一方面具有一可透空气的区域——其布置在所述密封区域的附近。
The present invention relates to doors having means for allowing air to pass through the door in one direction but preventing such passage in the opposite direction. As shown in the drawings, the door has at least one window (74) through which air passes, and an elastic membrane (76) covering the window (74). Said elastic membrane (76) has on the one hand an airtight area - which faces the window (74) and can completely cover said window (74), and on the other hand has an air-permeable area - which is arranged in the in the vicinity of the sealing area described above.
Description
Technical field
[01] the present invention relates to be used to close the door of aircraft interior one opening.
Background technology
[02] in aerocraft, can find to be furnished with in the main cabin different doors.At first, the door that separates main cabin and driving compartment is arranged.This is a kind of some special door.In fact, after the attack of terrorism that takes place September 11 calendar year 2001, on all aircrafts, this door is strengthened, so that especially shellproof and the discrepancy that prevents all unauthorized personnels.
[03] also be useful on the different places of coming in and going out--as the door in lavatory, kitchen etc.Generally ventilating in these places, and makes them be in the superpressure state for avoiding, and is suitable for setting the parts that air is discharged from described place.
[04] the invention still further relates to a kind of door, when the application's book was submitted to, this Men Shangwei used on service aircraft.In some aircraft, especially long-range aircraft, long-haul aircraft, cockpit door is positioned at the end in a passageway, and a space of using for bus attendant is basically led in described passageway, and the lavatory generally is arranged in this space.Some airline company allows the passenger to use described lavatory.In some aircraft, can be designed to close this passageway by one second that is positioned at main cabin one side.Therefore, this door can form a private space that gives over to the bus attendant special use in the driving compartment back.This sect has been arranged, just forbidden that the passenger comes in and goes out and be positioned at herein lavatory.This door also forms a visual barrier, prevents that the passenger from seeing cockpit door.Can improve the safety at driving compartment place like this.In fact, even this cockpit door is isolated, when the crew passed in and out driving compartment, this was still opened, thereby utilized the freedom of invader's turnover of this unlatching.
[05] aviation manufacturer's standard regulation, when decompression occurring in driving compartment or the main cabin, cockpit door must self-opening.Like this, pressure can be in the mutual balance in cockpit door both sides, thereby avoids aircaft configuration to suffer very strong stress.
[06] type gate--it can form a private space in the driving compartment back--should not disturbed the operation of cockpit door.When decompression occurring in the driving compartment, a large amount of air pass the private space and are attracted to driving compartment.Powerful in view of this air-flow, type gate must be opened immediately.On the contrary, if occur decompression in the main cabin,, be guided through the air-flow more limited (with respect to the situation that occurs decompression in the driving compartment) of type gate in view of the volume ratio between driving compartment (comprising the private space) and the main cabin.
[07] the present invention relates to such parts: when decompression occurring suddenly in the main cabin, described parts can allow air to lead to the main cabin from the passageway between cockpit door and type gate.
Summary of the invention
[08] innovation thinking of the present invention is to set a door that air-flow is passed through along certain direction, set simultaneously one in opposite direction ratio than the leak free door, so that especially form a barrier sound insulation, antisoiling and/or Smoke prevention.Therefore, the present invention is intended to propose such parts: at the type gate place, when occurring decompression in the main cabin, described parts do not disturb the work of cockpit door, and form in the opposite direction a barrier.
[09] for this reason, the present invention proposes to be used to close the door of aircraft interior one opening, it is characterized in that it has a device, and this device can make air pass described door along a direction, but prevents this passing through in the opposite direction.
[10] for this reason, can realize ventilating in aerocraft in a place, and need not to set the certain openings as wind circulation.The described device size that forms a boiler check valve is suitable for passing the air-flow of door.Also can adjust the quantity that makes the device that air passes through.
[11] the multiple device that air is passed through along single direction as well known to those skilled in the art.Therefore, for example can set a valve, it is installed pivotally around an axle that is level basically, and can cover a window that is implemented on the door.By gravity, valve are tending towards closing and stopping up window.On the contrary, when when superpressure appears in the window opposite with valve one side, described valve is tending towards opening, and air is passed through.Sealing element can center on window to be arranged, or is arranged in the periphery of valve, so that seal described window well.Also can consider, described door has the elastic memberance that at least one window and that air is passed through covers described window, described elastic memberance has an airtight zone on the one hand--it is in the face of described window and can cover described window fully, but and have the zone of an air permeable on the other hand--its be arranged in sealing area near.In this case, but the zone of the air permeable of diaphragm for example has the hole, and open in described diaphragm in described hole, so that air passes through.
[12] still, one preferred implementation of described door is designed to: described door has an at least one window and elastic memberance that air is passed through, and described elastic memberance can cover between the primary importance of whole window and the second place of most of elastic memberance away from described window at it and deforms.The use of diaphragm is favourable, because the inertia of diaphragm is little, and diaphragm itself can be guaranteed the hermetically enclosed of window.
[13] in this preferred implementation, advantageously, a lid is arranged in diaphragm one side apart with window certain distance, to limit described diaphragm deformation.This lid for example has the peripheral skirt of a perforation, and described skirt section has towards described skirt section outside a flange of extension at its free end, and, advantageously, the week of diaphragm along edge clamping between the periphery of the flange in described skirt section and window.Thereby guarantee the well secured of diaphragm, and when window is in the closed position, guarantee the excellent sealing at described window place.
[14] preferably, diaphragm has at least one free edge.
[15] employed diaphragm is for example made with polyurethane.
[16] in order to be collected in the electric charge of the air that passes through on the diaphragm, described diaphragm is preferably in has a metallic mesh on one of its surface, copper net grid for example, and this metallic mesh is connected to an electrical ground (masse é lectrique).This metallic mesh also has another function of strengthening membrane chip architecture.
[17] door of the present invention for example has a front surface and a rear surface that separates each other, and, describedly make air pass described door but prevent that this device that passes through in the opposite direction can be arranged in the clearance envelope that leaves between two surfaces of described door along a direction.Therefore, a surface of described door has the hole alternatively.
[18] same, in order to filter air, and therefore for example avoid dust and/or smog to pass through by described door, a filter advantageously makes air pass described door along a direction but prevents that this device that passes through in the opposite direction is associated with described.
[19] the invention still further relates to aerocraft, it is characterized in that, described aerocraft has for example above-mentioned one.
Description of drawings
[20] 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:
[21] Fig. 1 is the local section birds-eye view of aerocraft front portion;
[22] Fig. 2 is the front elevation according to door of the present invention;
[23] Fig. 3 is the horizontal sectional drawing by magnification ratio along Fig. 2 section line III-III;
[24] Fig. 4 is the detail drawing of releasing mechanism, and described releasing mechanism is in locked position on Fig. 3;
[25] Fig. 5 illustrates the mechanism of Fig. 4, and this mechanism is in the unlocked position;
[26] Fig. 6 to Fig. 8 is such view: when decompression occurring in the aerocraft driving compartment, they are corresponding with Fig. 3;
[27] Fig. 9 is the front elevation of the structure of supporting door shown in Figure 2;
[28] Figure 10 is the section-drawing along Figure 11 section line X-X;
[29] 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;
[30] 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
[31] Figure 14 illustrates assembly parts of two plates shown in Figure 12 and 13 in the mode of front elevation.
The specific embodiment
[32] 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.
[33] door 10 of driving compartment one of in the end in described passageway this passageway 8 of sealing.Innovation be to propose in the passageway the other end of 8 and arrange one second 12.
Have two radical functions for [34] 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.
[35] 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.
[36] especially when occurring decompression in the driving compartment 2, second 12 work that should not disturb cockpit door 10.
[37] 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.
[38] framework 16 has two side direction columns 20 and a gin pole 21, and they are by three torsion casees (caissons de torsion) 22--one top box, a raising middle flask and a nowel--be connected.Like this, on the one hand between top box and raising middle flask, and on the other hand between raising middle flask and nowel, described framework has two openings.Described each opening is all further separated with a crosspiece 24, thereby forms eight lattices altogether in framework, and each lattice is all admitted a plate 18.Eight lattices are scattered in two row, four of every row.Each lattice is admitted a plate 18, and it is illustrated in greater detail in Fig. 3 and 4.
[39] 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 ".
[40] each plate 18 has two plates: a front panel plate 26 and a back plate 28.
[41] the reclining inside face of one first flange 30 that links to each other with a side direction column 20 and the outside face of one second flange 32 of the gin pole 21 that reclining of front panel 26.First and second flanges 30 for example extend on the whole height of the lattice of admitting plate 18.The upper limb of front panel 26 and lower edge be free edge preferably.
[42] front panel 26 remains on second flange 32 by means of pivot claw (loquet) 34.Each claw 34 is installed on one 36.One spring (not shown) prestress is bearing on the outside face of front panel 26 described claw 34 in claw 34, thereby this front panel is kept resting on second flange 32.Same axle 36 can be used for keeping acting on the claw 34 on two front panel 26 of plate of two adjacent lattices.
[43] 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.
[44] 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.
[45] 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.
[46] 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.
[47] 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.
[48] 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.
[49] 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.
[50] 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 from aforesaid explanation and corresponding Fig. 3 to Fig. 8 that [51] 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.
[52] 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.Be and unclamp plate 18 cooresponding pressure relief value if P unclamps (), so, P unclamp multiply by second 12 the gross area 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 according to selected P unclamp value, the quantity of the pivot claw 34 of the area of plate 18 and every plate is regulated accordingly.
[53] in a single day above stated specification shows, 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.
[54] 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.
[55] 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.
[56] 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.
[57] 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.
[58] arm 57 forms the top of second 12 axle 56.It is installed in the bearing 60 pivotally, and described bearing 60 is fixed on the upper beam 52 by an angle bar shape member 62.
[59] 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.
[60] 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.
[61] 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.
[62] 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.
[63] front panel 26 itself is furnished with low pressure check valves.For example, each plate 18 can set two valves, shown in Figure 12 and 13.At each valve place, a cutting mouth 74 is arranged on the front panel 26.Each cutting mouth 74 is covered fully by an air tight elastic memberance 76.Lid 78 with a peripheral skirt 79 and a flange 80 can cover elastic memberance 76.This lid 78 is fixed on the inside face of front panel 26 at its flange 80 places.The outline body of elastic memberance 76 is clipped between this flange 80 and the interior plate 26 partly.If elastic memberance 76 and lid 78 for example are rectangles, for example can consider: the relative two edges of described elastic memberance 76 are kept by the flange 80 of described lid 78, and other two edges of described elastic memberance 78 are freely.Lid 78 parallels ground with interior plate 26, with it at a distance of the extension of certain distance ground.Opening is provided in this and covers, and for example is positioned at peripheral skirt 79 places, so that allow air to pass through.
[64] 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.
[65] 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.
[66] 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.
[67] elastic memberance 76 is for example made with polyurethane.To come from these electric charges of static in order when electric charge enters boiler check valve, collecting, can on each elastic memberance 76, to set a silk screen (de s é rigraphier un r é seau), for example copper wire gauze in window 74 1 sides.Therefore, this net for example is electrically connected with attaching parts 48, and described attaching parts 48 itself is electrically connected by back plate 28 and attaching parts 50 metal framework 16 with second 12.
[68] 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.
[69] 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.
[70] 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 second 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.
[71] above-mentioned second 12 can form one and be used for crew's the private space in its preferred implementation, and prevents 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 [72] 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.
[73] 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.
[74] obvious, 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.
[75] 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.).
[76] as seen, above-mentioned door can adapt to many standards by afore-mentioned:
[77]-under the situation of driving compartment place for decompression, it can carry out equilibrium of pressure,
[78]-under the situation of place, main cabin for decompression, it also can make pressure balanced mutually,
[79]-and this door is designed under the very large situation of mechanical strees, still keeps being connected as a single entity,
[80]-this weight is less relatively,
[81]-this can be furnished with traditional closing appliance,
[82]-can set supervisory system (peep hole, pick up camera etc.),
[83] but-also SELF CL of this,
[84] but-also auto lock of this,
[85]-this private space that bus attendant acquisition is separated with the remainder in main cabin,
[86]-and can implement one from angle attractive in appearance, this remainder with the main cabin combines together.
[87] 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 (11)
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0408584 | 2004-08-03 | ||
| FR0408584A FR2873981B1 (en) | 2004-08-03 | 2004-08-03 | DOOR FOR CLOSING AN OPENING WITHIN AN AIRCRAFT |
| US60652604P | 2004-09-02 | 2004-09-02 | |
| US60/606,526 | 2004-09-02 | ||
| PCT/FR2005/001821 WO2006024726A1 (en) | 2004-08-03 | 2005-07-18 | Door for closing an opening inside an aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101018708A true CN101018708A (en) | 2007-08-15 |
| CN100595107C CN100595107C (en) | 2010-03-24 |
Family
ID=34947996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200580026065A Expired - Lifetime CN100595107C (en) | 2004-08-03 | 2005-07-18 | A door used to close an opening in an aircraft interior |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN100595107C (en) |
| FR (1) | FR2873981B1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101918272A (en) * | 2008-01-21 | 2010-12-15 | 空中客车运作股份公司 | Pressurised aircraft carrier with open air exposure flap |
| CN102501966A (en) * | 2011-11-07 | 2012-06-20 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
| CN103237729A (en) * | 2011-01-26 | 2013-08-07 | 空中客车德国运营有限责任公司 | Door assembly with two door leaves |
| CN103619706A (en) * | 2011-08-17 | 2014-03-05 | B/E航空公司 | Aircraft interior door assembly |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85100918A (en) * | 1985-04-01 | 1985-12-20 | 易明 | Passenger plane with " Convention for the Suppression of Unlawful Seizure of Aircraft " function |
| FR2691789B1 (en) * | 1992-05-27 | 1999-04-23 | Michel Zaniewski | IMPROVEMENTS TO DEVICES PROVIDING THE AUTOMATIC DISTRIBUTION AND REGULATION OF AIR FLOWS, PARTICULARLY FOR VENTILATION OF PREMISES. |
| US20030192989A1 (en) * | 2002-04-10 | 2003-10-16 | Frank Owen | Security bulkhead and door construction |
| US6902137B2 (en) * | 2002-09-09 | 2005-06-07 | Adams Rite Aerospace, Inc. | Aircraft door latch/lock mechanism with pneumatic decompression override |
| 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 FR0408584A patent/FR2873981B1/en not_active Expired - Fee Related
-
2005
- 2005-07-18 CN CN200580026065A patent/CN100595107C/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101918272A (en) * | 2008-01-21 | 2010-12-15 | 空中客车运作股份公司 | Pressurised aircraft carrier with open air exposure flap |
| CN103237729A (en) * | 2011-01-26 | 2013-08-07 | 空中客车德国运营有限责任公司 | Door assembly with two door leaves |
| US9045214B2 (en) | 2011-01-26 | 2015-06-02 | Airbus Operations Gmbh | Door assembly with two door leaves |
| CN103619706A (en) * | 2011-08-17 | 2014-03-05 | B/E航空公司 | Aircraft interior door assembly |
| CN102501966A (en) * | 2011-11-07 | 2012-06-20 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
| CN102501966B (en) * | 2011-11-07 | 2016-04-13 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2873981B1 (en) | 2006-10-27 |
| FR2873981A1 (en) | 2006-02-10 |
| CN100595107C (en) | 2010-03-24 |
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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 |