EP3286084A1 - Vorrichtung zum ausgleichen einer druckdifferenz für ein luftfahrzeug - Google Patents
Vorrichtung zum ausgleichen einer druckdifferenz für ein luftfahrzeugInfo
- Publication number
- EP3286084A1 EP3286084A1 EP16713912.0A EP16713912A EP3286084A1 EP 3286084 A1 EP3286084 A1 EP 3286084A1 EP 16713912 A EP16713912 A EP 16713912A EP 3286084 A1 EP3286084 A1 EP 3286084A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flap
- test
- decompression
- receiving element
- test chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 230000006837 decompression Effects 0.000 claims abstract description 85
- 238000012360 testing method Methods 0.000 claims abstract description 77
- 238000005192 partition Methods 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 9
- 241000446313 Lamella Species 0.000 claims description 27
- 238000005096 rolling process Methods 0.000 claims description 6
- 239000012528 membrane Substances 0.000 claims description 4
- 239000004033 plastic Substances 0.000 claims description 3
- 238000010276 construction Methods 0.000 description 5
- 230000006378 damage Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 241001417534 Lutjanidae Species 0.000 description 1
- 206010047571 Visual impairment Diseases 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 208000029257 vision disease Diseases 0.000 description 1
- 230000004393 visual impairment Effects 0.000 description 1
Classifications
-
- 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
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/0023—Movable or removable cabin dividers, e.g. for class separation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
Definitions
- the present invention relates to an apparatus for equalizing a pressure difference for an aircraft with the features of the preamble of claim 1, a method for determining release forces of a decompression flap and a device for testing a decompression flap.
- a first compartment In the event of damage to the tailboard of the passenger aircraft in the area of such a passenger compartment, the sudden decompression of the pressure cabin, hereinafter referred to as a first compartment, results in a sudden pressure drop in the first compartment.
- a second space which adjoins the first space and is separated from the first space by at least one partition wall, can perform this pressure drop only with a time delay, so that there is a pressure difference between the first and the second space at least for a short period of time the partition abuts.
- the partition can be formed for example by a partition or an outer wall of a piece of furniture.
- the attachment of the decompression flap to the dividing wall is designed such that the flow opening is released when the predetermined, critical pressure difference between the first and the second space is exceeded.
- the decompression flap which opens out of the flow opening, to not cause injuries to the passengers as a result of the sudden release movement in the event of decompression
- the decompression flap is connected by a securing device to an aircraft-fixed structure, for example to the dividing wall itself.
- the safety device prevents uncontrolled movement in the case of accidental release of the decompression flap, for example due to high accelerations during turbulence or during an emergency landing.
- the decompression flap In order to allow the opening of the decompression flap, the decompression flap is held by a securing element which releases the decompression flap when a critical pressure difference is exceeded.
- the object of the invention is to be able to better predict the opening behavior of the decompression valve as a function of a defined pressure difference and thus to reduce the effort in the testing.
- the invention solves this problem with a device and a method according to the independent claims.
- an apparatus for compensating a pressure difference for an aircraft which comprises a planar, aircraft-fixed partition wall, which fluidly separates a first space from a second space.
- the dividing wall has a flow opening connecting the first and second spaces, wherein the flow opening is closed by a decompression flap.
- a securing element on the decompression flap is set up to release a release movement of the decompression flap when a predetermined pressure gradient between the first and second spaces is exceeded, so that a fluidic connection exists between the first and the second space, wherein the partition wall and / or or on the decompression flap, a receiving element is provided, with which the securing element is in operative connection, and wherein on the receiving element and / or the securing element, an adjusting element is provided, via which the distance between the securing element and the receiving element is adjustable.
- the adjustment can be ensured that the fuse element in the initial state, ie, when the decompression flap is closed, flush with the receiving element.
- This allows a stable and reproducible release force can be set, which can be determined experimentally.
- the results of the determination of the release force of the decompres- sion flap can then be transferred to further fixtures so that the testing effort for future fixtures and conversions is reduced.
- three adjustment positions are preferably provided. In a preferred setting position, the securing element comes just with the receiving element to the plant. In a further preferred adjustment position, a predefined gap results between the securing element and the receiving element. In a further preferred setting position, the securing element is pressed against the receiving element with a predefined force.
- an active surface of the securing element bears force-free against a corresponding active surface of the receiving element.
- the securing element is designed as a lamella, wherein the lamella preferably bears force-free against the receiving element.
- a lamella can hold the decompression flap in normal operation in the closed starting position, whereby a lamella can be inserted into the decompression flap to save space. When the predetermined pressure gradient is exceeded, the lamella yields and thus makes it possible to open the decompression flap.
- lamellae are known and inexpensive to produce construction elements, so that the fuse element can be produced inexpensively. Plastic lamellae and in particular rubber lamellae are particularly preferred since these lamellae are light in weight, can be produced easily and give way at a defined pressure gradient and an associated force.
- the securing element has a reproducible deformation behavior, so that the securing element does not have significantly changed elasticity even after multiple deformation, for example during installation of the decompression flap.
- a power-free concern stable reproducible conditions can be created.
- the receiving element has a groove, wherein the width of the groove largely corresponds to the width of the lamella.
- the lamella can be guided in the groove, wherein an end face of the lamella facing the groove bottom of the lamella comes into contact with the groove base.
- an exact positioning of the lamella to the receiving element is achieved, whereby a reliably reproducible force for opening the decompression flap can be determined or set.
- the securing element is designed as a rolling element and the receiving element as a rolling element snapper.
- WälzSystemschnapper for example KugelSchnapper or Rollenschnapper are known from the furniture construction elements, for example, to secure the closure of doors.
- the rolling element so the ball or roller, spring-loaded, so that it is pressed by a spring with a defined force against a corresponding recess in WälzSystemschnapper. This spring force can be adjusted by the adjustment, so that reliably repeatable and defined release forces for the decompression flap arise.
- a classification is also possible by, for example, different stiff springs are used, so that the release force for WälzShnapper can be adjusted for the same rolling element and the same Wälzlagerschnapper by the selection of a spring from the appropriate class.
- the adjusting element has a holding element for the securing element.
- the fuse element can be securely fixed in a defined position, which reduces the assembly effort and facilitates setting.
- a frame-shaped holding element for receiving the lamella is particularly preferred, so that the lamella is securely fixed is and deformation of the blade takes place only in a designated, defined area.
- a preferred embodiment is characterized in that the holding element can be changed by at least one screw in its position.
- a screw is a simple and inexpensive construction element to allow for adjustment and thus to ensure that the securing element abuts against the receiving element.
- the retaining element is held by two screws in its position, whereby tilting of the retaining element is avoided.
- the retaining element is embedded in a recess of the decompression flap.
- the holding element is not in the optically visible range, so that no visual impairment for the passengers.
- the retaining element is enclosed by the decompression flap, so that the decompression flap supports the retaining element and thus the risk of breakage of the retaining element is reduced.
- a device for testing a decompression flap, in particular for carrying out the method described in the previous section, comprising a test chamber and an antechamber separate from this test chamber, wherein the test chamber and the prechamber are separated by a membrane in which prechamber means are provided for lowering the air pressure in the prechamber to a test level, the test chamber has an opening and a decompression door closing the opening, a securing element on the decompression door being adapted to release the decompression door when a predetermined pressure gradient is exceeded released between the test chamber and the prechamber. If the antechamber and the test chamber are suddenly connected fluidically, the pressure in the test chamber drops. If the pressure drops far enough, the decompression flap opens and connects the test chamber with the environment.
- a fluidic connection between the test chamber and the environment is opened, wherein a receiving element is provided on the test chamber and / or on the decompression valve, with which the safety element is operatively connected.
- a receiving element is provided on the test chamber and / or on the decompression valve, with which the safety element is operatively connected.
- an adjusting element is provided, via which the distance between the securing element and the receiving element is adjustable such that an active surface of the securing element bears against a corresponding active surface of the receiving element.
- Means for detecting the triggering time of the decompression valve are present on the test chamber, wherein the means for detecting the triggering time comprise, in particular, a high-speed camera or a light barrier.
- the opening time of the decompression flap can be determined by the device for testing, and the forces acting on the decompression flap at this opening time can be determined from the pressure measurement, so that a triggering pressure or a triggering force can be assigned to each securing element.
- Fig. 1 is a schematic representation of an inventive
- Fig. 2 is a schematic representation of a device according to the invention
- FIG. 3 shows an exemplary embodiment of a device according to the invention for compensating a pressure difference for an aircraft with a securing element, a receiving element and an adjusting element;
- 4 shows an exemplary embodiment of a securing element in the form of a lamella and a receiving element which is in operative connection with the securing element;
- Adjustment of different triggering forces of decompression can be selected.
- FIG. 6 shows a device for testing a decompression flap.
- Fig. 1 shows schematically and by way of example a structure of a passenger plane with a VIP expansion.
- a first space 2 is provided, which is formed for example by a passenger compartment.
- the second space 3 is preferably formed in this embodiment by a storage space, more preferably by the conversion of a piece of furniture.
- a side wall 21 is shown, which separates the first space 2 from an environment.
- the volume of the first room 2 is larger than the volume of the second room 3;
- the disclosure content of this application expressly also includes other ratios of the room volumes.
- FIG. 2 the structure of a passenger aircraft with VIP expansion is analogous to FIG. 1 shortly after a sudden pressure drop, for example through a hole 22 in the hull 21, shown.
- the pressure drop of the pressure pi is caused by a damage 22 in the hull 21, so that within a very short time the pressure pi in the first space 2 equalizes the ambient pressure p.
- the second space 3 fluidically largely separated from the first space 2, so that the pressure p2 at least for a short period of time after the pressure drop in the first space 2 can be assumed to be constant; the pressure p2 is thus greater than the pressure pi.
- the decompression flap 5 and the connection of the decompression flap 5 with the partition wall 1 are shown in detail in FIG.
- the decompression flap 5 has a recess 18 into which a support element 17 is embedded.
- an adjustment 8 is used, wherein the adjusting member 8 has a holding member 20 and screws 19 for adjusting the distance between the holding member 20 and the support member 17.
- a securing element 6 is held by the holding element 20 which is frame-shaped.
- the securing element 6 is designed as a lamella 11, preferably as a plastic lamella 12, in particular as a rubber lamella.
- a receiving element 7 is fixed, which comprises a support frame 16 and a holding element 15 and is glued, for example, in the partition wall 1.
- the receiving element 7 may also be fastened with screws 24 on the partition wall 1.
- the support frame 16 in this case has a groove 13 into which the lamella 11 of the securing element 6 engages.
- the distance between the blade 11 and the receiving element 7 is set so that a surface 9 comes to rest on a front side of the blade 11 with a corresponding surface 10 on a groove bottom of the groove 13.
- a rolling element in particular a spring-loaded ball or a spring-loaded roller, can also be used as the securing element 6 are, wherein the receiving element 7 is preferably formed as a ball catch or a Rollenschnapper.
- Fig. 4 the contact area between the securing element 6 and the receiving element 7 is shown enlarged.
- the blade 11 is fixedly connected to the decompression flap 5, wherein, as described in Fig. 3, a not shown for reasons of clarity in this figure Einstellele element between the blade 11 and the decompression valve 5 is arranged.
- the blade 11 is located with the surface 9 virtue as force on the groove bottom of the groove 13, so that a positive connection between the blade 11 and the receiving element 7 is present.
- a predefined gap between the surface 9 and the groove bottom of the groove 13 can be adjusted, so that a reproducible release behavior is made possible.
- and an associated release force from the lamella 11 dissolves from the receiving element 7 and thus releases a caused by the pressure difference opening the decompression flap 5 free.
- Fig. 5a to 5d Darge presents, several classes IIa, IIb, 11c, lld provided by lamellae 11, which at the same body by different sized recesses 25 on the Slat 11 and associated different sized contact surfaces between the blade 11 and the receiving element 7 differ.
- the base body for example, has a length between 50 mm and 150 mm.
- the lamella IIa has no recess, while the lamella IIb has a reduced by the recesses by about 25 Aufnähme Chemistry.
- the receiving surface of the La melle 11c is reduced by about 50% and the receiving surface of the Slat lld is reduced by approx. 75%.
- the slats can be standardized, so that in a redesign of an installation in an aircraft depending on the required triggering forces the appropriate slats 11 can be selected for a decompression flap 4.
- FIG. 6 shows a device 40 for testing a decompression flap 5.
- the device 40 comprises an antechamber 41 and a test chamber 42, which are separated from each other by an airtight membrane 43.
- means 44 for generating a test vacuum are arranged in order to condition the prechamber 41 at the pressure p, at cruising altitude.
- the pre-chamber 41 is connected to a sufficiently large storage volume, so that the pressure p remains largely constant during testing.
- Means 46 for detecting an opening of the test flap 47 are arranged on the test chamber 42 with which the time of opening of the test flap 47 can be determined exactly.
- an electrical tronic contact, a stop or a light barrier in the pivoting range of the test flap 47 to detect the opening are arranged on the test chamber 42 with which the time of opening of the test flap 47 can be determined exactly.
- the membrane 43 is destroyed abruptly. As a result, the pressure in the test chamber 42 drops very quickly.
- the point in time is determined at which the lamella 11 can no longer withstand the pressure force and the test flap 47 opens.
- the pressure prevailing in the test chamber 42 at this time can be determined from the pressure measurement via the pressure sensors 48.
- the pressure load acting on the test flap 47 can be calculated.
- the release force of the test flap 47 can then be determined and the result of the respective lamella IIa, IIb, 11c, lld be assigned.
- one or more suitable lamellae 11 can then be selected for new constructions and the results transmitted from the test flap 47 to a decompression flap 5.
- the decompression flap 5 can either be held on one side by means of hinges, or held as a translational decompression flap 5 by a plurality of fins 11, so that the decompression flap 5 disengages from the dividing wall 1 after exceeding the triggering force and is held by the securing strip 23.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Air-Flow Control Members (AREA)
- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102015207599.0A DE102015207599B4 (de) | 2015-04-24 | 2015-04-24 | Vorrichtung zum Ausgleichen einer Druckdifferenz für ein Luftfahrzeug |
PCT/EP2016/057308 WO2016169750A1 (de) | 2015-04-24 | 2016-04-04 | Vorrichtung zum ausgleichen einer druckdifferenz für ein luftfahrzeug |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3286084A1 true EP3286084A1 (de) | 2018-02-28 |
Family
ID=55650427
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16713912.0A Withdrawn EP3286084A1 (de) | 2015-04-24 | 2016-04-04 | Vorrichtung zum ausgleichen einer druckdifferenz für ein luftfahrzeug |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP3286084A1 (de) |
DE (1) | DE102015207599B4 (de) |
WO (1) | WO2016169750A1 (de) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102017208115A1 (de) * | 2017-05-15 | 2018-11-15 | Lufthansa Technik Ag | Vorrichtung zum Ausgleichen einer Druckdifferenz für ein Luftfahrzeug |
CN112504642A (zh) * | 2020-11-09 | 2021-03-16 | 芜湖天航装备技术有限公司 | 一种用于调节装置试验台及其制作和性能试验方法 |
CN112728193B (zh) * | 2020-12-25 | 2022-07-05 | 兰州飞行控制有限责任公司 | 一种活门阀关紧作动器 |
CN114577504B (zh) * | 2022-05-07 | 2022-07-12 | 中国飞机强度研究所 | 一种飞机测试的防冻压力调节系统及其调节方法 |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2548623B1 (fr) * | 1983-07-08 | 1985-10-11 | Aerospatiale | Dispositif de securite pour l'ouverture d'une porte d'aeronef ouvrant vers l'exterieur en cas de surpression a l'interieur de cet aeronef et porte ainsi equipee |
DE4103013A1 (de) * | 1991-02-01 | 1992-08-06 | Airbus Gmbh | Haltevorrichtung fuer ein dekompressionspaneel |
DE4216277C2 (de) * | 1992-05-16 | 1994-12-01 | Deutsche Aerospace Airbus | Dekompressionspaneel für Zwischenwände und -böden von Passagier- und Frachträumen in Flugzeugen |
DE10031714C2 (de) * | 2000-06-29 | 2002-10-10 | Aircabin Gmbh | Dekompressionseinheit für den explosiven Luftdruckausgleich |
DE102004009017B3 (de) * | 2004-02-25 | 2005-08-04 | Aircabin Gmbh | Dekompressionsvorrichtung für einen abrupten Druckausgleich zwischen zwei getrennten Bereichen, insbesondere zwischen zwei druckbeaufschlagten Bereichen eines Flugzeugs |
DE102007061433B4 (de) * | 2007-12-20 | 2012-10-25 | Airbus Operations Gmbh | Verbesserte Dekompressionseinrichtung mit einem einstellbaren Auslösedruck |
DE102009006395B4 (de) * | 2009-01-28 | 2014-07-10 | Airbus Operations Gmbh | Dekompressionsvorichtung für ein Flugzeug |
FR2960854B1 (fr) * | 2010-06-04 | 2012-07-20 | Airbus Operations Sas | Porte a double fonction pour nacelle de moteur d'aeronef |
AT510153B1 (de) * | 2010-10-19 | 2012-02-15 | Facc Ag | Dekompressionseinheit |
CN103241395A (zh) * | 2013-05-31 | 2013-08-14 | 烟台宏远氧业有限公司 | 模拟航空迅速减压舱 |
-
2015
- 2015-04-24 DE DE102015207599.0A patent/DE102015207599B4/de not_active Expired - Fee Related
-
2016
- 2016-04-04 WO PCT/EP2016/057308 patent/WO2016169750A1/de active Application Filing
- 2016-04-04 EP EP16713912.0A patent/EP3286084A1/de not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
DE102015207599B4 (de) | 2016-12-01 |
WO2016169750A1 (de) | 2016-10-27 |
DE102015207599A1 (de) | 2016-10-27 |
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Inventor name: CARSTENSEN, SVEN Inventor name: PFINGSTEN, KAI-CHRISTOPH Inventor name: REIFFERSCHEID, MORITZ Inventor name: KNAPPKE, NILS |
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Inventor name: PFINGSTEN, KAI-CHRISTOPH Inventor name: CARSTENSEN, SVEN Inventor name: REIFFERSCHEID, MORITZ Inventor name: KNAPPKE, NILS |
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