WO2011004119A1 - Dispositif d'obturation d'un circuit vide-vite d'aéronef - Google Patents
Dispositif d'obturation d'un circuit vide-vite d'aéronef Download PDFInfo
- Publication number
- WO2011004119A1 WO2011004119A1 PCT/FR2010/051429 FR2010051429W WO2011004119A1 WO 2011004119 A1 WO2011004119 A1 WO 2011004119A1 FR 2010051429 W FR2010051429 W FR 2010051429W WO 2011004119 A1 WO2011004119 A1 WO 2011004119A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- seal
- circuit
- frame
- modifying
- aircraft
- Prior art date
Links
- 230000008878 coupling Effects 0.000 claims abstract description 7
- 238000010168 coupling process Methods 0.000 claims abstract description 7
- 238000005859 coupling reaction Methods 0.000 claims abstract description 7
- 238000004891 communication Methods 0.000 claims description 8
- 238000012986 modification Methods 0.000 claims description 4
- 230000004048 modification Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 2
- 238000007789 sealing Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 5
- 229920002943 EPDM rubber Polymers 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 238000010926 purge Methods 0.000 description 2
- 241001573881 Corolla Species 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000013519 translation Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/022—Test plugs for closing off the end of a pipe
-
- 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/20—Emptying systems
- B64D37/26—Jettisoning of fuel
Definitions
- the invention relates to closure devices of aircraft vacuum circuits.
- Some aircraft are equipped with a system that, when circumstances require, quickly release the fuel contained in the tanks. Such a system is called a quick-empty system. This release is referred to in English as “Fuel Dumping” and “Fuel Jettisioning”.
- Tests would therefore be to pressurize the circuit with the tank by means of an air-helium mixture, for example at a nominal pressure of 350 hectopascals.
- Such a device should be able to be used at the parts assembly stations on the aircraft and so-called site stations that deal with aircraft whose tanks and different fuel systems have already received kerosene. It is for this reason that such tools must meet the regulatory requirements, particularly the standards for non-electrical tools used in explosive zones. Thus, the device must allow to shut off the vacuum circuit while ensuring a proper seal with the latter to avoid any risk of accidental spillage of fuel.
- this outlet forms a sleeve in the mouth of which the device must be introduced to form a seal from the inside between this sleeve and the device.
- this sleeve has fastening rivets which protrude inside the sleeve so that they define a passage whose size is smaller than the dimension of the zone with which the device must seal and which is beyond. It is therefore to have a device that can cross these rivets without damaging them and achieve a satisfactory seal in the next area.
- An object of the invention is to provide a fast-empty circuit test device which makes it possible to achieve a seal in such a configuration of the output of the circuit.
- a shutter device of an aircraft evacuation circuit the device comprising a coupling end, the endpiece carrying a seal and means for modifying a device. dimension of the joint.
- the tip can be given a retracted configuration and an expanded configuration in which the size of the seal is larger than in the retracted configuration. It is thus possible to pass the tip in retracted configuration in the narrow zone the output of the circuit, then to give it the extended configuration so that it achieves a seal with the output of the circuit beyond this zone.
- the modification means are able to modify a dimension of a section, such as an edge, of the joint without modifying a dimension of another section, such as an edge, of the joint.
- the device simplifies the implementation of the device in that it is generally easier to deform a single section of the seal that the seal in its entirety.
- this arrangement allows to crush the seal on a portion of its length, it is not crushed over its entire length, in general.
- the seal in the closed position, generally has a non-constant outer diameter along the length of the seal and a non-cylindrical shape.
- the device is therefore more easily adaptable to conduits of diameters very different from each other.
- this adaptability makes it possible initially to give the tip a total diameter much smaller than that of the duct in which it is intended to penetrate, in particular so as not to damage certain areas of the duct, for example rivets or other elements. protruding in the duct in the radial direction.
- the modifying means occupy a main conduit of the seal.
- the modification means are mounted movably relative to the seal.
- the modification means have a ramp face for the seal.
- the face has a curved profile with a center of curvature located outside the joint.
- the modifying means are adjustable.
- the device comprises a member, such as a capstan, for controlling the modifying means.
- the device is able to put the duct and the nozzle into communication with gas through the gasket.
- the device comprises in particular a flexible pneumatic conduit and a rotating connector capable of performing this communication.
- the device comprises a frame and means independent of the end piece for fixing the frame to the circuit.
- the function of fixing the closure device to the vacuum circuit is not exerted, at least principally, by the tip, but by the fastening means. We can therefore dedicate the tip to the achievement of the sealing function.
- FIG. 1 is a perspective view of the device of the invention according to one embodiment
- FIG. 2 is a perspective view of the pneumatic circuit associated with the device of FIG. 1;
- FIG. 3 is a perspective view of the frame, the seal and the jaws of the device of Figure 1;
- Figure 4 is a view similar to Figure 1 showing the jaws open;
- FIG. 5 is a perspective view of an output of the empty-fast circuit of an airplane
- FIG. 6 is a perspective view of the device of Figure 1 in use
- FIG. 7 is a view in axial section of the device of FIG. 6 mounted on the outlet of FIG. 5;
- FIG. 8 is a perspective view of the plug of the device of FIG. 7.
- FIG. 6 illustrates a tool 2 comprising a pneumatic line 4 and a closure device 6 according to the invention.
- the pneumatic line 4 comprises the following elements arranged in series following each other and in gas communication with each other: a flexible pneumatic conduit 8, a metal valve 10, a "T" connector 12, and and finally a rotating connector 14.
- the "T" fitting carries, on its third branch, a manometer 16 provided with a protective collar 18.
- the closure device 6 is fixed to the free end of the rotary coupling.
- This device comprises a frame 20 of generally cylindrical shape of axis 22. It comprises, at its proximal axial end, a clevis 24 of annular shape, s' extending generally in a plane perpendicular to the axis 22.
- This yoke carries two arms 26 arranged at diametrically opposite positions on either side of the axis 22, here in upper and lower parts respectively in the figures.
- Each of the arms 26 is articulated to the yoke 24 about an axis 28 perpendicular to the axis 22 and non-intersecting with the latter.
- the arms 26 may thus have a closed configuration in which they are brought closer to the frame 20 and extend parallel to the axis 22, as illustrated in FIGS. 1, 3, 6 and 7, and an open configuration in which they are inclined. relative to the axis 22 and remote from the frame 20 as shown in Figure 4.
- Guides 30 or spacers, here the number of two, are interposed in the radial direction between the frame 20 and the arms 26.
- the two guides 30 are identical to each other and follow one another along the axis 22.
- the device 6 comprises a rod 32 of axis 22 connected by its axial end proximal to the rotating connector 14.
- This rod is rotatably mounted relative to the frame 20 about the axis 22. It is immobilized in translation relative to the frame 20.
- the rod 32 has, at its distal axial end, a male threaded portion on which is fixed, by means of a female threaded portion, a plug or actuator 34.
- the main part of the rod is formed by a piece 36 and the thread of the rod is carried by an end piece 38 attached to the main portion 36 being rigidly fixed thereto.
- the plug 34 is symmetrical of revolution about the axis 22. It comprises a base 40 which has the female threaded part ensuring the connection with the rod. It comprises an actuating part or cam 42 which has in particular an outer face 44 whose diameter increases from its proximal end to its distal end. This face has a convex profile in a radial plane to the axis 22, this profile having a center of curvature extending outside the actuating portion 42. In other words, the face 44 extends between the center of curvature and the axis 22. The face 44 thus has a corolla shape.
- the actuating portion 42 is fixed to the base 40 by means of screws, here three in number, extending parallel to the axis 22 and regularly distributed around the latter.
- the orifices associated with these screws pass right through the base 40.
- the cap comprises a protective flange 45 of the free end of the actuating part, also screwed in a similar manner to the latter.
- the frame 20 carries a seal 31 symmetry of revolution about the axis 22, of cylindrical shape and recessed at its center.
- the seal 31 is fixed rigidly by its axial end proximal to the distal end of the frame 20 while its distal axial end is left free.
- the seal 31 is for example made of EPDM material
- the device comprises adjustable control means for moving the actuating portion 42 relative to the seal.
- these means comprise a capstan 47 which comprises two radial arms 48 carrying respective handles 50 in the form of balls.
- the capstan is rigidly fixed to the proximal axial end of the rod 32.
- Means are provided to prevent rotation of the cap 34 relative to the frame, which comprise for example a key 46 rigidly fixed to the frame, extending in a direction radial to the axis 22, and movable in a groove 47 of the plug parallel to the axis 22. Thanks to the helical connection between the rod 32 and the plug 34, the rotation of the capstan about the axis 22 relative to to the frame causes the sliding of the plug along the axis 22 relative to the seal 31.
- the seal 31 is supported by its inner face against the outer face 44 of the cap.
- the stopper 34 occupies its position closest to the frame, that is to say the leftmost frame in FIG. 7, the greater part of the seal rests on the face 44.
- the distal end region of the seal 31 has an outside diameter d greater than in the retracted configuration, as illustrated in FIGS. 6 and 7.
- the diameter d is greater than the outer diameter of the proximal end zone of the seal because it bears on the distal end zone of the face 44.
- the rod 32 has a distal cavity 62 in communication with a through cavity 64 of the plug.
- the stem also has a proximal cavity 66 in communication with the rotating connector 14.
- the two cavities 62 and 66 of the rod are in mutual communication through radial orifices and via the center of the frame.
- the seal 31 and the plug 34 form a coupling end 43.
- FIG. 5 illustrates an exit duct of a vacuum-fast circuit of an aircraft such as an airplane.
- Such outlet ducts are located near the trailing edge of the wings for example.
- This duct has here, from left to right, a mouth zone 50, a fixing zone 52 and a bearing zone 54 following in this order.
- the attachment zone comprises rivets which extend inside the duct projecting from its internal face. In this zone, no contact is therefore allowed between the tip 43 and the conduit 48.
- the zones 50 and 54 have a cylindrical shape while the zone 52 has a flared shape.
- the inner diameter of the zone 54 is smaller than that of the zone 50.
- Tooling 2 is used as follows.
- the pneumatic line 4 is not fixed to the device 6.
- the tip 43 has its retracted configuration.
- the plug 34 is in its position furthest from the frame.
- the plug 34 is in the extended position.
- the arms 26 are in the open position.
- the tip 43 is inserted into the duct 48 by passing through the zones 50 and 52 until it reaches the zone 54. As illustrated in FIG. 7, the zone 50 then extends radially between the struts 30 and the frame. on the one hand, and the arms 26 on the other.
- the arms 26 are brought closer to the axis 22 and immobilized in the closed position.
- the arms carry at their free end respective half-collars 60 which can be fixed to each other by means of bolts comprising in particular a screw 63 and a button 61 acting as a nut and traversed by the opinion .
- each half-collar 60 has an inner surface 65 undercut resting against a corresponding flank face of the zone 50. The cooperation of these two faces prevents the withdrawal of the device by sliding along the axis 22.
- the free end of the duct 48 is in axial abutment against the yoke 24.
- the device 6 is thus rigidly fixed to the duct 48.
- the handles 50 of the capstan 46 are then maneuvered to turn the capstan 46 and thus slide the cap 34 towards the frame. This movement causes sliding of the seal 31 on the ramp face 44 and the deformation of the seal with an increase in the diameter d of its distal end edge.
- the pneumatic line 4 is then connected to the device 6 and the necessary tests can be carried out, in particular by means of the manometer 16 which makes it possible to visually check the pressure inside the vacuum-fast circuit.
- the tip can be adapted to conduits 48 of different diameters.
- the device removably and removably adapts at the outlet of the vacuum circuit to temporarily seal it and visualize the pressure therein during leak tests. It ensures easy connection to the vacuum circuit by avoiding contact with the parts carrying the rivets. It allows purging once the test is done.
- the seal 31 may have an annular shape other than circular so that the modifiable dimension will not necessarily be a diameter.
- the device of the invention can be used with other types of fast-empty circuit, in particular free of rivets.
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gasket Seals (AREA)
- Pipe Accessories (AREA)
- Pressure Vessels And Lids Thereof (AREA)
- Sealing Devices (AREA)
- Quick-Acting Or Multi-Walled Pipe Joints (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012104669/11A RU2012104669A (ru) | 2009-07-10 | 2010-07-07 | Перекрывающее устройство контура аварийного слива летательного аппарата |
EP10742213A EP2451709A1 (fr) | 2009-07-10 | 2010-07-07 | Dispositif d'obturation d'un circuit vide-vite d'aéronef |
CN201080030833.2A CN102481982B (zh) | 2009-07-10 | 2010-07-07 | 用于关闭航空器的应急放空回路的设备 |
US13/382,078 US8651143B2 (en) | 2009-07-10 | 2010-07-07 | Device for shutting a jettisoning circuit of an aircraft |
CA2767635A CA2767635C (fr) | 2009-07-10 | 2010-07-07 | Dispositif d'obturation d'un circuit vide-vite d'aeronef |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0954824 | 2009-07-10 | ||
FR0954824A FR2947807B1 (fr) | 2009-07-10 | 2009-07-10 | Dispositif d'obturation d'un circuit vide-vite d'aeronef |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011004119A1 true WO2011004119A1 (fr) | 2011-01-13 |
Family
ID=41665475
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2010/051429 WO2011004119A1 (fr) | 2009-07-10 | 2010-07-07 | Dispositif d'obturation d'un circuit vide-vite d'aéronef |
Country Status (7)
Country | Link |
---|---|
US (1) | US8651143B2 (fr) |
EP (1) | EP2451709A1 (fr) |
CN (1) | CN102481982B (fr) |
CA (1) | CA2767635C (fr) |
FR (1) | FR2947807B1 (fr) |
RU (1) | RU2012104669A (fr) |
WO (1) | WO2011004119A1 (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USD712769S1 (en) * | 2012-08-22 | 2014-09-09 | Eaton Corporation | Sensor housing for hydraulic hose |
CN107407661B (zh) * | 2015-03-31 | 2020-03-31 | 庞巴迪公司 | 用于无损检测的密封组件和插塞 |
CN108397634B (zh) * | 2018-04-25 | 2024-04-19 | 上海德朗汽车散热器制造有限公司 | 一种用于汽车散热器泄漏检测的水检闷头 |
CN114165673B (zh) * | 2021-10-18 | 2024-04-16 | 上海贤日测控科技有限公司 | 堵头装置 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2855003A (en) * | 1956-01-11 | 1958-10-07 | Ellis B Thaxton | Pipe stoppers |
US3483894A (en) * | 1966-04-07 | 1969-12-16 | Us Navy | High pressure pipe test plug |
US4624426A (en) * | 1984-07-30 | 1986-11-25 | Muscatell Ralph P | Fuel dump mechanism for aircraft |
WO2008017152A1 (fr) * | 2006-08-07 | 2008-02-14 | Car-Ber Investments Inc. | Dispositif et procédé pour isoler ou tester un segment de tuyau comportant un renfort axial |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2062519A (en) * | 1934-03-31 | 1936-12-01 | Ljungberg Johan Wilhelm | Testing plug |
US2475748A (en) * | 1945-10-10 | 1949-07-12 | Leroy Gene | Boiler tube test plug |
US2764184A (en) * | 1954-05-24 | 1956-09-25 | Shell Dev | Expandable tube plug |
US2937666A (en) * | 1957-05-31 | 1960-05-24 | Maisch Oliver | Internal tube seal |
US2856963A (en) * | 1957-06-19 | 1958-10-21 | Exxon Research Engineering Co | Tube plugging device |
US3156373A (en) * | 1962-05-28 | 1964-11-10 | Han Le Ray Corp | Plug devices |
US3618811A (en) * | 1969-09-15 | 1971-11-09 | Harsco Corp | Releasable fluid seal or test plug for conduits |
US3691609A (en) * | 1970-03-25 | 1972-09-19 | Hydro Vel Services Inc | Tube plugging tool |
US3983904A (en) * | 1975-03-13 | 1976-10-05 | Laviano Louis R | Plug assembly for sealing a pipe |
GB1518425A (en) * | 1976-02-19 | 1978-07-19 | Furmanite Int Ltd | Tube plug |
US4303101A (en) * | 1980-04-14 | 1981-12-01 | Tholen James W | End plug assembly for sewer pipe |
US4653540A (en) * | 1985-02-08 | 1987-03-31 | Norman Epstein | Plug for heat exchanger tubes |
-
2009
- 2009-07-10 FR FR0954824A patent/FR2947807B1/fr not_active Expired - Fee Related
-
2010
- 2010-07-07 US US13/382,078 patent/US8651143B2/en not_active Expired - Fee Related
- 2010-07-07 RU RU2012104669/11A patent/RU2012104669A/ru not_active Application Discontinuation
- 2010-07-07 CN CN201080030833.2A patent/CN102481982B/zh not_active Expired - Fee Related
- 2010-07-07 CA CA2767635A patent/CA2767635C/fr not_active Expired - Fee Related
- 2010-07-07 EP EP10742213A patent/EP2451709A1/fr not_active Withdrawn
- 2010-07-07 WO PCT/FR2010/051429 patent/WO2011004119A1/fr active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2855003A (en) * | 1956-01-11 | 1958-10-07 | Ellis B Thaxton | Pipe stoppers |
US3483894A (en) * | 1966-04-07 | 1969-12-16 | Us Navy | High pressure pipe test plug |
US4624426A (en) * | 1984-07-30 | 1986-11-25 | Muscatell Ralph P | Fuel dump mechanism for aircraft |
WO2008017152A1 (fr) * | 2006-08-07 | 2008-02-14 | Car-Ber Investments Inc. | Dispositif et procédé pour isoler ou tester un segment de tuyau comportant un renfort axial |
Also Published As
Publication number | Publication date |
---|---|
CA2767635C (fr) | 2017-08-08 |
FR2947807B1 (fr) | 2012-05-18 |
CN102481982B (zh) | 2015-07-22 |
RU2012104669A (ru) | 2013-08-20 |
CA2767635A1 (fr) | 2011-01-13 |
US20120104173A1 (en) | 2012-05-03 |
EP2451709A1 (fr) | 2012-05-16 |
FR2947807A1 (fr) | 2011-01-14 |
CN102481982A (zh) | 2012-05-30 |
US8651143B2 (en) | 2014-02-18 |
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