WO2000020275A2 - Fenetre d'avion - Google Patents

Fenetre d'avion Download PDF

Info

Publication number
WO2000020275A2
WO2000020275A2 PCT/US1999/021302 US9921302W WO0020275A2 WO 2000020275 A2 WO2000020275 A2 WO 2000020275A2 US 9921302 W US9921302 W US 9921302W WO 0020275 A2 WO0020275 A2 WO 0020275A2
Authority
WO
WIPO (PCT)
Prior art keywords
interior
trusses
exterior
window
windowpane
Prior art date
Application number
PCT/US1999/021302
Other languages
English (en)
Other versions
WO2000020275A3 (fr
Inventor
Samuels B. Williams
Original Assignee
Williams International Co., L.L.C.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Williams International Co., L.L.C. filed Critical Williams International Co., L.L.C.
Priority to AU62509/99A priority Critical patent/AU6250999A/en
Publication of WO2000020275A2 publication Critical patent/WO2000020275A2/fr
Publication of WO2000020275A3 publication Critical patent/WO2000020275A3/fr

Links

Classifications

    • 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
    • B64C1/1476—Canopies; Windscreens or similar transparent elements
    • B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen

Definitions

  • the instant invention relates generally to aircraft windows and more particularly to an aircraft window comprising posts and trusses that are integral with a composite fuselage.
  • the window frame posts and trusses are of minimal width to maximize passenger visibility.
  • Conventional aircraft window construction generally comprises a plurality of small elliptical or circular window panes, often constructed of plexiglass or polycarbonate material, arranged adjacent the passenger seating areas and recessed within the skin ofthe aircraft fuselage.
  • Known-in-the-art windows are generally of minimal size due to the difficulty of maintaining a pressure seal around each window, and the subsequent loss of cabin pressurization resulting from an inoperative window seal.
  • prior art windows have been designed to be relatively small in order to maintain sufficient strength and stiffness throughout the fuselage structure to bear the considerable forces acting on the airframe in flight.
  • prior art jet aircraft windows provide for only limited passenger visibility outside the aircraft.
  • An aircraft passenger cabin having a relatively small cross sectional area in conjunction with small passenger windows contributes to and exacerbates the phenomenon of claustrophobia experienced by some aircraft passengers.
  • the relatively wide structural members comprising the fuselage sections between the windows prohibit increasing the size ofthe windows appreciably and further contribute to the perception of being enclosed in a small space.
  • These wide posts are required in most airframes to dissipate forces such as hoop tension resulting from cabin pressurization and the shear forces associated with bending stress acting on the fuselage.
  • the instant invention utilizes top and bottom longitudinal trusses in conjunction with a plurality of lateral posts disposed therebetween to provide a strong, lightweight structure integrated within a composite or alloy aircraft fuselage for aircraft passenger windows.
  • Both the longitudinal trusses and the lateral posts are comprised of lightweight, known-in-the art alloy or composite material having a substantially greater cross-section than the fuselage skin ofthe aircraft.
  • the longitudinal trusses are integral to the fuselage skin along one edge thereof and have a reinforcement portion comprised of composite or alloy material tapering into the fuselage skin at the intersections ofthe longitudinal trusses and lateral posts.
  • the tapered reinforcement sections are utilized to distribute the loading forces acting upon the window and fuselage evenly throughout the intersection ofthe fuselage and the longitudinal trusses.
  • the longitudinal trusses have a first edge portion having interior and exterior rabbets thereon for engaging an interior windowpane and a plurality of exterior windowpanes respectively.
  • a plurality of lateral posts are disposed between and intersect the horizontal trusses. At each point of intersection between the posts and the trusses, the relatively rectangular post cross-section widens longitudinally into the longitudinal first edge portion, forming an arcuate intersection thereof.
  • the aforementioned tapered sections distribute the forces due to hoop tension acting on the lateral posts to the longitudinal trusses and thereafter, to the fuselage skin.
  • An additional second tapered composite or alloy reinforcement section disposed between the longitudinal trusses and the fuselage skin at the points of intersection ofthe lateral posts and the longitudinal trusses is further provided to strengthen the window structure. The second reinforcement section widens longitudinally and tapers laterally to blend into the fuselage skin.
  • the lateral posts are comprised of both interior and end posts, depending upon their position in the window frame.
  • the interior posts have a smaller width than the longitudinal trusses, for reasons explained hereinbelow. Additionally, the interior posts have a single rabbet disposed along the length of opposing post edge portions.
  • the end posts are disposed at the ends of a section of windows, for example at the last window near the tail ofthe aircraft, or between the window nearest the nose ofthe aircraft and the aircraft door, and further have both interior and exterior rabbets along the length of a first edge portion for engagement ofthe interior and exterior aircraft windows.
  • the end posts are constructed similarly to the longitudinal trusses, having one edge portion integral with and tapering into the fuselage skin, and an opposite edge portion having both interior and exterior rabbets. The rabbets engage both the interior and exterior windowpanes respectively.
  • the exterior posts have a width and cross-sectional area identical to the width ofthe longitudinally extending trusses.
  • the laterally extending interior posts are constructed with a slightly thinner cross- section than the longitudinally extending trusses to allow a single continuous interior window pane to be positioned between and engaged by a pair of end posts and longitudinal trusses. This allows the interior window surface ofthe passenger seating area along one side ofthe aircraft, for example, to be comprised of a single convex piece of clear polycarbonate material (as viewed from the exterior ofthe aircraft) running from one end post to another, without interruption from the interior posts.
  • the exterior windowpanes are comprised of individual panes of polycarbonate material that engage the exterior rabbets of and are bounded by a spaced pair of lateral posts and both longitudinal trusses.
  • the exterior windowpanes are provided with a notched edge portion around the perimeter thereof for engaging the aforementioned exterior rabbets ofthe trusses and the end posts.
  • the edge portion around the perimeter of each exterior pane provides a measure of protection against window blowout caused by cabin pressurization. It should be noted that the exterior windowpanes bear the force created by the difference in pressure between the aircraft cabin and the atmosphere when the aircraft is at altitude.
  • the instant invention also provides for a windowpane occupying a large portion of an aircraft door.
  • the top and bottom sections ofthe door frame are comprised ofthe aforementioned longitudinal trusses and the sides thereof are each provided with an end post. In this fashion, a large percentage ofthe aircraft fuselage from the cockpit to the tail is comprised of window material.
  • a yet further object ofthe instant invention is to provide for an aircraft window construction utilizing composite or alloy material trusses and posts to minimize the amount of structural material required to support the window panes while maintaining the structural integrity ofthe aircraft.
  • a further object ofthe instant invention is to provide a double-paned aircraft window having an interior pane substantially uninterrupted by vertical structural members.
  • Figure 1 is a perspective view of a forward swept-wing aircraft in accordance with the present invention.
  • Figure 2 is a view ofthe aircraft window taken in the direction ofthe arrow 2 of Fig. 1.
  • Figure 3 is a view ofthe instant invention taken along the line 3-3 of Fig. 2.
  • Figure 4 is a view ofthe aircraft window taken in the direction ofthe arrow 4 of Fig. 3.
  • Figure 5 is a view similar to Fig. 4 with only the exterior windows installed.
  • Figure 6 is a view ofthe instant invention taken along the line 6-6 of Fig. 4.
  • Figure 7 is a view ofthe instant invention taken along the line 7-7 of Fig. 4.
  • Figure 8 is a view of an alternative embodiment ofthe instant invention similar to Fig. 3.
  • Figure 9 is a perspective view of a swept-wing aircraft in accordance with an alternative embodiment ofthe instant invention.
  • a window 10 for an aircraft 20 having a fuselage 22 and a fuselage skin 24 comprises a pair of spaced longitudinal extending trusses 30 integral to the fuselage skin 24 interconnected by a plurality of laterally extending interior posts 50 and at least two laterally extending end posts 60 disposed therebetween.
  • the trusses 30 have a relatively greater cross-section than that ofthe fuselage skin 24.
  • the trusses 30 are disposed along the fuselage 22 in generally parallel spaced relation to each other to define the top and bottom ofthe window 10 opening.
  • Both trusses 30 are comprised ofthe same known-in-the-art composite or alloy material as employed in the fuselage skin 24 and are constructed as an integral part thereof. Each truss has a first elongated edge portion 32 extending both laterally and longitudinally along the fuselage 22.
  • each truss 30 first edge portion 32 is comprised of a plurality of exterior rabbets 34 disposed along the entire length ofthe first edge portion 32, and an interior rabbet 36 disposed along the entire length ofthe edge portion 32 ofthe truss 30.
  • the exterior rabbets 34 and the interior rabbets 36 are substantially parallel to each other along the length ofthe truss 30 first edge portion 32.
  • each longitudinally extending truss 30 has a second edge portion 38 opposite the first edge portion 32 extending both laterally and longitudinally along the length ofthe truss 30.
  • the second edge portion 38 is integral with a plurality of tapered reinforcement sections 40 blending the substantially thicker truss 30 cross-section into the relatively thin fuselage skin 24.
  • the reinforcement sections 40 are disposed on the trusses 30 at the intersections ofthe trusses 30 and the laterally extending posts 50 and 60, and have a thickness identical to that ofthe trusses 30 at the second edge portion 38 thereof tapering to a nominal thickness where the reinforcement sections 40 blend into the fuselage skin 24.
  • the trusses 30 and the posts 50 and 60 each have hollow interiors for minimizing the weight thereof.
  • the exterior rabbets 34 provide a mating surface for a plurality of convex shaped exterior windowpanes (as viewed from the exterior ofthe aircraft) 70 having a notched edge portion 72 disposed around the perimeter thereof.
  • the exterior rabbet 34 ofthe truss 30 engages the notched edge portion 72 ofthe exterior window panes 70 to prevent the panes 70 from "blowing out” due to the pressure differential between the interior ofthe aircraft 20 and the atmosphere at altitude.
  • the plurality of exterior windows 70 form a substantially smooth surface with the fuselage skin 24 on the exterior ofthe aircraft 20 when the windows 70 are properly engaged by the rabbets 34.
  • a single convex interior window 80 has a shaped edge portion 82 disposed around the perimeter thereof to engage the interior rabbet 36 ofthe longitudinally extending trusses 30.
  • the interior window 80 is disposed substantially parallel to the plurality of exterior window panes 70, wherein the interior rabbet 36 ofthe truss 30 engages the edge portion 82, thereby forming a double paned aircraft window 10.
  • Both the interior 80 and exterior 70 windows are secured in place by applying a suitable airtight adhesive to the edge portions thereof, thereby creating a dead air space therebetween. This air space acts as an efficient insulator, thus protecting passengers from temperature extremes.
  • Both the exterior windows 70 and the interior window 80 can further comprise a plurality of arcuate sections 84 at the corners thereof, providing the windows 70 and 80 with rounded corners.
  • the opposing longitudinally extending trusses 30 are interconnected by a plurality of elongated spaced laterally extending interior posts 50, each having opposing edge portions 52 extending both laterally and longitudinally along the length ofthe interior posts 50.
  • Each edge portion 52 is provided with an exterior rabbet 54 disposed along the entire length thereof.
  • the interior post rabbets 54 intersect and are integral with the truss 30 exterior rabbets 34 to form a plurality of continuous exterior rabbet surfaces 90 for engaging the notched edge 82 ofthe exterior window panes 70. As shown in Figs.
  • At least two elongated laterally extending end posts 60 are provided having opposing first and second edge portions 62 and 64 respectively, extending both laterally and longitudinally along the length ofthe post 60.
  • the end posts 60 are disposed between the opposing ends ofthe trusses 30.
  • Each end post 60 is provided with an exterior rabbet 66 and an interior rabbet 68 disposed along the first edge portion 62 thereof.
  • the end posts 60 intersect and are integral to both the top and bottom trusses 30 to provide an end to the window structure 10.
  • the end post 60 exterior rabbet 66 intersects both the top and bottom truss 30 exterior rabbets 34 to form a continuous exterior rabbet surface 90 for engaging the plurality of exterior window panes 70.
  • the second edge portion 64 is integral with and tapers into the relatively thin fuselage skin 24.
  • the interior rabbet 68 ofthe end posts 60 intersects the interior rabbets 36 ofthe top and bottom trusses 30 to form a continuous interior rabbet surface 100 extending around the perimeter ofthe interior window 80 and engaging the edge portion 82 thereof.
  • the interior rabbet surface 100 is comprised ofthe individual interior rabbets 36 ofthe trusses 30, and the interior rabbets 68 ofthe end posts 60.
  • the interior posts 50 must have a cross-section slightly smaller than that ofthe trusses 30 to allow the engagement ofthe interior window pane 80 edge portion 82 with the continuous interior rabbet surface 100.
  • This feature ofthe instant invention allows the interior window 80 ofthe instant invention to be comprised of a continuous piece of suitable window material, such as Plexiglas or a similar polycarbonate, uninterrupted by structural posts in the interior ofthe aircraft 20.
  • the continuous interior window 80 may further have a plurality of weep holes 86 disposed along the bottom edge thereof, to allow for the escape of condensation from between the interior 80 and exterior 70 window panes.
  • the trusses 30, the interior posts 50, and the end posts 60 each have an exterior rabbet 34, 54, and 68 respectively, oriented to engage a shaped edge 74 of a single exterior window 70 when positioned from the exterior ofthe aircraft.
  • the exterior windowpane 70 is positioned to engage the rabbets 34, 54, and 68 from the exterior ofthe aircraft and is secured thereto using a known-in-the-art epoxy adhesive suitable for bonding polycarbonate and composite fiber materials.
  • This embodiment ofthe instant invention allows a single exterior windowpane 70 occupying the entire length ofthe fuselage window section to be employed, similar to the continuous interior window 80.
  • the interior laterally extending posts 50 are disposed between and act to separate the exterior 70 and interior 80 windowpanes.
  • the instant invention can further be utilized in conjunction with conventional aircraft door by providing a door with an opposed pair of longitudinally extending trusses 30 and a pair of spaced laterally extending end posts 60 integral thereto. If necessary, the cross-section ofthe end posts 60 may be increased to accommodate the required locking and latching mechanisms therein.
  • the aircraft window 10 is elliptical or oval such that the interior windowpane 80 and the plurality of exterior windowpanes 90 form a substantially elliptical shape when engaged in their respective rabbets.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Vehicle Interior And Exterior Ornaments, Soundproofing, And Insulation (AREA)

Abstract

La présente invention concerne une fenêtre à double vitrage (10) pour un avion (20) offrant une visibilité supérieure pour les passagers et une construction de fenêtre selon l'état de l'art. De manière spécifique, l'invention prévoit une paire d'armatures (30) s'étendant de manière parallèle dans le sens longitudinal, recoupées par plusieurs montants d'extrémité (60) et intérieurs (58) s'étendant de manière latérale et espacée pour constituer une structure légère et robuste d'une fenêtre d'avion. Les éléments structuraux peuvent se constituer d'un matériau composite ou de matériaux d'alliage pour avion bien connus dans l'art et qui présentent une forme conique en s'amincissant en direction du revêtement du fuselage jusqu'à former partie intégrante de ce dernier. Plusieurs feuillures (34, 36) placées autour du périmètre des deux armatures horizontales (30) et des montants verticaux (50, 60) se mettent en prise avec une fenêtre intérieure continue (80) et plusieurs fenêtres extérieures (70) pour empêcher toute rupture de fenêtre.
PCT/US1999/021302 1998-10-06 1999-09-15 Fenetre d'avion WO2000020275A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU62509/99A AU6250999A (en) 1998-10-06 1999-09-15 Aircraft window

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US16686998A 1998-10-06 1998-10-06
US09/166,869 1998-10-06

Publications (2)

Publication Number Publication Date
WO2000020275A2 true WO2000020275A2 (fr) 2000-04-13
WO2000020275A3 WO2000020275A3 (fr) 2000-07-13

Family

ID=22605012

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1999/021302 WO2000020275A2 (fr) 1998-10-06 1999-09-15 Fenetre d'avion

Country Status (2)

Country Link
AU (1) AU6250999A (fr)
WO (1) WO2000020275A2 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1281613A3 (fr) * 2001-08-03 2004-02-04 Mitsubishi Heavy Industries, Ltd. Fenêtre d'avion en résine synthétique avec un revêtement dur et son procédé de réalisation
WO2005065920A3 (fr) * 2003-09-04 2005-09-15 Boeing Co Panneau de revetement a fenetre et procede pour son production
WO2005056383A3 (fr) * 2003-09-04 2005-12-08 Boeing Co Panneau de revetement transparent impregne de resine et procede permettant de produire ce panneau
US7028950B2 (en) 2004-05-10 2006-04-18 The Boeing Company Load bearing window
EP1375339A3 (fr) * 2002-06-25 2009-05-06 The Boeing Company Fenêtres d'avion et procédés associés pour son installation
WO2009098159A1 (fr) * 2008-02-05 2009-08-13 Airbus Operations Gmbh Fenêtre d'avion stratifiée porteuse tolérante aux dommages
FR2928343A1 (fr) * 2008-03-10 2009-09-11 Airbus France Sas Panneau du hublot et procede de fabrication d'un tel panneau aeronef comprenant un panneau de hublot
JP2009538778A (ja) * 2006-06-02 2009-11-12 エアバス ドイチェランド ゲゼルシャフト ミット ベシュレンクテル ハフツング 胴体構造及びその製造方法
WO2012066264A1 (fr) * 2010-11-19 2012-05-24 Airbus Operations Hublot de cabine à déformation programmée, procédé de fabrication d'un tel hublot et aéronef incorporant un tel hublot
AT513942A1 (de) * 2013-01-22 2014-08-15 Htp High Tech Plastics Gmbh Vorrichtung zur Abdeckung einer Sichtöffnung

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3429530A (en) * 1965-11-10 1969-02-25 Heinrich Hertel Window construction for fuselages of aircraft
US5044578A (en) * 1989-12-27 1991-09-03 White Thomas H Universal cabin sidewall panel for aircraft
US5271581A (en) * 1992-05-29 1993-12-21 Irish Michael J Window clip for aircraft
US5467943A (en) * 1993-08-19 1995-11-21 Jamco Corporation Window structure equipped on side walls of a cabin in the body of an airplane
US5988566A (en) * 1996-12-05 1999-11-23 Daimlerchrysler Aerospace Airbus Gmbh Aircraft window construction

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3429530A (en) * 1965-11-10 1969-02-25 Heinrich Hertel Window construction for fuselages of aircraft
US5044578A (en) * 1989-12-27 1991-09-03 White Thomas H Universal cabin sidewall panel for aircraft
US5271581A (en) * 1992-05-29 1993-12-21 Irish Michael J Window clip for aircraft
US5467943A (en) * 1993-08-19 1995-11-21 Jamco Corporation Window structure equipped on side walls of a cabin in the body of an airplane
US5988566A (en) * 1996-12-05 1999-11-23 Daimlerchrysler Aerospace Airbus Gmbh Aircraft window construction

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1707591A2 (fr) * 2001-08-03 2006-10-04 Mitsubishi Heavy Industries, Ltd. Procédé de production d'une fenêtre d'aéronef en matériau plastique avec revêtement anti-abrasif
US6756126B2 (en) 2001-08-03 2004-06-29 Mitsubishi Heavy Industries, Ltd. Aircraft window of synthetic resin having hard coated film and a method for producing the same
EP1281613A3 (fr) * 2001-08-03 2004-02-04 Mitsubishi Heavy Industries, Ltd. Fenêtre d'avion en résine synthétique avec un revêtement dur et son procédé de réalisation
EP1707591A3 (fr) * 2001-08-03 2007-02-21 Mitsubishi Heavy Industries, Ltd. Procédé de production d'une fenêtre d'aéronef en matériau plastique avec revêtement anti-abrasif
EP1375339A3 (fr) * 2002-06-25 2009-05-06 The Boeing Company Fenêtres d'avion et procédés associés pour son installation
EP2221168A1 (fr) * 2003-09-04 2010-08-25 The Boeing Company Panneau de revêtement de fenêtre et son procédé de fabrication
JP2007504049A (ja) * 2003-09-04 2007-03-01 ザ・ボーイング・カンパニー 樹脂が注入された透明な外皮パネルおよびその製造方法
US7300693B2 (en) 2003-09-04 2007-11-27 The Boeing Company Resin infused transparent skin panel and method of making same
WO2005056383A3 (fr) * 2003-09-04 2005-12-08 Boeing Co Panneau de revetement transparent impregne de resine et procede permettant de produire ce panneau
US7651756B2 (en) 2003-09-04 2010-01-26 The Boeing Company Resin infused transparent skin panel and method of making same
WO2005065920A3 (fr) * 2003-09-04 2005-09-15 Boeing Co Panneau de revetement a fenetre et procede pour son production
US7968170B2 (en) 2003-09-04 2011-06-28 The Boeing Company Composite single pane window for an aircraft and method of making same
US8262823B2 (en) 2003-09-04 2012-09-11 The Boeing Company Window skin panel and method of making same
US7028950B2 (en) 2004-05-10 2006-04-18 The Boeing Company Load bearing window
JP2009538778A (ja) * 2006-06-02 2009-11-12 エアバス ドイチェランド ゲゼルシャフト ミット ベシュレンクテル ハフツング 胴体構造及びその製造方法
US8444088B2 (en) 2006-06-02 2013-05-21 Airbus Operations Gmbh Fuselage structure and method for the production of a fuselage structure
US8245975B2 (en) 2008-02-05 2012-08-21 Airbus Operations Gmbh Load-supporting and damage-tolerant laminated aircraft window
WO2009098159A1 (fr) * 2008-02-05 2009-08-13 Airbus Operations Gmbh Fenêtre d'avion stratifiée porteuse tolérante aux dommages
FR2928343A1 (fr) * 2008-03-10 2009-09-11 Airbus France Sas Panneau du hublot et procede de fabrication d'un tel panneau aeronef comprenant un panneau de hublot
US8286915B2 (en) 2008-03-10 2012-10-16 Airbus Operations Sas Aircraft comprising a window panel
FR2967644A1 (fr) * 2010-11-19 2012-05-25 Airbus Operations Sas Hublot de cabine a deformation programmee, procede de fabrication d'un tel hublot et aeronef incorporant un tel hublot
WO2012066264A1 (fr) * 2010-11-19 2012-05-24 Airbus Operations Hublot de cabine à déformation programmée, procédé de fabrication d'un tel hublot et aéronef incorporant un tel hublot
CN103221305A (zh) * 2010-11-19 2013-07-24 空中客车运营简化股份公司 具有程控变形的机舱舷窗、制造这类舷窗的方法和包括这类舷窗的航空器
US9114870B2 (en) 2010-11-19 2015-08-25 Airbus Operations (S.A.S.) Cabin window with planned deformation, method of manufacturing such a window and aircraft comprising such a window
CN103221305B (zh) * 2010-11-19 2015-11-25 空中客车运营简化股份公司 具有程控变形的机舱舷窗、制造这类舷窗的方法和包括这类舷窗的航空器
RU2574048C2 (ru) * 2010-11-19 2016-01-27 Эрбюс Операсьон Иллюминатор кабины с запрограммированной деформацией, способ изготовления такого иллюминатора и летательный аппарат, содержащий такой иллюминатор
AT513942A1 (de) * 2013-01-22 2014-08-15 Htp High Tech Plastics Gmbh Vorrichtung zur Abdeckung einer Sichtöffnung
AT513942B1 (de) * 2013-01-22 2017-11-15 Htp High Tech Plastics Gmbh Vorrichtung zur Abdeckung einer Sichtöffnung

Also Published As

Publication number Publication date
WO2000020275A3 (fr) 2000-07-13
AU6250999A (en) 2000-04-26

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