EP1668198A1 - Structures deployables - Google Patents

Structures deployables

Info

Publication number
EP1668198A1
EP1668198A1 EP04775603A EP04775603A EP1668198A1 EP 1668198 A1 EP1668198 A1 EP 1668198A1 EP 04775603 A EP04775603 A EP 04775603A EP 04775603 A EP04775603 A EP 04775603A EP 1668198 A1 EP1668198 A1 EP 1668198A1
Authority
EP
European Patent Office
Prior art keywords
deployable structure
deployable
members
hinge
elements
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Withdrawn
Application number
EP04775603A
Other languages
German (de)
English (en)
Other versions
EP1668198A4 (fr
Inventor
Jat Y.R. c/o Nat. University Of Singapore LIEW
A. c/o Nat University of Singapore KRISHNAPILLAI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
National University of Singapore
Original Assignee
National University of Singapore
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 National University of Singapore filed Critical National University of Singapore
Publication of EP1668198A1 publication Critical patent/EP1668198A1/fr
Publication of EP1668198A4 publication Critical patent/EP1668198A4/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
    • E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
    • E04B1/343—Structures characterised by movable, separable, or collapsible parts, e.g. for transport
    • E04B1/344—Structures characterised by movable, separable, or collapsible parts, e.g. for transport with hinged parts
    • E04B1/3441—Structures characterised by movable, separable, or collapsible parts, e.g. for transport with hinged parts with articulated bar-shaped elements
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
    • E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
    • E04B1/18—Structures comprising elongated load-supporting parts, e.g. columns, girders, skeletons
    • E04B1/19—Three-dimensional framework structures
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/005—Girders or columns that are rollable, collapsible or otherwise adjustable in length or height
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
    • E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
    • E04B1/18—Structures comprising elongated load-supporting parts, e.g. columns, girders, skeletons
    • E04B1/19—Three-dimensional framework structures
    • E04B2001/1996—Tensile-integrity structures, i.e. structures comprising compression struts connected through flexible tension members, e.g. cables

Definitions

  • the present invention relates broadly to deployable structures and an assembly comprising a plurality of deployable structures.
  • Deployable structures for example, space frames, beam structures, etc.
  • These structures are usually transported in a folded state to a chosen site for deployment. After use, they may be folded back and stored for redeployment.
  • conventional deployable structures suffer from poor structural configurations in a fully deployed state.
  • Many conventional foldable structures deploy into non-optimal shapes as the requirement for the structure to be foldable imposes geometric constraints that are sometimes contrary to structural requirements.
  • the deployable structures may be bulky in a folded state, and are mechanically complex in design.
  • Typical self-stabilizing or “clicking” or “self-locking” deployable structures do not provide structurally optimal forms in the fully deployed state. Some of them require enormous forces and coordination for deployment and undergo significant bending during deployment. Other forms of structural systems require a large number of individual components and complicated assembly operations to form the structure, making deployment or folding the structures time consuming and costly.
  • a deployable structure comprising: a plurality of pairs of hingeably connected members, a first hinge element; and a second hinge element; wherein the two members of each pair of hingeably connected members are connected to the first and the second hinge elements respectively; and wherein the first hinge element is capable of being stabilized for facilitating stabilization of the deployable structure into a deployed state.
  • the deployable structure may further comprise: a central member wherein the first and second hinge elements are connected to different ends of the central member; and wherein one portion of the first hinge element is detachably connected to the central member such that the first hinge element is stabilized when connected to the central member.
  • the deployable structure may further comprise a fastening element to fasten the first hinge element to the central member.
  • the deployable structure may comprise three or more pairs of hingeably connected members.
  • One of the two members in each pair of hingeably connected members may be connected to the other member of said pair by at least one third hinge element.
  • the deployable structure may further comprise cables or flexible elements connecting the third hinge elements.
  • One of the two members in each pair of hingeably connected members may connected to the other member of said pair via one or more secondary members.
  • the secondary members may be substantially parallel to an imaginary line joining the first and second hinge elements, when the deployable structure is in the deployed state.
  • the hinge elements may allow a single degree-of-freedom of movement.
  • the members may comprise one or more of a group comprising struts, rods, tubes, telescopic elements, self stabilizing elements and cables.
  • the deployable structure may further comprise one or more energy stored devices for facilitating deployment and/or folding of the deployable structure.
  • an assembly comprising a plurality of deployable structures, each deployable structure comprising: a plurality of pairs of hingeably connected members, a first hinge element; and a second hinge element; wherein the two members of each pair of hingeably connected members are connected to the first and the second hinge element respectively; and wherein the first hinge element is capable of being stabilized for facilitating stabilizing the deployable structure in a deployed state.
  • Each deployable structure may further comprise: a central member wherein the first and second hinge elements are connected to different ends of the central member; and wherein one portion of the first hinge element is detachably connected to the central member such that the first hinge element is stabilized when connected to the central member.
  • the assembly may further comprise at least one cable or connecting the plurality of deployable structures.
  • Figure 1 is a schematic representation of a deployable structure according to an embodiment of the present invention
  • Figure 2 is a schematic representation of the deployable structure of Figure 1 when partially folded;
  • Figure 3a is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • Figure 3b is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • Figure 4 a is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • Figure 4b is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • Figure 4c is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • Figure 5 is a schematic representation of the deployable structure Figure 1 , showing an upper plane, a middle plane and a lower plane;
  • Figure 6 is a schematic representation of a structural unit according to another embodiment of the present invention.
  • Figure 7 is a schematic representation of a structural unit according to yet another embodiment of the present invention.
  • Figure 8 is a schematic representation of a structural unit according to another embodiment of the present invention.
  • Figure 9 is a schematic representation of a structural unit according to yet another embodiment of the present invention.
  • Figure 10 is a schematic representation of a structural unit according to another embodiment of the present invention.
  • the described embodiments relate to a structural system of foldable, deployable or collapsible structures made up of interconnected units that are extensible and collapsible into various structural shapes, for example, space frames, panels, columns, domes, vaults.
  • the deployable structure 100 comprises a central element 130, four upper elements 140, four lower elements 150, and a network of cables or flexible elements 170.
  • the upper and lower elements 140, 150 are struts.
  • the four lower elements 150 are attached to a lower hinge 104, and the four upper elements 140 are attached to an upper hinge 108.
  • Each of the upper elements 140 is hingeably connected to a corresponding lower element 150 by a middle hinge 112, forming a pair.
  • Each middle hinge 112 is connected to adjacent middle hinges 112 by the network of cables 170.
  • the upper and lower elements 140, 150 may be made of metallic or composite materials.
  • the hinges 104, 108, 112 allow the upper and lower elements 140, 150 to rotate in a single degree-of-freedom, acting as pin-joints, and enable deployment and folding of the deployable structure 100.
  • a central element 130 When the deployable structure 100 is in a deployed state, one end of a central element 130 is detachably connected to the upper elements 140 via the upper hinge 108, and the other end of the central element 130 is connected to the lower elements 150 via the lower hinge 104.
  • This allows the deployable structure100 to be folded or deployed by attaching or detaching the end of the central element 130 from the upper hinge 108.
  • the central element 130 may be detachably connected to either the lower hinge 104 or the upper hinge 108 at one end or both ends.
  • the central element 130 may comprise two sections (not shown) detachably joined with each end of the central element 130 attached to the upper hinge 108 and the lower hinge 104, respectively.
  • the upper hinge 108 may have means for disengaging and engaging the detachable end of the central element 130, for example, a fastening mechanism (not shown) may be used to lock the detachable end of the central element 130 to the upper hinge 108 when the deployable structure 100 is fully deployed.
  • the central element 130 is substantially perpendicular to the ground 190.
  • the deployable structure 100 in Figure 1 is in the form of a square module. However, it should be appreciated that numerous other configurations, for example, triangular, hexagonal, pentagonal or other polygonal shapes may be formed with substantially the same arrangement, which has the central element 130 connecting the lower and upper hinges 104, 108.
  • the basic unit shown in Figure 1 can also be implemented without the central member by restraining the geometry of the upper elements (140) and lower elements 150 by means of a lockable hinges 108, 112, 104, which restrain the movement of the elements 140, 150 when the deployable structure 100 is in the fully deployed state.
  • upper hinges 1080 may be disposed between lower hinges 1040 and a network of cables or flexible members 1700 joining the middle hinges 1120, as shown in Figure 10.
  • Figure 2 is a schematic representation of the deployable structure 100 in a partially folded state.
  • the deployable structure 100 is folded from the fully deployed state by detaching the central element 130 from the upper hinge 108.This may be done by various means, for example, by releasing the fastening mechanism (not shown) on the upper hinge 108.
  • the central element 130 is in the form of a telescopic element, the length of the central element 130 may be reduced during detachment of the central element 130 from the upper hinge 108.
  • the detachable end of the central element 130 is disconnected from the upper hinge 108, the elements 140, 150 are folded towards the central member.
  • the cables or flexible members 170 By exploiting the flexibility of the cables or flexible members 170 to improve the foldability of the deployable structure 100, improved compaction of the structure 100 can be achieved, when the structure 100 is folded. Further, the use of the cables or flexible members 170 make the deployable structure 100 significantly lighter and stiffer, compared to conventional designs. The mechanical complexity of the structure is also minimised. The cables 170 also carry tensional loads efficiently and help to stabilise the geometry of the deployable structure 100. Furthermore, a wide variety of structural shapes may be created by varying the length of the cables 170. The cables 170 may be metallic or composite materials cables, fiber-based cables, etc.
  • a plurality of deployable structures may be connected and deployed to form structural systems.
  • a plurality of the deployable structures 300 may be connected in-line to form a beam 301 , as shown in Figure 3a.
  • a cable or 390 may be used to join the lower hinge 304 of each deployable structure 300 to form the beam 301.
  • the middle hinges e.g. 307 may be of an integral type between adjacent individual structures 300, i.e. one middle hinge e.g. 307 may be "shared" between adjacent individual structures 300.
  • a plurality of the deployable structures 350 may be connected in-line to form a beam 302, as shown in Figure 3b.
  • a cable 391 may be used to connect the upper hinges 306, in addition to the cable 391 joining the lower hinges 305.
  • a plurality of deployable structures 400 may be connected and deployed in an array to form space frames and vaults, as shown in Figure 4a.
  • connecting cables 490 may be used to join the lower hinges 404 of each of the deployable structures 400.
  • a combination of beam and space frame structures can also be synthesized using variations of the deployable structure 400. For example, a barrel vault configuration can be created by changing the lengths of the connecting cables 491 joining the lower elements 406, as shown in Figure 4b.
  • Figure 4c illustrates another example embodiment with additional connecting cables 493 connecting the upper elements 407.
  • the connecting cables 490, 493 may be in other forms, for example, elements.
  • Figures 4b and 4c show only one row of connected deployable structures.
  • the length of the connecting cables 490 joining the array of deployable structures 400 may be changed to achieve similar configurations shown in Figures 4b and 4c.
  • Other shapes, for example, a dome can also be created by using a combination of hexagonal, pentagonal, triangular and other structural shapes.
  • the deployable structure 500 may be divided into three planes - a first plane (lower plane) 510 comprising the lower hinge 504, a second plane (upper plane) 520 comprising the upper hinge 508 and a third plane (middle plane) 530, between the lower plane 510 and the upper plane 520, comprising by the middle hinges 512.
  • a network of cables (not shown), a membrane or sheet , etc may be attached to the upper and/or middle and/or lower planes 510, 520, 530 respectively to form various types of structural systems. It should be appreciated that a plurality of planes may be provided between the lower and upper planes 510, 520.
  • FIG. 6 shows a schematic representation of the deployable structure 700 according to another example embodiment.
  • the deployable structure 700 has two layers of middle hinges comprising upper middle hinges 712 and lower middle hinges 714.
  • a vertical member 765 connects each of the upper middle hinges 712 to a corresponding lower middle hinge 714, defining a parallelepiped..
  • deployable structural units may be disposed between an upper middle plane 862 and a lower middle plane 864 of the deployable structure 800, as shown in Figure 8, to increase the depth of the deployable structure 800, improve structural efficiency and to facilitate deployment of the structure 800.
  • the additional structural units 895 comprise a pair of rods 896, 897 pivoted to each other substantially in the centre.
  • the deployable structure 900 may comprise cables 970 connecting the middle hinges 912 diagonally, as shown in Figure 9.
  • the deployable structure 900 may also have additional cables connecting the middle hinges 912 (compare the cables 170 in Figure 1).
  • the central element may have energy stored devices such as springs, that help in the deployment process.
  • energy stored devices such as springs
  • Various telescopic and cable-realized mechanisms may be used to assist the coordinated deployment of the structure.
  • Springs may be incorporated into the hinges for the same purpose.
  • the cables may also be spring loaded or may have elastic attachments to prevent entanglement during deployment of the structure.
  • the elements may be telescopic or telescopic and lockable to provide flexibility in configuring the structure.
  • deployable structures may be combined with structural kinematic chains to facilitate deployment.
  • the cables and/or the elements may be pre-tensioned to enhance the structural behavior of the unit.
  • Fabric, sheet and other forms of covering material may be attached to the rods or cables by introducing additional connectors or by designing their shape to facilitate direct attachment.
  • the example embodiments described above allow the fully deployed state of the structure to be structurally optimal.
  • the structures in the example embodiments achieve quick installation with the minimal assembly operations.
  • the structure is substantially free of stress during deployment and in the folded configuration.
  • deployable structures include a wide range of temporary and permanent structures such as exhibition, emergency, entertainment, military, and space structures that require rapid deployment. It also can be used for shelters, roofs, bridges, pylons, radars, vaults and structures of various configurations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)

Abstract

La présente invention se rapporte à une structure déployable (100) comportant une pluralité d'éléments raccordés par charnières, un premier élément charnière (108) et un second élément charnière (104), les deux éléments de chaque paire d'éléments raccordée par charnières étant raccordés respectivement au premier et au second élément charnière, ledit premier élément charnière (108) pouvant être stabilisé pour faciliter la stabilisation de la structure déployable (100) dans un état déployé.
EP04775603A 2003-09-03 2004-09-03 Structures deployables Withdrawn EP1668198A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US49984803P 2003-09-03 2003-09-03
PCT/SG2004/000281 WO2005021882A1 (fr) 2003-09-03 2004-09-03 Structures deployables

Publications (2)

Publication Number Publication Date
EP1668198A1 true EP1668198A1 (fr) 2006-06-14
EP1668198A4 EP1668198A4 (fr) 2009-03-04

Family

ID=34272881

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04775603A Withdrawn EP1668198A4 (fr) 2003-09-03 2004-09-03 Structures deployables

Country Status (4)

Country Link
US (1) US20100058704A9 (fr)
EP (1) EP1668198A4 (fr)
CN (1) CN1875153A (fr)
WO (1) WO2005021882A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104018023A (zh) * 2014-05-06 2014-09-03 阜阳市光普照明科技有限公司 一种led封装用铜合金键合连接线的制备方法

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110252717A1 (en) * 2010-04-16 2011-10-20 Graf Fernandez Rodrigo Foldable structures for a construction
US8402711B2 (en) * 2010-07-16 2013-03-26 University Of South Florida Multistable shape-shifting surfaces
WO2012009719A2 (fr) * 2010-07-16 2012-01-19 University Of South Florida Surfaces changeant de forme
ES2640986T3 (es) * 2010-11-19 2017-11-07 European Space Agency Estructura de soporte desplegable compacta de poco peso
BE1020575A5 (fr) * 2012-03-16 2014-01-07 Carpro Construction et procede de construction.
US20150167288A1 (en) * 2012-07-06 2015-06-18 Paul Harkin Adjustable Structures
NO337317B1 (no) * 2013-11-04 2016-03-07 Ipi Access As Sammenleggbar, langstrakt bærekonstruksjonsmodul og en sammenleggbar, langstrakt modulær bjelkekonstruksjon.
CN103615639A (zh) * 2013-11-25 2014-03-05 中国航空工业集团公司沈阳发动机设计研究所 一种卫星反射器用可伸缩支撑机构
CN103758210B (zh) * 2014-01-10 2016-06-08 东南大学 一种用于实现自由曲面的完全折叠结构及其方法
US9783978B1 (en) * 2016-08-01 2017-10-10 University Of South Florida Shape-morphing space frame apparatus using linear bistable elements
US11680398B2 (en) * 2020-10-12 2023-06-20 Jacob Eisenberg Strata space frame

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3771274A (en) * 1972-05-30 1973-11-13 Gen Dynamics Corp Expandable retractable structure
US4539786A (en) * 1983-03-03 1985-09-10 Ltv Aerospace And Defense Co. Biaxial scissors fold, post tensioned structure

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3381923A (en) * 1965-12-27 1968-05-07 Fairchild Hiller Corp Deployable structure
US4290244A (en) * 1976-07-13 1981-09-22 Zeigler Theodore Richard Collapsible self-supporting structures and panels and hub therefor
US4587777A (en) * 1981-10-09 1986-05-13 General Dynamics Corporation/Convair Div. Deployable space truss beam
US4557097A (en) * 1983-09-08 1985-12-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Sequentially deployable maneuverable tetrahedral beam
DE3414220C1 (de) * 1984-04-14 1985-10-10 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln Mastartige,raeumliche Fachwerkstruktur
JPS60233249A (ja) * 1984-05-07 1985-11-19 小野田　淳次郎 展開トラス
US4677803A (en) * 1986-02-20 1987-07-07 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Deployable geodesic truss structure
US5167100A (en) * 1986-06-12 1992-12-01 Anandasivam Krishnapillai Deployable structures
US5016418A (en) * 1986-08-22 1991-05-21 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Synchronously deployable double fold beam and planar truss structure
US4958474A (en) * 1987-05-18 1990-09-25 Astro Aerospace Corporation Truss structure
FR2671601B1 (fr) * 1991-01-11 1993-08-06 Guinaudeau Expl Ets Michel Structure deployable et repliable notamment pour la formation d'un stand.
US5819492A (en) * 1995-07-17 1998-10-13 Konicek; Richard R. Collapsible roof truss utilizing an opposed flange roof hinge
US5701713A (en) * 1996-03-29 1997-12-30 Silver; Daniel J. Adjustable truss
JPH10236398A (ja) * 1997-02-24 1998-09-08 Mitsubishi Electric Corp 展開構造物

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3771274A (en) * 1972-05-30 1973-11-13 Gen Dynamics Corp Expandable retractable structure
US4539786A (en) * 1983-03-03 1985-09-10 Ltv Aerospace And Defense Co. Biaxial scissors fold, post tensioned structure

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2005021882A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104018023A (zh) * 2014-05-06 2014-09-03 阜阳市光普照明科技有限公司 一种led封装用铜合金键合连接线的制备方法

Also Published As

Publication number Publication date
WO2005021882A1 (fr) 2005-03-10
US20090199503A1 (en) 2009-08-13
CN1875153A (zh) 2006-12-06
US20100058704A9 (en) 2010-03-11
EP1668198A4 (fr) 2009-03-04

Similar Documents

Publication Publication Date Title
US20100058704A9 (en) Deployable structures
US9376796B2 (en) Rapidly deployable structures based upon negative poisson's ratio (NPR) auxetic components
US10734941B2 (en) Compact, self-deploying structures and methods for deploying foldable, structural origami arrays using a compression column
US9676501B1 (en) Space solar array architecture for ultra-high power applications
US3771274A (en) Expandable retractable structure
US7059094B2 (en) Frame structure
ES2926318T3 (es) Concepto de estructura de satélite eficiente para lanzamientos individuales o de apilamiento múltiple
US7211722B1 (en) Structures including synchronously deployable frame members and methods of deploying the same
US6173726B1 (en) Erectable shelter including a collapsible truss
US8905357B1 (en) Thin membrane structure
US20190085552A1 (en) Mobile solar array and truss
US4604844A (en) Deployable M-braced truss structure
WO2005111343A1 (fr) Structure deployable
US20070145195A1 (en) Deployable array support structure
US20030182879A1 (en) Stiffener reinforced foldable member
EP0565629A4 (en) Collapsible canopy framework having captured scissor ends with non-compressive pivots
US20220181787A1 (en) Satellite antenna having pantographic trusses and associated methods
CA1148521A (fr) Chassis et volet articule escamotable
US20220321057A1 (en) Distributed flexible membrane backing systems, devices, and methods
US20220017241A1 (en) Deployable Supporting Frame, and Housing Structure Provided with Such Supporting Frame, in Particular for Aerospace Applications
US11732496B1 (en) Shelter and hub system
US20020157326A1 (en) Panel assembly for space applications, arranged to enable synchronizing the deployment of the panels
US12006686B2 (en) Framework and system of interconnected frameworks
WO1989007696A1 (fr) Charpentes repliables pour bannes sur pied
JP3979456B2 (ja) 展開型骨組み構造体の結束規制装置

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060315

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
A4 Supplementary search report drawn up and despatched

Effective date: 20090203

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100401