US20100058704A9 - Deployable structures - Google Patents

Deployable structures Download PDF

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Publication number
US20100058704A9
US20100058704A9 US10/570,910 US57091006A US2010058704A9 US 20100058704 A9 US20100058704 A9 US 20100058704A9 US 57091006 A US57091006 A US 57091006A US 2010058704 A9 US2010058704 A9 US 2010058704A9
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US
United States
Prior art keywords
deployable structure
deployable
members
hinge
elements
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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.)
Abandoned
Application number
US10/570,910
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English (en)
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US20090199503A1 (en
Inventor
Jat Yuen Richard Liew
Anandasivam 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
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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
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Assigned to NATIONAL UNIVERSITY OF SINGAPORE reassignment NATIONAL UNIVERSITY OF SINGAPORE NUNC PRO TUNC ASSIGNMENT (SEE DOCUMENT FOR DETAILS). Assignors: KRISHNAPILLAI, ANANDASIVAM, LIEW, JAT YUEN RICHARD
Publication of US20090199503A1 publication Critical patent/US20090199503A1/en
Publication of US20100058704A9 publication Critical patent/US20100058704A9/en
Abandoned legal-status Critical Current

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    • 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:
  • 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:
  • first and second hinge elements are connected to different ends of the central member
  • 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:
  • first hinge element is capable of being stabilized for facilitating stabilizing the deployable structure in a deployed state.
  • Each deployable structure may further comprise:
  • first and second hinge elements are connected to different ends of the central member
  • 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.
  • FIG. 1 is a schematic representation of a deployable structure according to an embodiment of the present invention
  • FIG. 2 is a schematic representation of the deployable structure of FIG. 1 when partially folded;
  • FIG. 3 a is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • FIG. 3 b is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • FIG. 4 a is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • FIG. 4 b is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • FIG. 4 c is a schematic representation of a plurality of connected deployable structures according to another embodiment of the present invention.
  • FIG. 5 is a schematic representation of the deployable structure FIG. 1 , showing an upper plane, a middle plane and a lower plane;
  • FIG. 6 is a schematic representation of a structural unit according to another embodiment of the present invention.
  • FIG. 7 is a schematic representation of a structural unit according to yet another embodiment of the present invention.
  • FIG. 8 is a schematic representation of a structural unit according to another embodiment of the present invention.
  • FIG. 9 is a schematic representation of a structural unit according to yet another embodiment of the present invention.
  • FIG. 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.
  • FIG. 1 A schematic representation of a deployable structure 100 in an example embodiment is shown in FIG. 1 .
  • 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
  • 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 structure 100 to be folded or deployed by attaching or detaching the end of the central element 130 from the upper hinge 108 . It should be appreciated that 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. Alternatively, 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.
  • 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 FIG. 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 FIG. 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 FIG. 10 .
  • FIG. 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 FIG. 3 a .
  • 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 FIG. 3 b.
  • 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 FIG. 4 a .
  • 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 .
  • a barrel vault configuration can be created by changing the lengths of the connecting cables 491 joining the lower elements 406 , as shown in FIG. 4 b.
  • FIG. 4 c 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.
  • FIGS. 4 b and 4 c 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 FIGS. 4 b and 4 c.
  • 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 .
  • FIGS. 6 to 10 Alternative embodiments of the deployable structure are shown in FIGS. 6 to 10 .
  • Vertical rods 620 may be attached to the middle hinges 612 of the deployable structure 600 to facilitate attachment of sheets of fabric material or to increase the depth of the structural unit, or for bracing and other purposes.
  • FIG. 7 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 FIG. 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 FIG. 9 .
  • the deployable structure 900 may also have additional cables connecting the middle hinges 912 (compare the cables 170 in FIG. 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.

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  • 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)
US10/570,910 2003-09-03 2006-03-03 Deployable structures Abandoned US20100058704A9 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US49984803P 2003-09-03 2003-09-03
SGPCT/SG05/21882 2004-09-03
PCT/SG2004/000281 WO2005021882A1 (fr) 2003-09-03 2004-09-03 Structures deployables

Related Parent Applications (1)

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

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US20090199503A1 US20090199503A1 (en) 2009-08-13
US20100058704A9 true US20100058704A9 (en) 2010-03-11

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120067529A1 (en) * 2010-07-16 2012-03-22 University Of South Florida Shape-shifting surfaces
US20120234508A1 (en) * 2010-07-16 2012-09-20 University Of South Florida Multistable shape-shifting surfaces
US20220112706A1 (en) * 2020-10-12 2022-04-14 Jacob Eisenberg Strata space frame

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* Cited by examiner, † Cited by third party
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WO2011128769A2 (fr) * 2010-04-16 2011-10-20 Rodrigo Graf Fernandez Structures pliables pour une construction
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
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
US9783978B1 (en) * 2016-08-01 2017-10-10 University Of South Florida Shape-morphing space frame apparatus using linear bistable elements

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US3771274A (en) * 1972-05-30 1973-11-13 Gen Dynamics Corp Expandable retractable structure
US4290244A (en) * 1976-07-13 1981-09-22 Zeigler Theodore Richard Collapsible self-supporting structures and panels and hub therefor
US4539786A (en) * 1983-03-03 1985-09-10 Ltv Aerospace And Defense Co. Biaxial scissors fold, post tensioned structure
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
US4574535A (en) * 1984-04-14 1986-03-11 Deutsche Forschungs- Und Versuchsanstalt Fur Luft- Und Raumfahrt E.V. Mast-type three-dimensional framework structure
US4587777A (en) * 1981-10-09 1986-05-13 General Dynamics Corporation/Convair Div. Deployable space truss beam
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
US4745725A (en) * 1984-05-07 1988-05-24 Japan Aircraft Mfg. Co., Ltd. Deployable truss structure
US4958474A (en) * 1987-05-18 1990-09-25 Astro Aerospace Corporation Truss structure
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
US5167100A (en) * 1986-06-12 1992-12-01 Anandasivam Krishnapillai Deployable structures
US5701713A (en) * 1996-03-29 1997-12-30 Silver; Daniel J. Adjustable truss
US5819492A (en) * 1995-07-17 1998-10-13 Konicek; Richard R. Collapsible roof truss utilizing an opposed flange roof hinge
US5931420A (en) * 1997-02-24 1999-08-03 Mitsubishi Denki Kabushiki Kaisha Deployable truss structure

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FR2671601B1 (fr) * 1991-01-11 1993-08-06 Guinaudeau Expl Ets Michel Structure deployable et repliable notamment pour la formation d'un stand.

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US3381923A (en) * 1965-12-27 1968-05-07 Fairchild Hiller Corp Deployable structure
US3771274A (en) * 1972-05-30 1973-11-13 Gen Dynamics Corp Expandable retractable 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
US4539786A (en) * 1983-03-03 1985-09-10 Ltv Aerospace And Defense Co. Biaxial scissors fold, post tensioned structure
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
US4574535A (en) * 1984-04-14 1986-03-11 Deutsche Forschungs- Und Versuchsanstalt Fur Luft- Und Raumfahrt E.V. Mast-type three-dimensional framework structure
US4745725A (en) * 1984-05-07 1988-05-24 Japan Aircraft Mfg. Co., Ltd. Deployable truss structure
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
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
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120067529A1 (en) * 2010-07-16 2012-03-22 University Of South Florida Shape-shifting surfaces
US20120234508A1 (en) * 2010-07-16 2012-09-20 University Of South Florida Multistable shape-shifting surfaces
US8402711B2 (en) * 2010-07-16 2013-03-26 University Of South Florida Multistable shape-shifting surfaces
US8424265B2 (en) * 2010-07-16 2013-04-23 University Of South Florida Shape-shifting surfaces
US20220112706A1 (en) * 2020-10-12 2022-04-14 Jacob Eisenberg Strata space frame
US11680398B2 (en) * 2020-10-12 2023-06-20 Jacob Eisenberg Strata space frame

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US20090199503A1 (en) 2009-08-13
WO2005021882A1 (fr) 2005-03-10
EP1668198A1 (fr) 2006-06-14
EP1668198A4 (fr) 2009-03-04
CN1875153A (zh) 2006-12-06

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Owner name: NATIONAL UNIVERSITY OF SINGAPORE, SINGAPORE

Free format text: NUNC PRO TUNC ASSIGNMENT;ASSIGNORS:LIEW, JAT YUEN RICHARD;KRISHNAPILLAI, ANANDASIVAM;REEL/FRAME:022298/0162

Effective date: 20080904

Owner name: NATIONAL UNIVERSITY OF SINGAPORE,SINGAPORE

Free format text: NUNC PRO TUNC ASSIGNMENT;ASSIGNORS:LIEW, JAT YUEN RICHARD;KRISHNAPILLAI, ANANDASIVAM;REEL/FRAME:022298/0162

Effective date: 20080904

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