WO2001071126A1 - Structure de couverture deployable et procede de deploiement associe - Google Patents

Structure de couverture deployable et procede de deploiement associe Download PDF

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Publication number
WO2001071126A1
WO2001071126A1 PCT/US2000/007706 US0007706W WO0171126A1 WO 2001071126 A1 WO2001071126 A1 WO 2001071126A1 US 0007706 W US0007706 W US 0007706W WO 0171126 A1 WO0171126 A1 WO 0171126A1
Authority
WO
WIPO (PCT)
Prior art keywords
shell
assembly
frame
frame assembly
deployable
Prior art date
Application number
PCT/US2000/007706
Other languages
English (en)
Inventor
David P. Cadogan
Original Assignee
Ilc Dover, Inc.
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 Ilc Dover, Inc. filed Critical Ilc Dover, Inc.
Priority to AU2000263338A priority Critical patent/AU2000263338A1/en
Priority to PCT/US2000/007706 priority patent/WO2001071126A1/fr
Priority to US09/937,763 priority patent/US6735920B1/en
Publication of WO2001071126A1 publication Critical patent/WO2001071126A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G99/00—Subject matter not provided for in other groups of this subclass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
    • B64G1/2222—Folding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
    • B64G1/2227—Inflating
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/08—Means for collapsing antennas or parts thereof
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/12—Supports; Mounting means
    • H01Q1/1235—Collapsible supports; Means for erecting a rigid antenna
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/12—Supports; Mounting means
    • H01Q1/1242—Rigid masts specially adapted for supporting an aerial
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas

Definitions

  • This invention relates generally to a method and an apparatus capable of deploying and
  • a lightweight space structure such as a solar array, reflector, sunshield,
  • the invention relates more specifically to a method and
  • Inflatable structures offer many benefits over conventional deployable structures
  • inflatable tubular structures weigh less than deployable truss structures
  • inflatable tubular structures is not insignificant.
  • apparatus weight which is less than that of conventional inflatable deployment structures.
  • present invention to provide a method and an apparatus capable of facilitating the deployment
  • the present invention is directed to a deployable space frame comprising a
  • the present invention is also directed to a method of packaging and deploying the space
  • the method comprises (a) collapsing the frame assembly by packaging the shell to provide
  • the packaged frame assembly/shell by employing the shell inflator to inflate the shell while
  • the space frame requires substantially less material to construct
  • the present invention therefore, provides a lightweight means for both deploying
  • the invention comprises a lighter-weight system
  • the invention also more generally provides for the deployment of any lightweight
  • FIG. 1 is a partial perspective view of a space frame according to a first preferred
  • FIG. 2 is a cross-sectional view of the shell and the frame assembly depicted in FIG. 1.
  • FIG. 3 is a cross-sectional view of the shell and the frame assembly according to a second
  • FIG. 4 is a cross-sectional view of the shell and the frame assembly according to a third
  • the deployable space frame is an ultra-lightweight structural member that is simple to
  • the space frame comprises a truss beam that comprises a series of connected box frames, or bays,
  • the deployable space frame requires substantially less material to accomplish the same
  • the deployed beam becomes a rigid structural member that does not
  • a deployable space frame 100 constructed in accordance with
  • the space frame 100 comprises a packageable. deployable. and rigidizable frame
  • assembly 110 having an assembly base end and an assembly tip end; a packageable. deployable.
  • Frame assembly 110 comprises a plurality of connected thin- walled rigidizable composite
  • struts which define a series of connected box frames, or bays, and has a polygonal cross-sectional
  • frame assembly 1 10 comprises
  • first, second, and third longerons 111 extending from the assembly base end to the assembly tip
  • Struts 111 and 112 can comprise various materials of construction and various shapes
  • the struts are thin-
  • the means for attaching the frame assembly shell to the frame assembly serves to connect
  • means for attaching the frame assembly shell to the frame assembly include tabs that are affixed
  • the tabs can be attached by means
  • the space frame properties are derived through the use of finite element beam modeling.
  • a geometrical configuration is determined such that the capacity
  • the space frame is approximately equal to the required compressive force.
  • the required compressive force for example, in one
  • struts having a wall thickness of from 50 to 75 m, and a diameter of from
  • the frame assembly cross-sectional dimensions are such that the frame assembly
  • cross section is capable of being inscribed within a 20.5 cm diameter circle.
  • Shell 120 is used for deployment, governs the deployed structure's straightness. and can
  • the shell also provides the
  • the shell supports the loads from inflation and transfers those loads into the
  • rigidizable space frame assembly to tension the members prior to rigidization.
  • the strength of the space frame during deployment is derived from the inflatable shell.
  • the inflatable shell governs the cross-sectional moment of inertia of the frame
  • shell 120 comprises a polyimide film having a thickness of 12
  • the shell inflator comprises a pressure-regulated gas source, such as nitrogen gas or a gas
  • a deployable space frame 200 constructed in accordance with a
  • frame assembly 210 comprises a plurality of connected thin- walled composite struts
  • first, second, third, and fourth longerons 211 extending from the assembly base
  • aforementioned shell having a substantially circular cross-sectional shape, but also includes all
  • a deployable space frame 300 constructed in
  • triangular cross-sectional strut configuration as the embodiment depicted in FIG.2. but includes a shell 320 having a lobed cross-sectional shape. Additionally, even though the lobed cross-
  • FIG. 3 rectangular cross-sectional strut configuration depicted in FIG. 3 (i.e.. a shell having a lobe
  • a lobed cross-sectional shape can be employed in which the number of lobes is equal to the number of sides of the polygon.
  • the method of packaging and deploying a space frame 100. 200, or 300 (referred to
  • frame assembly 110 is collapsed from the assembly tip end to the assembly
  • the packaging step is accomplished by rolling
  • the frame assembly-containing shell from the shell tip end to the shell base end.
  • the frame assembly-containing shell could be folded from the shell
  • frame assembly 1 10 and shell 120 are controllably deployed from the
  • the method of packing the space frame minimizes volume and ensures deployment
  • the packing method is also low in mass, utilizes flight proven technology, and
  • inflation system can take several forms, a preferred embodiment is bottled N 2
  • valves that are actuated by computer or by human intervention, such
  • Redundant valves and pressure sensing transducers are employed in the
  • the shell is fitted with relief valves to prevent over-pressurization.
  • operation of the space frame depends on maintaining the stiffness of the inflatable shell while the
  • stowed shell and produces the smoothest deployment comprises the rolled inflatable shell with a means for imparting resistance to deployment, i.e.. a means for controlling the rate of unrolling
  • the adhesive can be used to control
  • peel strength of this adhesive is constant over a wide temperature range about the predicted
  • the adhesive comprises high molecular weight compounds having high
  • hook-and-loop fasteners embedded in the exterior wall of the shell can be used to control
  • the shell is then flattened and rolled about the 9 to 3 o'clock axis.
  • inflation gas is introduced, the shell
  • means can be, for example, a frictional device or a ratchet mechanism, such as a means for
  • assembly struts to be collapsible for packaging, and then deployable to shape when the shell is
  • the struts therefore, comprise a thermoplastic shape memory composite material.
  • thermoplastic shape memory composite will return to its manufactured “set” shape when heated
  • transition temperature will then cause the material to become rigid. This allows the struts to be
  • the struts comprise thermoplastic composite laminate material
  • the packaged frame assembly is deployed and rigidized. First, the packaged frame assembly is preheated either by the
  • the packaged frame assembly would have good conduction paths and would be
  • the composite material above its second order transition temperature and provide it with some
  • MLF' melting insulation
  • the composite material * s cooling rate is dictated by the insulating capability of the shell
  • the insulation could be in the form of
  • NDA vapor deposited aluminum
  • the MLI cover also controls the fluctuations in the temperature of the
  • thermoplastic and ultraviolet curable (thermoset) materials have been used.
  • thermoplastic materials include the low coefficient of thermal
  • thermoplastic materials are possible as matrix resins for use in composite struts.
  • thermoset material is a modified thermoset that mimics a thermoplastic. Its properties include ease of
  • the resin can be applied to various reinforcements such as graphite, "KEVLAR," glass
  • poly(p-phenylene-2.6-benzobisoxazole)("PBO”) which is a rigid-rod
  • Hybrid weaves may also be a potential method of improving the reinforcement's capability while still retaining all of the
  • the present invention therefore, by making possible the use of a variety of lightweight
  • the space frame minimizes the space
  • the space frame is covered with MLI locally
  • the area over the roll may also be covered with a high alpha/epsilon material,
  • the space frame provides tolerance to increasingly hostile environments, in
  • the frame assembly is provided by the resiliency of the rigidizable materials and the protective
  • the space frame minimizes stowage volume and accommodates stowage in
  • the space frame can be tailored to meet the structural requirements of a
  • structural characteristics include, for example, tapering the shell diameter from base to tip;
  • the material fiber type, fiber orientation, resin type
  • thickness of the structural members and
  • FIG.3 rectangular (FIG.3) cross-sectional configuration
  • another embodiment could comprise any other
  • frame comprises a plurality of packageable, deployable. and rigidizable frame assemblies, each of
  • the assemblies having an assembly first end and an assembly second end; a plurality of
  • each of the shells disposed around each of the corresponding frame
  • each of the shells having a shell first end and a shell second end; means for

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

Cette structure de couverture (100) peut faciliter le déploiement, et le support ultérieur, d'une structure spatiale (100), et elle comprend un ensemble cadre (110) pouvant être emballé, déployé et rigidifié, une enveloppe d'ensemble cadre (120) pouvant être emballée, déployée, gonflée, et que l'on a placée autour de l'ensemble cadre (110); des moyens de fixation de l'enveloppe (120) sur l'ensemble cadre (110), ainsi qu'un gonfleur d'enveloppe. Le procédé d'emballage et de déploiement de la structure de couverture (100) comprend les étapes suivantes consistant: (a) à replier l'ensemble cadre (110) en emballant l'enveloppe (120), de manière à obtenir un ensemble cadre/enveloppe emballé; (b) à déployer de manière commandée l'ensemble cadre (110) et l'enveloppe (120) à partir de l'ensemble cadre/enveloppe emballé, en utilisant le gonfleur de manière à gonfler l'enveloppe (120) tout en dotant l'enveloppe (120) d'une certaine résistance au déploiement, de façon que la pression gazeuse intérieure requise pour continuer le déploiement de l'enveloppe soit suffisante pour totalement gonfler la portion de l'enveloppe (120) dans laquelle le gaz a été introduit; (c) à continuer à résister au déploiement jusqu'à ce que l'ensemble cadre (110) et l'enveloppe (120) soient déployés; (d) à cesser d'introduire du gaz dans l'enveloppe (120); (e) à rigidifier l'ensemble cadre (110) et (f) à mettre en dépression l'enveloppe (120).
PCT/US2000/007706 2000-03-23 2000-03-23 Structure de couverture deployable et procede de deploiement associe WO2001071126A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
AU2000263338A AU2000263338A1 (en) 2000-03-23 2000-03-23 Deployable space frame and method of deployment therefor
PCT/US2000/007706 WO2001071126A1 (fr) 2000-03-23 2000-03-23 Structure de couverture deployable et procede de deploiement associe
US09/937,763 US6735920B1 (en) 2000-03-23 2000-03-23 Deployable space frame and method of deployment therefor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2000/007706 WO2001071126A1 (fr) 2000-03-23 2000-03-23 Structure de couverture deployable et procede de deploiement associe

Publications (1)

Publication Number Publication Date
WO2001071126A1 true WO2001071126A1 (fr) 2001-09-27

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Country Status (2)

Country Link
AU (1) AU2000263338A1 (fr)
WO (1) WO2001071126A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102437404A (zh) * 2011-08-18 2012-05-02 哈尔滨工业大学 一种可刚化充气展开桁架式平面天线与太阳帆板一体机构
CN105406165A (zh) * 2015-12-23 2016-03-16 哈尔滨工业大学 一种伸缩式雷达天线背架
CN106184697A (zh) * 2016-09-14 2016-12-07 北京航空航天大学 一种直线贯穿构架式复合材料机身结构
CN106697336A (zh) * 2016-12-07 2017-05-24 上海宇航***工程研究所 一种多板压紧释放***
CN109100863A (zh) * 2018-06-15 2018-12-28 上海卫星工程研究所 一种实现六棱柱状遮光罩折叠收缩的设计方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5630296A (en) * 1994-08-25 1997-05-20 Kendall, Jr.; Robert T. Inflatable emergency shelter
US5706846A (en) * 1995-09-27 1998-01-13 United Defense, L.P. Protective action system including a deployable system

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5630296A (en) * 1994-08-25 1997-05-20 Kendall, Jr.; Robert T. Inflatable emergency shelter
US5706846A (en) * 1995-09-27 1998-01-13 United Defense, L.P. Protective action system including a deployable system

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102437404A (zh) * 2011-08-18 2012-05-02 哈尔滨工业大学 一种可刚化充气展开桁架式平面天线与太阳帆板一体机构
CN105406165A (zh) * 2015-12-23 2016-03-16 哈尔滨工业大学 一种伸缩式雷达天线背架
CN105406165B (zh) * 2015-12-23 2018-04-03 哈尔滨工业大学 一种伸缩式雷达天线背架
CN106184697A (zh) * 2016-09-14 2016-12-07 北京航空航天大学 一种直线贯穿构架式复合材料机身结构
CN106697336A (zh) * 2016-12-07 2017-05-24 上海宇航***工程研究所 一种多板压紧释放***
CN109100863A (zh) * 2018-06-15 2018-12-28 上海卫星工程研究所 一种实现六棱柱状遮光罩折叠收缩的设计方法
CN109100863B (zh) * 2018-06-15 2020-08-25 上海卫星工程研究所 一种实现六棱柱状遮光罩折叠收缩的设计方法

Also Published As

Publication number Publication date
AU2000263338A1 (en) 2001-10-03

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