US3848821A - Space-saving storage of flexible sheets - Google Patents

Space-saving storage of flexible sheets Download PDF

Info

Publication number
US3848821A
US3848821A US00283961A US28396172A US3848821A US 3848821 A US3848821 A US 3848821A US 00283961 A US00283961 A US 00283961A US 28396172 A US28396172 A US 28396172A US 3848821 A US3848821 A US 3848821A
Authority
US
United States
Prior art keywords
sheet
hub
major
set forth
extended position
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.)
Expired - Lifetime
Application number
US00283961A
Other languages
English (en)
Inventor
H Scheel
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.)
Individual
Original Assignee
Individual
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
Priority claimed from DE19712144034 external-priority patent/DE2144034C3/de
Application filed by Individual filed Critical Individual
Application granted granted Critical
Publication of US3848821A publication Critical patent/US3848821A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04H—BUILDINGS OR LIKE STRUCTURES FOR PARTICULAR PURPOSES; SWIMMING OR SPLASH BATHS OR POOLS; MASTS; FENCING; TENTS OR CANOPIES, IN GENERAL
    • E04H15/00—Tents or canopies, in general
    • E04H15/26—Centre-pole supported tents
    • 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
    • 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
    • B64G1/2229—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 deployment actuating mechanism
    • 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
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/407—Solar sailing
    • 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
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S135/00—Tent, canopy, umbrella, or cane
    • Y10S135/904—Separate storage means or housing for shelter
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S242/00—Winding, tensioning, or guiding
    • Y10S242/917—Accommodating special material or article, e.g. antenna
    • Y10S242/918—Web material, e.g. thermal insulation

Definitions

  • ABSTRACT A hub and deployable annular sheet folded and wrapped thereon, the folds including major fold lines lying in straight lines which are tangent to an imaginary cylinder located just inside of the hub, and the sheet material being additionally folded or pleated between the major fold lines in such a way that at each fold line only one thickness of the material is folded upon itself, and the sheet being deployable to extended position, and in some modifications held therein, by rib means lying along the major fold lines.
  • This invention relates to apparatus for storing and deploying a thin flexible sheet, particularly an annular or circular sheet of plastic or fabric material, by folding the sheet in a way resembling pleating while wrapping it against the outer surface of a cylinder or prism to which the sheet is fixed in the vicinity of its center.
  • Storage according to the present invention is useful for many purposes, for instance, to wrap and store tents, umbrellas, sails, sheet filter materials, reflecting radiators, etc., and this apparatus is especially useful for storing and deploying large arrays comprising solar cells mounted on a supporting sheet for use in connection with spacecraft power generation. Another use is to fold and store, and to automatically deploy heat shields, micrometeorite shields, or the like.
  • An essential characteristic of this type of storage is that the finally stored sheets must occupy only a very small spatial volume, and that when folded and wrapped, they must be protected from damage, especially environmental damage such as pressure, shock, vibration, or exposure to humidity or to other detrimental contact.
  • the present invention seeks to teach an optimum way to fold and wrap a sheet of material having a memory for its bend lines against the surface of a cylindrical hub which is fixed concentrically to the center of the sheet and has its axis normal to the surface of the sheet when deployed, regardless of which of the above practical applications the present invention is applied to. This is quite difficult to accomplish because plane sheets are only foldable along straight lines. As a result, the spiral type of wrapping as shown, for example, in FIG. 3 of US. Pat. No. 3,109,608, starting precisely at the center of the sheet is out of the question.
  • intermediate fold lines which bisect the angle between two adjacent major fold lines and extend out to the perimeter of the circular sheet, folding the sheet material in alternate directions so as to produce a pleating effect.
  • the number of times that the sheet material is pleated along minor fold lines can be increased, so long as folded sectors are all essentially the same width as measured parallel to the axis of the cylinder when the pleats are wound upon it.
  • Another object of the present invention is to provide a system for folding and wrapping a circular sheet about a cylinder while at the same time placing padding spacers between the adjacent pleat segments of the circular sheet when it is initially folded and as it is being wrapped upon the cylinder.
  • This is especially useful, for instance, where the present teaching is employed to provide a solar cell array so as to pad the individual solar cells and prevent breakage thereof during wrapping of the supporting circular sheet material onto the cylinder.
  • it is also useful to securely hold the array close to the cylindrical hub using releasable bindings and/or plastic band covers, so that the stored array cannot be prematurely displaced as a result of shocks, vibrations or accelerations.
  • Still another important object of the invention is to provide stiffening means to supplement the memory of the pleated sheet, such as spring-type ribs or even inflatable rib tubes which can be pressurized from within to cause them to extend outwardly of the array, these stiffening means being preferably attached to the sheet material at the major folds and being wrapped together with the sheet material around the storage cylinder.
  • Deployment of the sheet material can be easily permitted or effected, by releasing the bindings and/or plastic covers and using the spring tendency or inflation of the stiffening ribs to cause them to assume straight-line configurations so as to unwrap the sheet and deploy it in an approximately radial plane, thus resulting in de ployment to a stable configuration which can then be used as a tent, umbrella, sail, filter, radiator, etc.
  • This same type of circular planar configuration is also especially useful as a solar array in which solar cells are attached in a pattern to the sheet material, or in which the sheet material is deployed for use as a radiation or micrometeorite shield.
  • Active control of the rate of deployment can be achieved for example, by using strings which are fastened to the outer tips of the ribs and which can be spooled on or off of the reel means located at or inside of the hub, using brakes or motors. Refolding and wrapping of the sheet material, once deployed, can be achieved remotely by using the same motor to pull the strings back in towards the center of the hub and thereby wrap the sheet back into the stored position.
  • a force field acting radially from the center of the structure can be used to accomplish deployment.
  • the centrifugal force created by rotation of the hub and sheet may be used to deploy the sheet and maintain it in an extended condition with or without stiffener ribs, or in altemative configurations it may be possible to use electrostatic repulsion from an electrostatically charged hub to accomplish deployment of the sheet.
  • inflatable stiffener means built into the sheet or attached to it in such a way as to automatically stiffen it and urge it into deployment, for instance, using elongated flexible tubes which can be pressurized from within, perhaps using internally generated gas or foam material so that once deployed it will remain deployed.
  • the present structure and technique need not be limited to the storing and deployment of essentially planar sheets because, for example, parabolic sheet material structures can be stowed ina similar manner if the over-all sheet material is provided with small elastic intermediate segments of suitable area which would be attached to the major and to the intermediate or secondary fold lines. If this were done, the deployment processes and structures described above can be used to accomplish non-planar resulting structures, such as parabolic dish structures capable of use as high gain RF antenna reflectors.
  • the present technique and structures have certain advantages which exist whether the structure is used as a tent, umbrella, sail, filter, reflector, etc.
  • One very important advantage is that all sheet material folds are accomplished using only single folds where only single thicknesses of the material on opposite sides of the fold lines and contiguous thereto will lie against each other, as distinguished from several layers of material being first stacked together and then all folded about'a common bend, which latter type of folding tends to unduly stress and stretch the outer layers of the stacked material. Since all of the pleats are single pleats, tangling during deployment is avoided, and in fact almost impossible.
  • Another advantage of this type of structure is that whatever stiffening ribs are used, whether spring metal or pressurized tubes, etc., these can also be wrapped around the hub. When released, the stiffeners materially aid in the deployment of the structure into extended position with exceptional ease and rapidity.
  • the present sheet being supported at its center, can be stiffened by ribs which are relatively short in length so that when deployed, the sheet becomes exceptionally stable.
  • the stiffening means can be selected and shaped in cross-section so as to provide stiffening of the deployed sheet in any predetermined direction whereby the sheet is held substantially planar when deployed.
  • the sheet has a slight fish-bone pleating pattern when deployed, the pattern being attributable to the lines about which it was folded, and these lines give the sheet when deployed an attractive and interesting appearance.
  • the present invention has special advantages when applied to lightweight solar generator arrays for space vehicles, these advantages being especially apparent when compared with the usual roll-up array where single solar cells are mounted on large rectangular flexible sheets of plastic, usually called blankets.
  • the roll-up blanket can generally extend from the drum on which it is rolled only to a distance which is about five times its width, because beyond that length the blanket would have too low a degree of torsional stiffness.
  • the present novel structure is used to provide a solar array of circular shape, such an array has the following advantages over the conventional roll-up strip blanket array.
  • the outer dimensions of the circular array according to the present invention can be designed quite freely and without serious concern over the axial length of the cylindrical hub on which it is to be stored after folding, whereas a non-folded roll-up blanket array would require a long hub whose length would be determined by the diameter of the unrolled blanket.
  • the axial length of the drum on which the array is stored can be very important.
  • the present storage structure provides much less friction during deployment between the various solar cell components and/or the sheet on which they are mounted, since the pleats open about the bend lines which act as hinges and do not tend to scrape across the adjacent pleat.
  • the successful deployment of a circular array is more reliable, and once deployed in the array can be maintained deployed very reliably simply by centrifugal force in a spin stabilized unit.
  • the stiffening means can be used in the present structure than in the case of the rolled-up blanket array, thus, the bending stresses on the stiffening means can be less and they can be designed from lighterweight materials.
  • the power-to-weight ratio of the solar cell can accordingly be increased, and for the same reason the vibrational bending frequency of the present circular solar array will be much higher as compared to that of a roll-up array.
  • the array will provide less interference with the attitude control system of a spacecraft upon which it is mounted.
  • the deployed array is subject to balanced forces which extend, not in only a few directions, but in all directions from the center, whereby it is maintained exceptionally planar.
  • the pleats of the supporting sheet material between the folds are all strips of the same width, and thus all of the solar cell arrays can be mounted thereto using the same jigs.
  • Such constant-width strips can be fabricated at high production rates using individual seriesconnected thin film solar cells, which would provide for economic production of an array.
  • the cylindrical shape of the stowed array makes its incorporation as a part of a spacecraft especially easy since the stowed array will lie neatly beneath a cylindrical shroud or fairing of the launch rocket.
  • a number of storage hubs, each carrying its own solar array wrapped according to the present disclosure can be folded outwardly on lightweight structural arms from the spacecraft, and then each of theflindividual arrays deployed from this extended position.
  • FIG. 1 is a side view of a storage cylinder or hub upon which a circular sheet has been folded and wrapped;
  • FIG. 2 is a view similar to FIG. 1 but showing the sheet partially unwrapped from the cylinder;
  • FIG. 3 is an elevation view similar to FIGS. 1 and 2 but showing the circular sheet fully unwrapped and deployed in a plane normal to the axis A of the cylinder;
  • FIG. 4 is a partial view looking up along the axis of the storage cylinder and showing the circular sheet fully deployed;
  • FIG. 5 is a cross-sectional view taken along line 5-5 of FIG. 1;
  • FIG. 6 is a schematic partial sectional view taken along line 6-6 of FIG. 5 but showing the sheet somewhat expanded from its normal tightly wound stored position so as to make its folds visible;
  • FIGS. 7, 8, and 9 are related perspective views showing a somewhat modified embodiment of the invention in three different degrees of deployment, FIG. 7 showing the sheet in an early stage of deployment, FIG. 8 showing the sheet in an advanced state of deployment and FIG. 9 showing sheet fully deployed;
  • FIG. 10 shows a still further modified version of the invention including means for controlling the rate of deployment and for rewrapping the sheet around the cylinder.
  • FIG. 11 shows an enlarged cross-sectional view through a spring metal rib
  • FIG. 12 shows an enlarged cross-sectional view through an inflatable plastic rib.
  • FIGS. 1, 2 and 3 show a cylindrical hub 1 having an outer surface against which the sheet material 2 is stowed by folding and then wrapping it in the manner described.
  • FIG. 5 illustrates the fact that when the sheet is fully stowed, the outer diameter of the cylinder is only slightly enlarged because the sheet material lies flat against it. Thus, in stowed condition the sheet requires only a very little space.
  • the structure also includes a plurality of flexible rib members or stiffeners 4 each of which is attached to the storage cylinder 1 at its inner end and extends therefrom outwardly along a major fold 3a, 3b, 3c, of the sheet material 2. The sheet material is attached all along the length of its contact with each of the ribs 4.
  • FIG. 6 is a view of the wrapped-up sheet material which has been radially expanded to show how the sheet 2 is draped over the respective ribs 4 at major folds 3a, 3b, 3c, Between the major folds 3, there are located a number of intermediate and minor folds 5a, 5b, 5c, and 5d, and these four folds repeat between each of the major folds all the way around the pattern. Note that the folds 5a, 5b, and fold (down in FIGS. 2 and 3) toward the viewer in FIG. 4, whereas the folds 3 and 5d fold away from the viewer (up in FIGS. 2 and 3). There are intennediate folds 5a, and 5d and there are minor folds 5b and 50 which are located so that they intersect the intermediate folds.
  • the individual folds of the sheet may be interspersed with padding spacers P as shown in FIG. 6.
  • a plastic retaining band 7, FIG. 6, which can be held together at its ends in a suitable manner designated to tightly confine the folded and wrapped circular sheet to prevent damage thereto, and in the case of a space vehicle to hold the wrapped sheet and ribs tightly against all possible displacements.
  • FIG. 2 shows the circular sheet partially deployed.
  • H the axial height of the wrapping on the hub cylinder 1
  • this height is the same as the widths H of the strips between the fold lines as shown in FIG. 4.
  • the crosssectional shape of each rib 4 is arcuate so that it can be bent for wrapping around the cylinder, but so that when it is extended in a straight line it will have stiffness as required to hold the circular sheet material firmly deployed in a planar manner.
  • FIG. 3 shows the circular sheet 2 in elevation view completely deployed and supported by the arcuate stiffener ribs 4 which are mounted in the cylindrical hub 1.
  • FIG. 4 shows a view of the deployed circular sheet 2 as seen from above along the axis A of the cylinder 1, FIG. 3, thereby illustrating the extended ribs 4 as straight lines and attached to the circular sheet 2 at the major folds 3a, 3b, 3c, When the circular sheet is deployed, it lies substantially transversely at the upper end 1a of the circular hub just above the ribs 4.
  • the sub-folds 6a, 6b, 6c, and 6d correspond with the folds 5a, 5b, 5c, and 5d but are located between another pair of ribs 4.
  • the intermediate folds 5a and 6a bisect the angles 8 fonned between each pair of adjacent major folds 3 and are pleated in alternating directions with respect thereto.
  • a group of solar cells 9 are shown on the fabric between the ribs 4 and the minor fold 50 to show typical placement thereof.
  • the major folds 3a, 3b, 3c, and the ribs 4 attached thereat extend in directions which are tangent to the outer surface of the hub cylinder 1, this is not true. Actually, they are tangent to an imaginary circle C which is of slightly smaller radius r than the radius R of the outer surface of the hub 1, FIG. 4. The radius r of the imaginary circle C is selected with respect to the radius R of the hub 1 such that extensions of any two adjacent major bend lines 3 will intersect at a common point K which lies slightly outside the surface of the hub 1.
  • the ribs 4 and the major folds 3a, 3b, 3c lie at a certain angle alpha with respect to a radial line L passing through the center axis A of the cylinder 1 and the point of intersection of the ribs 4 and major fold lines 3 with the surface of the cylinder 1.
  • This angle varies, depending on how many major folds and ribs are employed around the periphery of the cylinder 1.
  • the angle alpha must be carefully selected in order to provide proper geometry to achieve correct storage and deployment of the assembly. For example, if four major folds are employed, the angle alpha should be about 52 (R/r equals 1.28). If six major folds are used, as shown in FIG. 4, then the angle is about 66 degrees, (R/r equals 1.10). For eight major folds, an angle of about 71 is proper (R/r equals 1.05).
  • FIGS. 7, 8 and 9 show a modification of the structure illustrated in FIG. 4, in which the number of pleats is increased between each pair of ribs 14 for the purpose of shortening the height H of the sheet 12 when it is wrapped upon the cylindrical hub 10.
  • the length of the hub is substantially covered in the same way as the hub 1 is covered by the sheet 2 in FIG. 1.
  • the diameter of the sheet 12 becomes larger and larger while the covered height H" of the cylinder, FIG. 8, remains constant until all subfolds 5b, 5c, and 5d are deployed, ie the deployment reaches the point K.
  • H" rapidly increases as can be seen by comparing the dimension H" in FIG. 8 with the dimension H in FIG. 9 in which the sheet material is fully deployed. Since the number of pleats has been increased as shown in FIG. 9, as compared with the number of pleats shown in FIG. 4, the dimension H is accordingly smaller than the dimension H in FIG. 4 assuming the same outside diameter of the deployed sheet material.
  • FIG. 10 illustrates a still further modification of the structure in which two things are changed.
  • the number of pleats has been still further increased to illustrate a different embodiment which would wrap on an even shorter length H of storage hub.
  • the second difference is that in FIG. 10 means has been added by which a controlled rate of deployment of the sheet material can be achieved, and by which the sheet material can be mechanically rewrapped into folded condition.
  • the hub is generally referred to by the reference character 20, and the sheet is referred to by the reference character 22.
  • the ribs are referred to by the character 24, and at the end of each of these ribs 24 there is attached a string 26 which extends from the tip of the rib in toward the central hub.
  • a drive means in the illustrated case a motor M capable of rotating a wind-up reel 28 attached to it and lying concentric with the cylinder 20 on which the fabric wraps.
  • a motor M capable of rotating a wind-up reel 28 attached to it and lying concentric with the cylinder 20 on which the fabric wraps.
  • Each of the strings 26 is wrapped onto the reel 28 and secured thereto, and it will therefore be seen that starting with the strings wound tightly on the reel and the sheet 22 folded and wrapped tightly on the storage cylinder 20, as the motor M is rotated clockwise the strings will be paid out from the reel, thereby allowing the ribs 24 to extend to their fully deployed positions at a controlled rate.
  • the motor can be reversed to drive the reel 28 counterclockwise, thereby pulling the strings tightly in toward the cylinder and returning the sheet material to wrapped condition. Since the sheet material is permanently creased at each of the major and minor folds and bends, it rolls up to its stored condition again quite readily.
  • the sheet material is a plastic fabric having sufficient memory to regain its folded position about the original creases when the ribs 24 to which it is attached are wound again onto the hub 20.
  • ribs instead of being C-shaped as shown in FIG. 11, are hollow plastic tubes 4a as shown in FIG. 12, which are inflated from within by gas pressure or by a foam substance to a sufficient pressure that the ribs 4a assume and retain linear deployment.
  • a force field operating substantially radially from the axis A of the cylinder, for instance, an electrostatic force or the centrifugal force caused by rotation of the entire assembly.
  • Apparatus for storing on a hub an annular sheet in folded condition and for deploying it into extended position comprising:
  • the sheet having multiple predetermined sharplydefined bend lines about which the sheet is pleated by folding the sheet in one axial direction at multiple major bend lines uniformly spaced about the sheet and then folding the sheet oppositely at intermediate bend lines bisecting the angle between adjacent major bend lines, the folds being made in such a way that at each bend line only the sheet material contiguous thereto is folded upon itself, said major bend lines each extending from the hub as a substantially straight line which is tangent to an imaginary coaxial cylinder located within the hub and of slightly smaller diameter and selected such that extensions of adjacent major bend lines would intersect at common points lying near the surface of the hub; and
  • flexible tube means comprising stiffening rib means fixed to the sheet along each major bend line and each rib means being attached to the hub where the bend line intersects it, the tube means being inflatable to stiffen them and deploy the sheet into extended position.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Tents Or Canopies (AREA)
  • Photovoltaic Devices (AREA)
US00283961A 1971-08-30 1972-08-28 Space-saving storage of flexible sheets Expired - Lifetime US3848821A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19712144034 DE2144034C3 (de) 1971-08-30 Zusammenfalten eines Flächengebildes zu raumsparendem Wickel

Publications (1)

Publication Number Publication Date
US3848821A true US3848821A (en) 1974-11-19

Family

ID=5818511

Family Applications (1)

Application Number Title Priority Date Filing Date
US00283961A Expired - Lifetime US3848821A (en) 1971-08-30 1972-08-28 Space-saving storage of flexible sheets

Country Status (2)

Country Link
US (1) US3848821A (enExample)
FR (1) FR2186944A5 (enExample)

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1991008949A3 (en) * 1989-12-08 1991-08-22 Cambridge Consultants Furlable sheet structures and methods of furling
US5795284A (en) * 1994-11-15 1998-08-18 Trw Occupant Restraint Systems Gmbh Method of and device for folding a gas bag of a vehicle occupant restraint system
US5800328A (en) * 1994-11-15 1998-09-01 Trw Occupant Restraint Systems Gmbh Method of and device for folding a gas bag of a vehicle occupant restraint system
FR2836451A1 (fr) * 2002-02-22 2003-08-29 Centre Nat Etd Spatiales Structure deployable pour satellite artificiel
US20040012865A1 (en) * 2000-09-07 2004-01-22 Shangli Huang Spin-stabilized film mirror and its application in space
US8356774B1 (en) * 2008-04-21 2013-01-22 The United States Of America As Represented By The Secretary Of The Air Force Structure for storing and unfurling a flexible material
US20150021440A1 (en) * 2009-12-16 2015-01-22 Daniel W. Allen Debris management system and method of operation thereof
US20150140253A1 (en) * 2013-11-20 2015-05-21 Brigham Young University Rigidly foldable array of three-dimensional bodies
US20160376037A1 (en) 2014-05-14 2016-12-29 California Institute Of Technology Large-Scale Space-Based Solar Power Station: Packaging, Deployment and Stabilization of Lightweight Structures
US9555904B2 (en) 2012-08-09 2017-01-31 Analytical Mechanics Associates, Inc. Gossamer apparatus and systems for use with spacecraft
US9742348B2 (en) 2013-09-16 2017-08-22 Brigham Young University Foldable array of three-dimensional panels including functional electrical components
GB2555656A (en) * 2016-11-08 2018-05-09 Oxford Space Systems Deployable wrapped rib assembly
US10189583B2 (en) * 2015-05-13 2019-01-29 Analytical Mechanics Associates, Inc. Deployable sheet material systems and methods
US10232696B1 (en) * 2018-03-10 2019-03-19 Carwig Llc Automatic vehicle sunshade system
CN110065652A (zh) * 2019-03-29 2019-07-30 上海卫星工程研究所 航天器用平面收纳比折叠及充气展开结构的折叠方法
US10454565B2 (en) 2015-08-10 2019-10-22 California Institute Of Technology Systems and methods for performing shape estimation using sun sensors in large-scale space-based solar power stations
CN110723314A (zh) * 2019-10-12 2020-01-24 上海宇航系统工程研究所 一种空间薄膜结构展开机构
US10654350B1 (en) 2018-03-10 2020-05-19 Carwig Llc Automatic vehicle sunshade system
US10696428B2 (en) 2015-07-22 2020-06-30 California Institute Of Technology Large-area structures for compact packaging
WO2020150735A1 (en) * 2019-01-18 2020-07-23 M.M.A. Design, LLC Deployable system with flexible membrane
US10738498B2 (en) 2016-11-08 2020-08-11 Oxford Space Systems Ltd Deployable mast structure
US10992253B2 (en) 2015-08-10 2021-04-27 California Institute Of Technology Compactable power generation arrays
EP3706245A4 (en) * 2017-10-30 2021-06-23 Institute for Q-shu Pioneers of Space, Inc. REFLECTOR, DEVELOPED ANTENNA AND SPACE VEHICLE
US11066843B2 (en) * 2019-04-26 2021-07-20 Radio Flyer Inc. Canopy assembly
US11128179B2 (en) 2014-05-14 2021-09-21 California Institute Of Technology Large-scale space-based solar power station: power transmission using steerable beams
US11223139B2 (en) 2016-06-21 2022-01-11 Institute For Q-Shu Pioneers Of Space, Inc. Expandable antenna
US20220041302A1 (en) * 2020-04-22 2022-02-10 Timothy N. Sippel Gyromesh solar sail spacecraft and sail panel assemblies
US11362228B2 (en) 2014-06-02 2022-06-14 California Institute Of Technology Large-scale space-based solar power station: efficient power generation tiles
GB2610222A (en) * 2021-08-27 2023-03-01 Space Forge Ltd Spacecraft heat shield
US11634240B2 (en) 2018-07-17 2023-04-25 California Institute Of Technology Coilable thin-walled longerons and coilable structures implementing longerons and methods for their manufacture and coiling
US20230220940A1 (en) * 2022-01-07 2023-07-13 Inventions, Plus LLC Disk with adjustable outer diameter
US11772826B2 (en) 2018-10-31 2023-10-03 California Institute Of Technology Actively controlled spacecraft deployment mechanism
US12021162B2 (en) 2014-06-02 2024-06-25 California Institute Of Technology Ultralight photovoltaic power generation tiles
US12235082B1 (en) * 2023-09-01 2025-02-25 United States Of America As Represented By The Secretary Of The Air Force Deployable origami structure

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU188471U1 (ru) * 2018-11-12 2019-04-15 Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева - КАИ" (КНИТУ-КАИ) Трансформируемый каркас
RU187288U1 (ru) * 2018-11-12 2019-02-28 Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева - КАИ" (КНИТУ-КАИ) Трансформируемый каркас

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942794A (en) * 1957-03-04 1960-06-28 Maurice A Huso Sheet reel
US3010372A (en) * 1960-02-11 1961-11-28 Wade E Lanford Folding apparatus

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942794A (en) * 1957-03-04 1960-06-28 Maurice A Huso Sheet reel
US3010372A (en) * 1960-02-11 1961-11-28 Wade E Lanford Folding apparatus

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1991008949A3 (en) * 1989-12-08 1991-08-22 Cambridge Consultants Furlable sheet structures and methods of furling
US5795284A (en) * 1994-11-15 1998-08-18 Trw Occupant Restraint Systems Gmbh Method of and device for folding a gas bag of a vehicle occupant restraint system
US5800328A (en) * 1994-11-15 1998-09-01 Trw Occupant Restraint Systems Gmbh Method of and device for folding a gas bag of a vehicle occupant restraint system
US20040012865A1 (en) * 2000-09-07 2004-01-22 Shangli Huang Spin-stabilized film mirror and its application in space
FR2836451A1 (fr) * 2002-02-22 2003-08-29 Centre Nat Etd Spatiales Structure deployable pour satellite artificiel
US8356774B1 (en) * 2008-04-21 2013-01-22 The United States Of America As Represented By The Secretary Of The Air Force Structure for storing and unfurling a flexible material
US20150021440A1 (en) * 2009-12-16 2015-01-22 Daniel W. Allen Debris management system and method of operation thereof
US9731844B2 (en) * 2009-12-16 2017-08-15 Daniel W. Allen Debris management system and method of operation thereof
US9555904B2 (en) 2012-08-09 2017-01-31 Analytical Mechanics Associates, Inc. Gossamer apparatus and systems for use with spacecraft
US9742348B2 (en) 2013-09-16 2017-08-22 Brigham Young University Foldable array of three-dimensional panels including functional electrical components
US9512618B2 (en) * 2013-11-20 2016-12-06 Brigham Young University Rigidly foldable array of three-dimensional bodies
US20150140253A1 (en) * 2013-11-20 2015-05-21 Brigham Young University Rigidly foldable array of three-dimensional bodies
US11128179B2 (en) 2014-05-14 2021-09-21 California Institute Of Technology Large-scale space-based solar power station: power transmission using steerable beams
US20160376037A1 (en) 2014-05-14 2016-12-29 California Institute Of Technology Large-Scale Space-Based Solar Power Station: Packaging, Deployment and Stabilization of Lightweight Structures
US10144533B2 (en) 2014-05-14 2018-12-04 California Institute Of Technology Large-scale space-based solar power station: multi-scale modular space power
US10340698B2 (en) 2014-05-14 2019-07-02 California Institute Of Technology Large-scale space-based solar power station: packaging, deployment and stabilization of lightweight structures
US11362228B2 (en) 2014-06-02 2022-06-14 California Institute Of Technology Large-scale space-based solar power station: efficient power generation tiles
US12021162B2 (en) 2014-06-02 2024-06-25 California Institute Of Technology Ultralight photovoltaic power generation tiles
US10815012B2 (en) * 2015-05-13 2020-10-27 Analytical Mechanics Associates, Inc. Deployable sheet material systems and methods
US10189583B2 (en) * 2015-05-13 2019-01-29 Analytical Mechanics Associates, Inc. Deployable sheet material systems and methods
US20190263540A1 (en) * 2015-05-13 2019-08-29 Analytical Mechanics Associates, Inc. Deployable sheet material systems and methods
US10696428B2 (en) 2015-07-22 2020-06-30 California Institute Of Technology Large-area structures for compact packaging
US10992253B2 (en) 2015-08-10 2021-04-27 California Institute Of Technology Compactable power generation arrays
US10454565B2 (en) 2015-08-10 2019-10-22 California Institute Of Technology Systems and methods for performing shape estimation using sun sensors in large-scale space-based solar power stations
US10749593B2 (en) 2015-08-10 2020-08-18 California Institute Of Technology Systems and methods for controlling supply voltages of stacked power amplifiers
US11223139B2 (en) 2016-06-21 2022-01-11 Institute For Q-Shu Pioneers Of Space, Inc. Expandable antenna
WO2018087541A1 (en) * 2016-11-08 2018-05-17 Oxford Space Systems Deployable wrapped rib assembly
US10738498B2 (en) 2016-11-08 2020-08-11 Oxford Space Systems Ltd Deployable mast structure
CN110313106A (zh) * 2016-11-08 2019-10-08 牛津空间系统有限公司 可展开缠绕肋组件
GB2555656A (en) * 2016-11-08 2018-05-09 Oxford Space Systems Deployable wrapped rib assembly
US11381001B2 (en) 2017-10-30 2022-07-05 Institute For Q-Shu Pioneers Of Space, Inc. Reflector, deployable antenna, and spacecraft
EP3706245A4 (en) * 2017-10-30 2021-06-23 Institute for Q-shu Pioneers of Space, Inc. REFLECTOR, DEVELOPED ANTENNA AND SPACE VEHICLE
US10654350B1 (en) 2018-03-10 2020-05-19 Carwig Llc Automatic vehicle sunshade system
US10232696B1 (en) * 2018-03-10 2019-03-19 Carwig Llc Automatic vehicle sunshade system
US11634240B2 (en) 2018-07-17 2023-04-25 California Institute Of Technology Coilable thin-walled longerons and coilable structures implementing longerons and methods for their manufacture and coiling
US11772826B2 (en) 2018-10-31 2023-10-03 California Institute Of Technology Actively controlled spacecraft deployment mechanism
US11724828B2 (en) 2019-01-18 2023-08-15 M.M.A. Design, LLC Deployable system with flexible membrane
WO2020150735A1 (en) * 2019-01-18 2020-07-23 M.M.A. Design, LLC Deployable system with flexible membrane
US12227310B2 (en) 2019-01-18 2025-02-18 M.M.A. Design, LLC Deployable system with flexible membrane
CN110065652A (zh) * 2019-03-29 2019-07-30 上海卫星工程研究所 航天器用平面收纳比折叠及充气展开结构的折叠方法
US11066843B2 (en) * 2019-04-26 2021-07-20 Radio Flyer Inc. Canopy assembly
CN110723314A (zh) * 2019-10-12 2020-01-24 上海宇航系统工程研究所 一种空间薄膜结构展开机构
US11958637B2 (en) * 2020-04-22 2024-04-16 Geoshade Corporal Gyromesh solar sail spacecraft and sail panel assemblies
US20220041302A1 (en) * 2020-04-22 2022-02-10 Timothy N. Sippel Gyromesh solar sail spacecraft and sail panel assemblies
GB2610222B (en) * 2021-08-27 2024-04-24 Space Forge Ltd Spacecraft heat shield
GB2610222A (en) * 2021-08-27 2023-03-01 Space Forge Ltd Spacecraft heat shield
US20240270412A1 (en) * 2021-08-27 2024-08-15 Space Forge Limited Spacecraft Heat Shield
US12208928B2 (en) * 2021-08-27 2025-01-28 Space Forge Limited Spacecraft heat shield
US20230220940A1 (en) * 2022-01-07 2023-07-13 Inventions, Plus LLC Disk with adjustable outer diameter
US12235082B1 (en) * 2023-09-01 2025-02-25 United States Of America As Represented By The Secretary Of The Air Force Deployable origami structure
US20250076006A1 (en) * 2023-09-01 2025-03-06 Government Of The United States, As Represented By The Secretary Of The Air Force Deployable Origami Structure

Also Published As

Publication number Publication date
FR2186944A5 (enExample) 1974-01-11
DE2144034B2 (de) 1975-06-05
DE2144034A1 (de) 1973-03-08

Similar Documents

Publication Publication Date Title
US3848821A (en) Space-saving storage of flexible sheets
US6904722B2 (en) Elongated truss boom structures for space applications
US3863870A (en) Spin stabilized vehicle and solar cell arrangement therefor
US3510086A (en) Outrigger for space missiles
JP2001036334A (ja) 反射性メッシュのパッキング方法、懸垂線装置及び周辺トラス反射鏡の配置補助装置
JP6668009B2 (ja) 展開可能構造用の収納可能テープばねの内蔵方法およびテープばね展開可能構造
JP3541225B2 (ja) 大型膜宇宙構造物およびその展開方法
US3541569A (en) Expandable parabolic reflector
US9755318B2 (en) Mesh reflector with truss structure
CA1297858C (en) Self erecting solar panel complex deployment system
US7595769B2 (en) Arbitrarily shaped deployable mesh reflectors
JP6669445B2 (ja) テープばね展開可能構造
US3606211A (en) Outrigger construction
US20190131714A1 (en) Deployable antenna reflector
WO2015130505A1 (en) Mesh reflector with truss structure
EP3598576B1 (en) Reflecting systems, such as reflector antenna systems, with tension-stabilized reflector positional apparatus
US3450372A (en) Self-projectable element for a space vehicle
JP2017100714A (ja) 太陽光発電装置の組を含む展開可能構造物、そのような展開可能構造物を展開するシステム、およびそのようなシステムを含む人工衛星
JP2004314944A (ja) 宇宙船搭載用展開構造体の折畳連結構造
US3809337A (en) Spin stabilized vehicle and solar cell arrangement therefor
CN111323987A (zh) 一种空间可展开遮光结构
Kadonishi et al. Compact packaging of planar gossamer space structures using textile membranes
US3495250A (en) Expandable cavity-backed spiral antenna
CN108482859B (zh) 火箭的包装方法、包装箱段的制备方法和包装箱段
US3722840A (en) Spin stabilized vehicle and solar cell arrangement therefor