• 专利附录
  • 专利说明
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    • 专利摘要:
    In a method for packaging and unpacking a spacecraft membrane (1) which has, in an extension plane, a longitudinal axis between opposite longitudinal corners (4) and a transverse axis extending transversely to the longitudinal axis and through transverse wedges, to form a spacecraft membrane package, two packaging steps are performed: in a first packaging step, the spacecraft membrane (1) is wrapped along the transverse axis for forming a transverse package (9). In a second packaging step, the transverse package (9) is wrapped along the longitudinal axis to form a longitudinal package. The package of the spacecraft membrane (1) in the first packaging step comprises a package of the material of the spacecraft membrane (1) from each side, or from both sides of the longitudinal axis. In this case, in the first packaging step, the spacecraft membrane (1) is packaged so that in the transverse product packaging (9), the transverse wedges are freely accessible. In the second packaging step, the transverse packaging (9) is packaged so that in the longitudinal product packaging, the longitudinal corners (4) are freely accessible. The longitudinal packaging is unpacked by pulling on the longitudinal corners (4). Then, the transverse packaging (9) is unpacked by pulling on the transverse corners.
    公开号:FR3062114A1
    申请号:FR1850442
    申请日:2018-01-19
    公开日:2018-07-27
    发明作者:Siebo Reershemius；Peter Spietz
    申请人:Deutsches Zentrum fuer Luft und Raumfahrt eV；
    IPC主号:
    专利说明:

    Holder (s): DEUTSCHES ZENTRUM FUR LUFTUND RAUMFAHRT E.V ..
    O Extension request (s):
    Agent (s): trusted.
    IPSILON Société par actions simpli® PROCESS FOR PACKING AND UNPACKING A SPACE VESSEL MEMBRANE, PACKAGING A SPACE VESSEL MEMBRANE AND A SPACE VESSEL MEMBRANE HANDLING UNIT.
    FR 3 062 114 - A1 (57) In a method for packaging and unpacking a spaceship membrane (1) which has, in a plane of extent, a longitudinal axis between opposite longitudinal corners (4) and a transverse axis s extending transversely to the longitudinal axis and across transverse corners, to form a spacecraft membrane wrapping, two wrapping steps are carried out: in a first wrapping step, the spacecraft membrane (1) is wrapped along the transverse axis to form a transverse package (9). In a second packaging step, the transverse packaging (9) is packaged along the longitudinal axis to form a longitudinal packaging. The packaging of the spacecraft membrane (1) in the first packaging step includes packaging the spacecraft membrane material (1) from either side, or on either side of the longitudinal axis. In this case, in the first packaging step, the spaceship membrane (1) is wrapped so that in the transverse packaging produced (9), the transverse corners are freely accessible. In the second packaging step, the transverse packaging (9) is packaged so that in the longitudinal packaging produced, the longitudinal corners (4) are freely accessible. The longitudinal packaging is unpacked by pulling on the longitudinal corners (4). Then, the transverse packaging (9) is unpacked by pulling on the transverse corners.

    -1 METHOD FOR PACKAGING AND UNPACKING A SPACE VESSEL MEMBRANE, PACKAGE OF A SPACE VESSEL MEMBRANE AND A SPACE VESSEL MEMBRANE HANDLING UNIT
    TECHNICAL FIELD OF THE INVENTION
    A method for packaging and unpacking a spacecraft membrane to form a spacecraft membrane package and a spacecraft membrane handling unit are provided.
    In spacecraft, spacecraft membranes are used for various functions. For example, spacecraft membranes are used as solar sails, as antennas, as brake sails (“drag sails” in English) or in the form of a large surface support structure for photovoltaic cells, said functions can also be combined in the same spacecraft membrane. The spacecraft membrane is usually packaged in compact form to form a spacecraft membrane package, the package can be a fold or winding or a combination of the two. The spacecraft membrane packaging produced is then stored with minimal bulk in the spacecraft. Once the spacecraft is in space, the spacecraft membrane packaging can then be unpacked.
    STATE OF THE ART
    For the packaging of spacecraft membranes, there are various known techniques which have in common the fact that the packaging of spacecraft membrane must be as compact as possible and that the unpacking must be able to be carried out fully automatically so that 'It can be performed in space at the spacecraft level without human intervention.
    In their state of use, spaceship membranes are often rectangular, in particular square.
    The scientific book Design and Sizing Method for Deployable Space Antennas (M.
    Straubel; Dissertation, Otto-von-Guericke University, Magdeburg, 2012), discloses a process for wrapping an antenna membrane. The antenna membrane is rectangular and has masts that can be rolled up along its long sides. Starting at its short sides, the antenna membrane is wound with the masts on coil bodies. Similarly, the antenna membrane can also be wound only from one of its short sides on a coil body. The width of the antenna membrane is
    -2directly limited by the length of the reel body or reel bodies and therefore also by a storage length provided in the spacecraft. For a larger membrane, a larger coil body is required, the weight of the coil body increasing with its width. The larger membranes therefore load the spacecraft not only with their own increased weight, but also increase the weight of the coil body.
    In order to avoid a limitation of the width of the spaceship membrane due to the requirements of storage space, it is known to specifically assemble square spaceship membranes made up of four partial membranes in the form of right triangles.
    The IKAROS spacecraft of the Japanese Space Exploration Agency (JAXA) has four triangular solar sail membranes which are assembled to form a square (see for example http://global.jaxa.jp/projects/sat/ikaros). The solar sail membranes have tension cables at the ends of which weights are mounted. The solar sail membranes and the tension cables are wound on a central coil body. The solar sail membranes are unpacked by projecting outwards, by a rotation of the spacecraft, the weights and their tension cables with the solar sail membranes fixed to them. Without the masts, only with the tension cables, the tensioned solar sail membranes are flexible. The solar sail membranes therefore only remain taut as long as the spacecraft rotates. The weights required for unpacking and maintaining the stretched state are, outside the unpacked state, on the tension cables. The oscillations produced during unpacking, due to the low damping, can weaken very slowly, so that the solar sail membranes can still oscillate for several days, or even several weeks, after unpacking, so that in certain circumstances , the solar sail membranes cannot be used during this time. It would be problematic to operate a corresponding spacecraft membrane in the form of a photovoltaic membrane, since the photovoltaic membranes must be oriented rapidly towards the sun. A rapid orientation of the solar sail membrane such as that of IKAROS is however only possible with an excessively high energy input: due to the rotation necessary to tension the spacecraft membrane and the centrifugal forces occurring as a result, the spacecraft can only be redirected with a considerable supply of energy.
    The National Aeronautics and Space Administration (NASA) NanoSail-D2 spacecraft also has four triangular solar sail membranes that are assembled to form a square (see for example
    -3https: //www.nasa.gov/mission_pages/smallsats/nanosaild.html). The solar sail membranes have rollable metal masts which extend from the center of the square along its diagonals. The solar sail membranes and the masts are wound on a central coil body. The solar sail membranes are unpacked, releasing the coiled masts and releasing the energy accumulated in the masts during winding.
    For the Gossamer project of the German Aerospace Center (DLR), four triangular solar sail membranes are assembled to form a square. Each solar sail membrane is folded in an accordion pattern and is wound at both ends on a respective reel body, so that each solar sail membrane can be unrolled and therefore unpacked from its center by unrolling masts. in both directions (see for example http://www.dlr.de/irs/en/DesktopDefault.aspx/tabid-6931/11365_read-
    26354 / gallery-l / gallery_read-Image.46.16877 /). The packaging therefore requires a total of eight coil bodies. These coil bodies remain outside on the masts and increase the load on the masts, in particular during maneuvers of the spacecraft, so that the latter must be designed in a stable manner and therefore more massive than if they were only to carry the solar veil membranes. It is also known to discard the coil bodies after unpacking. However, this produces unnecessary waste in space and violates the national and international codes of conduct of aerospace agencies aiming to avoid waste in space.
    Also known from document DE 10 2010 048 054 A1 is a method for unpacking a sheet which has four triangular sheet portions which are assembled to form a square. The sheet portions are wound from their hypotenuse and parallel to it in several windings in the same direction then are folded in an accordion manner so as to produce an elongated sheet package. Then the foil package is folded centrally once so that its two ends are overlapped and a central fold is formed. Starting from the central fold, the foil package is wound onto a spool body. The packaging thus requires a total of four coil bodies. Unpacking is carried out by attaching deployable masts to the ends of the sheet packaging and unwinding and then unfolding the sheet membrane from the reel body by deploying the masts.
    OBJECT OF THE INVENTION
    The invention relates to a method for packaging and unpacking a spacecraft membrane, and a spacecraft membrane manipulation unit for improved unpacking and improved operation of the spacecraft membrane.
    -4 DESCRIPTION OF THE INVENTION
    The invention follows from the observation that the spaceship membranes in which the rectangular shape, in particular square shape, consists of several segments, in particular segments in the shape of right triangles, have the drawback that the segments are normally fixed only at their corners and are not connected to each other. For example, the triangular segments are not connected to each other along the diagonals of the square. As a result, for example, the distribution of the applied tensile tension is less good, folds can easily form and / or the useful surface is reduced.
    The invention relates to a method for packaging and unpacking a spacecraft membrane which has, in an extent plane, a longitudinal axis between opposite longitudinal corners and a transverse axis extending transversely to the longitudinal axis and through opposite transverse corners, to form a wrapping of spaceship membrane. In a first packaging step, the spacecraft membrane is packed along the transverse axis to form a transverse packaging and in a second packaging step, the transverse packaging is packed along the longitudinal axis to form a longitudinal packaging. In the first packaging step, the spacecraft membrane is in this case wrapped so that in the transverse packaging produced, the transverse corners are freely accessible. The packaging in the first packaging step includes packaging the spacecraft membrane material from each side, and / or on either side, of the longitudinal axis. In the second packaging step, the transverse wrapping is wrapped so that, in the longitudinal packaging produced, the longitudinal corners are freely accessible. In this way, the longitudinal packaging can be unpacked by pulling on the longitudinal corners and then the transverse packaging can be unpacked by pulling on the transverse corners.
    The invention also relates to a spacecraft membrane handling unit comprising a spacecraft membrane package comprising a spacecraft membrane which has, in an extent plane, a longitudinal axis between opposite longitudinal corners and a transverse axis extending transverse to the longitudinal axis and through opposite transverse corners and which is packed along the transverse axis to form a transverse packaging and which is packed along the longitudinal axis to form a longitudinal packaging. The spacecraft membrane package includes a package of the spacecraft membrane material from each side, and / or on either side, of the longitudinal axis. In the transverse product packaging, the corners
    -5 crossways are freely accessible. In the longitudinal packaging produced, the longitudinal corners are freely accessible. In this way, the longitudinal packaging can be unpacked by pulling on the longitudinal corners and then the transverse packaging can be unpacked by pulling on the transverse corners.
    The longitudinal packaging is therefore superimposed on the transverse packaging. The fact that, in the longitudinal packaging produced, the opposite longitudinal corners are freely accessible, does not mean that in the longitudinal packaging, the transverse corners must also be freely accessible. The transverse corners may not be freely accessible until the longitudinal packaging has been unpacked. If, for example, an unpacking mechanism is provided with which the spacecraft membrane is to be unpacked, it can be directly connected to the longitudinal corners but only indirectly to the transverse corners. The indirect connection can for example be made by means of cords which can be packaged together with the longitudinal packaging.
    The longitudinal corners and / or the transverse corners of the spacecraft membrane are fixed to deployable masts so that the traction applied to the longitudinal corners and to the transverse corners can be exerted by deploying the masts. In this way, a spacecraft membrane handling unit is produced with the spacecraft membrane package and the masts. For example, one or two longitudinal masts can be used in the direction of the longitudinal axis and one or two transverse masts can be used in the direction of the transverse axis. The fact that the masts are deployable can mean that the masts can be rolled out or telescoped. In each case, the masts have a mechanism which makes it possible to increase the distance from one end of the mast to the other end of the mast so that the masts can be brought from a compact stored state with a small longitudinal extent to a working state for the spaceship membrane with a large longitudinal extent. Unpacking of the spaceship membrane can therefore be achieved exclusively by deploying the masts. In particular, if, at the level of the longitudinal packaging, all of the longitudinal and transverse corners of the spacecraft membrane are exposed, but otherwise also indirectly, already in the case of a stored state in which the masts have returned and the spacecraft membrane is wrapped, the masts can be attached to or connected to the longitudinal corners and / or transverse corners of the spacecraft membrane.
    The spaceship membrane may have a parallelepiped shape, for example rectangular or diamond-shaped, in particular square but also trapezoidal. For a parallelepipedic spacecraft membrane, in particular square or diamond-shaped, the axis
    -6longitudinal is a first diagonal and the transverse axis and a second diagonal. Square and diamond spacecraft membranes are therefore well suited because they have perpendicular diagonals, and the same length in the case of a square, which produce the longitudinal and transverse axes and which are also axes of symmetry. The size of the spacecraft membrane is not limited in this case, as for example in the case of a rectangle wound on one side or on both sides, by a length of a coil body and therefore at the end account by a workable installation length of the spacecraft membrane packaging. In particular, very large spacecraft membranes can be packaged without their edge length being limited by an installation length predefined by a storage space in the spacecraft. The spacecraft membrane therefore does not necessarily have to have a straight edge, but the edge can for example be regular or irregular sawtooth. In the case of a sawtooth edge, a flexible sheet is preferably not used. On the contrary, in this case, the edge may have a corresponding rigidity, for example because square photovoltaic elements protrude there with their corners. A sawtooth edge can for example also be used when the spaceship membrane has photo voltaic cells which are arranged in strips and offset so that a kind of staircase is obtained along the fish bone.
    Unlike the packaging of spacecraft membranes known in the state of the art, in which it is necessary to construct large rectangular spacecraft membranes, in particular square, in a modular fashion from four triangular spacecraft membranes , the spacecraft membrane according to the invention may not be divided. While in prior art spaceship membrane packaging, the sides, in particular the sides of the right angle of the right triangles, are not fixed but are only stretched between fixing points at the corners triangles, the parallelepiped spaceship membrane according to the invention can be stretched very effectively at its four corners (longitudinal and transverse) and therefore uniformly and completely, so that for example the risk of formation of folds is reduced. In the known method for tensioning several triangular spaceship membranes, a plurality of reel bodies is also often used, for example up to eight reel bodies, as for example for Gossamer-1. On the one hand, this undesirably increases the total weight of the spacecraft and also generates increased complexity during unpacking, which is associated with an increased risk of failure. If only because of the high number of coil bodies, the devices required for unpacking are also more complex than what is necessary according to the invention. On the other hand, preferably within the framework of the invention, it is possible to dispense with the use of a reel body for the packaging of the transverse packaging, while for the packaging of
    -7 longitudinal packaging, a coil body can be used. In one embodiment, it is even possible to package the longitudinal packaging without a reel body.
    The term packaging of the spacecraft membrane here means any operation with which the spacecraft membrane is brought into a compact form, for example folding or winding. Folding can also be achieved by a winding and subsequent compression of a winding obtained. The packaging may also have several stages, for example the spaceship membrane may first be folded and then be rolled up or may first be folded in one direction and then be folded in another direction.
    The fact that the spacecraft membrane packaging includes a packaging of the spacecraft material on either side of the longitudinal axis may mean that the spacecraft membrane is wrapped on itself on the two sides of the longitudinal axis, the two sides of the longitudinal axis being packed independently of each other. This packaging with two partial transverse packaging on the two sides of the longitudinal axis can be carried out simultaneously or one after the other. Such packaging can be produced symmetrically in the case of a square or diamond-shaped spaceship membrane, in particular with specular symmetry, but can also be carried out with point symmetry, for example in the case of a generally rectangular spacecraft membrane. The packaging may also not be symmetrical, for example being produced with an accordion fold on both sides of the longitudinal axis, the accordion folds, however, having different fold widths, i.e. different distances. between their folding edges. The partial transverse packages may, but need not be, adjacent to each other along the longitudinal axis or parts of the longitudinal axis. The spacecraft membrane can also be wrapped on itself so that the material on both sides of the longitudinal axis is wrapped by overlapping or engaging with each other. For example, the spacecraft membrane can be folded along the longitudinal axis and then be folded to form an accordion fold or can be rolled up.
    The packaging can be carried out, both in the first packaging step and in the second packaging step, from the inside to the outside or from the outside to the inside. It can simply be a different way of proceeding, as for example in the case of an accordion fold, which has an identical appearance regardless of the direction from which it is folded. The result may however be different, for example in the case of a spacecraft membrane winding, in which the place where the spacecraft membrane winding started determines which part of the spacecraft membrane
    -8 spaceship is located inside and which part is outside in the winding produced. A winding can in this case comprise both a free winding and a winding on a coil body, the coil body possibly remaining in the winding or being able to be removed therefrom. Similarly, in the case of a folding in which, unlike accordion folding where a folding direction is alternated, one always folds in the same direction (the result corresponds to what is described above by winding and compression) , the place where you started to wrap the spaceship membrane determines which part of the spaceship membrane is inside and which part is outside.
    The longitudinal packaging can be unpacked by pulling on the longitudinal corners without having to otherwise fix the spacecraft membrane. The spacecraft membrane is then retained after unpacking only at its longitudinal and transverse corners. However, it is also possible to locally attach the spacecraft membrane. For this, the spacecraft membrane can itself be fixed (for example in a central region or in an edge region and / or at the level of the spacecraft). The spacecraft membrane may however also be attached to a coil body around which it is wound, the coil body being in turn rotatable on the spacecraft so that after unpacking, the membrane spacecraft is attached indirectly to the spacecraft through the coil body. The spacecraft membrane can also be removably attached to the coil body, for example by a Velcro-type strip.
    The longitudinal packaging can be formed by folds on both sides of the transverse axis. The folds can for example be accordion folds. In this case, the folding surfaces can be arranged essentially perpendicular to the extent plane, so that the folds with specular symmetry produce an accordion-like appearance. By pulling on the longitudinal corners, the folds with specular symmetry are then unfolded, that is to say that the accordion folds are for example separated from each other. A corresponding embodiment can in particular be selected for a square or diamond-shaped spaceship membrane. However, it can also be applied to other geometries of specular symmetry spacecraft membranes.
    The folds can also be folded each time from the longitudinal corner to an unwrapped bridge portion of the spacecraft membrane package. The spacecraft membrane package then has, along its longitudinal axis, in the center, the bridge portion, in which the spacecraft membrane is not wrapped in the longitudinal package. This is particularly advantageous in the case where components
    - 9 individuals must be guided from one side of the spacecraft membrane across the plane of the spacecraft membrane to the other side of the spacecraft membrane. In this case, it may be a mast, but also for example cables, cable passages, tension cables, antennas or any other components of a spacecraft. These can be guided through the bridge part by creating a recess in the bridge part through which the component is guided. In this case, the recess can be found only in a lower layer of the spacecraft membrane, while the component guided through the membrane passes in front of the other layers. The recesses may, however, also be provided in all of the layers so that the spacecraft membrane, when unpacked, may have the recesses at regular or irregular intervals.
    Passage of a component through the spacecraft membrane is also possible without the bridge portion.
    The longitudinal packaging can also be formed by a central folding (in particular only once), seen along the longitudinal axis, of the transverse packaging, and a subsequent winding. The same central folding effect is obtained if the transverse packaging is fixed along the longitudinal axis centrally to the coil body and is thus wound on the coil body by rotating the coil body. Due to the central folding of the transverse package, the transverse package has, in the folded state, one end at which the two longitudinal corners of the spacecraft membrane are located and a second end at which finds the folding edge produced by the central folding. Starting at the folding edge, the transverse packaging is then freely wound or is wound on a spool body. In this way, the longitudinal corners are placed outside on the winding formed and the transverse packaging in the winding is located in a doubled manner continuously. Thus, the opposite longitudinal corners are exposed and the longitudinal packaging can be unpacked according to the invention.
    When using a coil body for winding, it is advantageous that the entire spacecraft membrane can be wound on a coil body. Compared to the number of up to eight of the prior art coil bodies, this constitutes a considerable saving in weight to be transported by the spacecraft and represents a significant reduction in the complexity of the device. In addition, the single coil body, after unwinding or after complete unpacking, remains at the center of the spacecraft membrane. This means in certain circumstances an advantageous weight distribution at the level of the spacecraft membrane and therefore at the level of the spacecraft as a whole, since the corners and the edges of the spacecraft membrane are not weighed down
    -10 by the weights of the coil bodies.
    The packaging of the spacecraft membrane in the first packaging step on either side of the longitudinal axis can be carried out symmetrically. In particular, for typical square spacecraft membranes, the package may for example be a package with specular symmetry. The packaging can however also be for example with point symmetry, as for example in the general case of a rectangle, which is already in itself point symmetry with respect to its diagonals which serve as longitudinal and transverse axes, but which n is not specularly symmetrical.
    The transverse packaging may have accordion folds on either side of the longitudinal axis. The accordion folds can be oriented with their layers essentially parallel to the plane of extent of the spacecraft membrane. The accordion folds can for example be formed so that on either side of the longitudinal axis, that is to say for a square or diamond-shaped spaceship membrane, on both sides. another on a diagonal, a triangular part of the spaceship membrane is folded into an accordion.
    The spacecraft membrane may have spring elements which bias the spacecraft membrane in a packed or unpacked state. In the case of an accordion fold, the spring elements can for example stress the individual folds from the unfolded state into the folded state. When the spring elements stress the spacecraft membrane, for example in a wrapped state, they allow the spacecraft membrane to be packaged (stored) also during the operation of the spacecraft, i.e. usually when no human intervention is not possible. In other words, when the traction acting on the corners (longitudinal and / or transverse) of the spaceship membrane, which is also used for unpacking, is released, the spaceship membrane is automatically repacked again due to the effect of spring elements. The spring elements can also stress the spacecraft membrane only in a partially wrapped or partially unpacked state so that, for example, the spacecraft membrane can only return to the state of transverse packaging but not of longitudinal packaging . Possibly, in the case of the use of such spring elements for the unpacking of the spacecraft membrane, a greater force expenditure may be necessary because during the unpacking, it is necessary to work against a prestress. spring elements.
    Advantageous improvements of the invention result from the claims, the description and the drawings. The advantages mentioned in the description, characteristics and
    - It combinations of several characteristics, are only provided as examples and can act separately or with each other without the benefits must necessarily be obtained from embodiments according to the invention. Without thereby modifying the subject matter of the appended claims, it can be said, with regard to the content of the disclosure of the documents of the original application and of the patent, that: additional features result from the drawings - in particular illustrated geometries and relative dimensions of several components with respect to each other as well as their relative arrangement and their functional connection. The combination of features of different embodiments of the invention or features of different claims is also possible by departing from the selected retro-references of the claims and is encouraged here. This also relates to the features which are illustrated in separate drawings or which are cited in the description of these drawings. These features can also be combined with features of different claims. Likewise, features cited in the claims may be omitted for other embodiments of the invention.
    The characteristics mentioned in the claims and in the description, in relation to their number, must be interpreted in the sense that it is exactly this number or a number greater than the number cited, without it being necessary to 'explicitly use the expression at least. For example if it is a corner, it should also be interpreted to mean exactly a corner, two corners or more than two corners. These characteristics may be supplemented by other characteristics or may be the only characteristics from which the respective result is obtained.
    The reference numbers indicated in the claims do not constitute any limitation on the scope of the objects protected by the claims. They only serve to make the claims easier to understand.
    BRIEF DESCRIPTION OF THE FIGURES
    The invention will be explained and described in more detail below with the aid of preferred embodiments illustrated in the figures.
    Figure 1 illustrates a spacecraft membrane from above.
    Figure 2 illustrates the spacecraft membrane of Figure 1 in a partially wrapped or partially unwrapped state in oblique perspective view from above.
    FIGS. 3 to 11 illustrate partial steps of a first packaging step in which a spacecraft membrane is wrapped to form a transverse packaging, in perspective view obliquely from above.
    Figure 11 illustrates the spacecraft membrane in a partially wrapped or partially unpacked state with fasteners separated from each other by fasteners, in oblique perspective view from above.
    FIG. 12 illustrates an enlarged portion XII of FIG. 11.
    Figure 13 illustrates, in an enlarged portion XIII of Figure 12, a connector of the fixing device.
    Figure 14 illustrates, in an enlarged portion XIV of Figure 12, a clamp of the fixing device.
    Figure 15 illustrates, in an enlarged portion XV of Figure 12, a loop of the fixing device.
    Figure 16 illustrates a portion of a wrapped or partially wrapped spacecraft membrane with a fastener closed with a connector, clamp, and a loop.
    FIGS. 17 and 18 illustrate partial steps of a second packaging step, in which the transverse packaging according to FIG. 10 is packaged to form a longitudinal packaging, in perspective view obliquely from above.
    Figures 19 and 20 illustrate another possible embodiment with partial steps for the second packaging step in perspective view obliquely from above.
    FIG. 21 illustrates an additional possible embodiment for the longitudinal packaging in perspective perspective obliquely from above.
    FIG. 22 illustrates the longitudinal packaging according to FIG. 20, a mast being guided through the longitudinal packaging, in perspective view obliquely from above.
    Figure 23 illustrates the longitudinal packaging according to Figure 21, a mast being guided through the longitudinal packaging, in perspective view obliquely from above.
    - 13 Figures 24 to 27 illustrate, in oblique perspective view from above, an unpacking or partial unpacking of the spacecraft membrane with a successive loosening of the fixing devices.
    Figure 28 illustrates a spaceship membrane in a partially unwrapped or partially wrapped state in oblique perspective view from above.
    Figure 29 illustrates a flow diagram of a method of packaging a spacecraft membrane with a mounting of fasteners.
    Figure 30 illustrates a flow diagram of an additional method of packaging a spacecraft membrane.
    DESCRIPTION OF THE FIGURES
    For the components of identical or different embodiments which have the same or similar shape and / or function, the same reference numbers will be used below. For components which occur several times, for example on two sides of an axis of symmetry, these will be distinguished by letters or Roman numerals affixed. These components will be referred to in common without the letters or Roman numerals.
    Figure 1 illustrates a square spacecraft membrane 1. The spacecraft membrane 1 has a longitudinal axis 2 and a transverse axis 3. Due to the square shape of the spacecraft membrane 1, the longitudinal axis 2 and l transverse axis 3 correspond to the diagonals 27 of the spaceship membrane 1. Along the longitudinal axis 2, the spaceship membrane 1 has two opposite longitudinal corners 4. It also has, along the transverse axis 3 , opposite transverse corners 5. Parallel to the longitudinal axis 2, at regular intervals between the longitudinal axis 2 and the transverse corners 5, the spaceship membrane 1 has fold lines 6, which are illustrated here with lines thin in dashes. The fold lines 6 can be made before packaging, for example can be pre-folded or can be marked by boundaries, for example between adjacent photovoltaic cells, or can be created only during packaging.
    In Figure 2, the spacecraft membrane 1 is illustrated in partially unwrapped or partially wrapped form. Along the fold lines 6, the spacecraft membrane 1 is folded into an accordion 8 so that the fold lines 6 form edges
    - 14de folding 7. In this case, as the folds are regular, the upper folding edges 7c, d and the lower folding edges 7a, b are arranged in parallel planes. The accordion folds 8 have a specular symmetry with respect to the longitudinal axis 2, which is thus an axis of symmetry 26, and is illustrated here in a partially folded intermediate state, in which the accordion folds 8 are slightly open.
    In the region of the folding edges 7, there may be spring elements not illustrated here, which urge the spaceship membrane in a wrapped or unpacked state. In the intermediate state illustrated in Figure 2, the possible spring elements are therefore stretched in each case (at least in part).
    Figures 3 to 10 illustrate partial steps of a first step of packaging the spacecraft membrane 1. In Figure 3, the spacecraft membrane 1 is fully deployed. In FIG. 4, a folding of the spacecraft membrane 1 begins, the spacecraft membrane 1 being folded simultaneously (or also successively) towards the two accordion folds 8 with specular symmetry.
    FIG. 4 illustrates a first partial step of the first packaging step. At the start of the accordion folding 8, the spaceship membrane 1 was folded from the two transverse corners 5 in the direction of the longitudinal axis 2, first beyond the longitudinal axis 2 and then again in rear from longitudinal axis 2 outwards. In this way, symmetrical folding edges 7 have been created. The longitudinal and transverse corners 4 and 5 are therefore exposed. Similarly, for the additional partial steps illustrated in FIGS. 4 to 9, the spacecraft membrane 1 has each time been folded with the transverse corners 5 inwards in the direction of the longitudinal axis 2, d ' first beyond it and then back outward again. The fold edges 7 are therefore arranged closely one above the other, which also results in fold lines 6 spaced regularly according to FIG. 1.
    In FIG. 10, finally, the folding in accordion 8 is finished, and therefore also for the illustrated example of the first packaging step. A transverse package 9 is obtained in which two accordion folds 8 are adjacent to each other along the longitudinal axis 2 with their fold edges 7c, 7d. The longitudinal corners 4 and the transverse corners 5 are in this case exposed. The transverse extent of the transverse packaging 9 corresponds to the sum of the transverse extents of the two accordion folds. The transverse package 9 has two partial transverse packages which are arranged on each side of the longitudinal axis 2.
    - 15 Along the axis of symmetry 26 of the transverse packaging 9, symmetrical layers 28 of the spacecraft membrane 1 are therefore each time in abutment against each other along their folding edges 7. The peripheral edges of the spaceship membrane 1 extend, due to the accordion folds 8, between the outer edges of the transverse packaging 9 and the axis of symmetry 26, in the form of meanders or in the form of a zigzag. In this case, the transverse packaging 9 has all the more layers 28 as it approaches its center, seen along the axis of symmetry 26. The letters i, ii, iii, ... below mean the individual folds (or also corresponding components, see the fastening devices 30i, 30ii, ...) from the outside to the inside, while the letters a and b denote the right side respectively and left of the longitudinal axis 2. In the center is formed an upper layer 28xiv with the transverse corners 5. On the outside, the lower layer 28i is exposed. Above, that is to say folded inwards in the direction of the axis of symmetry 26, is the second layer 28ii. Again, folded outward, is the third layer 28iii. Only a triangle of the second layer 28ii therefore remains exposed. At the tip of this triangle, at the folding edge 7c, 7d, a first inflection point 29i is formed. Similarly, the fourth layer 28iv again folded inwards forms a triangle at the point of which, at the level of the folding edge 7c, 7d, is located a second point of inflection 29ii. Due to the symmetry of the accordion folds, the transverse package 9 has opposite pairs and therefore adjacent to each other and corresponding to inflection points 29ia, 29ib; 29iia, 29iib; ... Between the pairs of inflection points 29a, 29b is each time arranged a fixing device 30. In the example illustrated, the transverse packaging 9 thus has fourteen layers 28i, 28ii, ... 28xiv and twelve pairs of symmetrical inflection points 29a, 29b and twelve fixing devices 30. In FIG. 10, the fixing devices 30 are not illustrated because they could not be seen because of their size.
    FIG. 11 illustrates the transverse packaging 9, the fixing devices 30 being illustrated in the open state. For the sake of clarity of the illustration, all the fixing devices 30 are not illustrated in FIG. 11, but only six fixing devices 30, namely 30i, 30ii, 30iii, ... for half of the spacecraft membrane packaging 12. In Figure 11, the symmetrical accordion folds 8 are almost completely folded. Only the second layer 28ii is lifted from the lower layer 28i, in order to better be able to see the fixing devices 30. The illustrated fixing devices 30 each have three fixing elements, in this case connectors 31, clips 32 and loops 33. The connectors 31 are arranged along a first folding edge 7c each time at the fixing points 52a in the region of the inflection points 29ia, 29iia, 29iiia, ... A the opposite, along the folding edge 7d, the clamps 32 are each arranged at the fixing points 52b in the region of the inflection points 29ib,
    -1629iib, 29iiib, ... Along the axis of symmetry 26 or the diagonal 27, the loops 33i, 33ii, 33iii, ... are distributed uniformly. Figure 12 illustrates this in an enlarged section.
    Figures 13, 14 and 15 are in turn enlarged sections of Figure 12. Figure 13 illustrates the connector 31. The connector 31 is applied with a bearing portion 34 against the spacecraft membrane 1. In a edge portion 35, the connector 31 can in this case be bent along the folding edge 7. In a fixing portion 36, the connector 31 is connected for example by engagement by material bonding to the membrane of spacecraft 1. The attachment portion may constitute a thin film joint. In the simplest case, the fixing portion 36 can for example be formed with a piece of adhesive tape. In an overhanging portion 37, the connector 31 projects beyond the folding edge 7d.
    The clamp 32 has a cross section approximately U-shaped (cf. FIG. 14) and is connected with a lateral branch of the U by engagement by material bonding with the spacecraft membrane 1. The end limiting the opening of the U of this side branch ends in flush with the folding edge 7 without this being necessarily the case.
    FIG. 15 illustrates the loop 33 which is arranged in the region of the longitudinal axis 2 against the lowest layer 28i of the spacecraft membrane 1. The loop 33 can be rigid or elastic.
    FIG. 16 illustrates, in a resolution comparable to that of FIGS. 13 to 15, the fixing device 30 in the closed state. The connector 31 is pressed with its protruding portion 37 into the clamp 32. The connector 31 is retained there by friction engagement and by the clamping effect of the clamp 32. As the connector 31 has previously been inserted through the loop 33, the connector 31 and the clamp 32 are retained in the state connected between the lowest layer 28i and the loop 33. The transverse packaging 9 is therefore fixed in three directions to prevent unpacking:
    by the connection between the connector 31 and the clamp 32, there is a fixing in the directions 38, 39, in which, during a controlled unfolding, exerting traction forces;
    by the loop 33, fixing occurs in the direction 40 perpendicular to the directions 38, 39 and perpendicular to the lowest layer 28i.
    It is clearly seen, in Figures 12 to 16, that the fixing device 30 or its elements
    - 17de fixing should not be arranged exactly in the inflection points 29a, 29b. In particular, for practical reasons, the fixing points 52a, 52b are here arranged slightly offset relative to the inflection points 29. For the fixing effect of the fixing device 30, it is also not crucial that it is disposed itself in the inflection points 29. On the contrary, the fixing device 30 can exert its fixing effect just as well in any other position along the folding edge 7. It it is however advantageous that the fixing device 30 is placed at the level of the inflection points 29 or in the immediate vicinity of these, because one can in certain circumstances thus avoid the formation of folds in the membrane of the spacecraft 1 during unpacking.
    In Figure 17 begins a second packaging step. The transverse packaging 9 is for this purpose wound around a winding center 10. The winding center 10 may possibly have a coil body not shown here. In this case, the winding begins approximately at the height of the transverse corners 5 in the center along the longitudinal axis 2 at the level of the transverse packaging 9. The transverse packaging 9 can be folded in the center so that the corners longitudinal 4 are superimposed and that the winding begins at a central folding edge 53 thus formed.
    In Figure 18, the second packaging step is complete. The transverse package 9 is wrapped, that is to say wound, to form a longitudinal package 11 and therefore to form a spacecraft membrane package 12. It can be seen that the longitudinal corners 4 in this case are always exposed, here on opposite sides of the periphery of the winding formed by the longitudinal packaging 11, the longitudinal corners 4 being turned in opposite directions. The transverse corners 5, in this embodiment of the spacecraft membrane package 12, are located inside the longitudinal package 11 near the winding center 10. If they are to be connected to external elements, such as for example a membrane manipulation mechanism of a spacecraft, this can however occur for example by means of cables or wires. Optionally, fixing devices can be provided to prevent winding or unwinding, which are not illustrated in Figures 17 and 18.
    In the case where the manufacture of the longitudinal packaging 11 occurs by a winding according to FIGS. 17 and 18, the folding edge 53 may also not be arranged centrally, and therefore of different lengths of the transverse packaging 9 are wound on both sides of the folding edge 53. In this way, it is possible, for example, to predefine, depending on the requirements, in which peripheral zone of the winding produced according to FIG. 18 the longitudinal corners 4 are arranged and how the longitudinal corners 4 are arranged one by
    -18report to the other at the level of the winding produced.
    Figures 18, 17 and 10 to 3 can correspondingly be considered in reverse as an unpacking operation. By exerting tensile forces at the level of the spacecraft membrane packaging 12 according to FIG. 18 on the longitudinal corners 4, the longitudinal packaging 11 is first unpacked, that is to say in this case unrolled . Then we get again the state according to Figure 10 in which we have the transverse packaging 9. Now, tensile forces can be exerted on the transverse corners 5, so that the accordion folds 8 are unfolded up 'that the spacecraft membrane 1 has again reached the completely unpacked state according to Figure 3 (see also Figures 24 to 27).
    Figures 19 and 20 illustrate a different embodiment for the second packaging step: according to Figure 19, is produced (from the transverse packaging 9 illustrated above), to form the longitudinal packaging 15, folds in accordion 13 made symmetrically with respect to the transverse axis 3. In this case, a bridge part 14 remains in the unfolded state in the region of the transverse axis 3. In the region of the bridge part 14, the transverse corners 5 are exposed. Optionally, fixing devices can be provided for the accordion folds 13, which are not illustrated in FIGS. 19 and 20. Thus, it is possible that fixing devices 30 fix the longitudinal packaging 15 and / or that fixing devices fix the transverse packaging 8.
    FIG. 20 illustrates a corresponding longitudinal packaging 15 or a spacecraft membrane packaging 16. The accordion folds 13, now in compact form, extend essentially perpendicular to an extent plane of the spacecraft membrane 1 defined by the longitudinal axis 2 and the transverse axis 3. The longitudinal corners 4 are exposed. In the region of the bridge portion 14, the transverse corners 5 are also exposed. As described for the embodiment of Figure 18, by pulling on the longitudinal corners 4, one can return to the second packing step according to Figures 20 and 19 and thus unpack the spaceship membrane 1. By pulling again on the transverse corners 5, as described above, we can return to the first packaging step, as illustrated in Figures 10 to 3 (see Figures 24 to 27).
    Figure 21 illustrates an additional embodiment for a 15 'longitudinal package or for a 16' spacecraft membrane package. This embodiment essentially corresponds to that of FIG. 20, but does not however have a bridge part 14. A continuous accordion-like folding 13 ′ is thus formed.
    As illustrated in FIGS. 22 and 23, the deck part 14 can in particular be advantageous when a component of the spacecraft, for example a mast 17, has to be guided through the membrane of spacecraft 1. The mast 17 may for example be guided through the spacecraft membrane 1 at the point of intersection of the longitudinal axis 2 and the transverse axis 3. The bridge part 14 may have a recess 54. For this purpose, the the recess 54 can be formed for example in a lower layer 28i of the spacecraft membrane 1. Corresponding recesses can also be formed in the region of the folding edges 7 at other layers of the spacecraft membrane 1, these recesses, for the folded state of the accordion folding 8, need only be twice as small as the recess in the lowest layer 28i. It is however also possible, as illustrated in FIG. 22, to make only a crushing 18 of the accordion folds 8 along the folding edges 7 by the mast 17. If a bridge part 14 is provided at the level of the packaging of spacecraft membrane 16, the mast 17 can then have a diameter of comparable size, insofar as the spacecraft membrane 1 allows a corresponding crushing 18.
    The embodiment of Figure 21 is also suitable, as illustrated in Figure 23, for the passage of masts 17 (in this case preferably thin), a crushing 19 along the longitudinal axis 2 occurring in this case also in addition to the crushing 18 along the transverse axis 3.
    As already described, the fixing devices 30 can be mounted in any position on the spacecraft membrane 1. The positioning of the fixing device 30 in the region of the inflection point 29 allows a simple and controlled unfolding, as illustrated in Figures 24 to 27. To this end, tensile forces are exerted at the transverse corners 5 on the spacecraft membrane 1. In Fig. 24, the spacecraft membrane 1 is already unpacked to an extent such that a fastening device 30vi is for the first time also stressed with tensile forces, by the tensile forces acting in directions 38, 39. As a result, the spacecraft membrane 1 is unpacked until a first partial unpacking length 41 and is protected against additional unpacking by the fixing device 30. The fixing device 30vi is released actively or, for example when the fixing device according to FIGS. 11 to 16 is used, in passive form. In the case where the fixing device 30 is formed with a connector 31 and a clamp 32, the loosening of the fixing device 30 lies in the fact that the connector 31 is removed from the clamp 32 due to the tensile force exerted. Thus, the application of a higher tensile force than for the unpacking itself is necessary to loosen the fixing device 30. In this case, the threshold of the force which must be applied to loosen the fixing device 30 can be
    -20 predefined constructively by the clamping force of the connector 31 in the clamp 32. In another configuration of the fixing device 30, it is possible to carry out any other loosening thereof. For example, it is also possible to envisage destruction, tearing and the like of a fastening element of the fastening device 30. Once the fastening device 30vi is loose, the spaceship membrane 1 is released for unpacking only until 'to the engagement of the fixing device according to 30v. With this fixing device 30v, the spacecraft membrane 1 is therefore fixed on a second partial unpacking length 42 to prevent it from unpacking further (FIG. 25). Similarly, an enlarged partial unpacking length is gradually released each time up to the fixing device according to 30iv, 30iii, 30ii, 30i. FIG. 26 illustrates the state in which the second largest possible partial unpacking length 43 is reached, in which only one fastening device 30i remains which prevents the spaceship membrane 1 from unpacking. In FIG. 27, finally, the last fixing device 30i is in turn loosened and the spaceship membrane 1 is unpacked with its greatest possible (partial) unpacking length 44.
    FIG. 28 illustrates the spaceship membrane 1 in a partially unwrapped or partially wrapped intermediate state, the spaceship membrane 1 having spring elements 55 (not visible in this illustration), which stress the spaceship membrane 1 in a packed or unpacked condition. If FIG. 28 illustrates a state in which the spring elements 55 are relaxed, for complete unpacking of the spaceship membrane 1, a tensile force must be exerted against the action of the spring elements 55. This corresponds to a normal unpacking operation. However, if the tensile force decreases, then, under the action of the spring elements 55, the spacecraft membrane 1 is again brought back to the partially unpacked state illustrated in Figure 28. This may be desirable, for a operation of a spacecraft on which the spacecraft membrane 1 is used, if one wishes to repackage at least part of the spacecraft membrane 1 for example in order to put only a partial surface of a solar sail in action , or to store the spacecraft membrane L again If the spacecraft membrane 1 for example is provided with photovoltaic cells, it can be brought into the partially unpacked state in order to obscure the photovoltaic cells and prevent generation undesirable excessively high current.
    Figure 29 illustrates a flow diagram of a method 45 for packaging the spacecraft membrane 1. In a step 46, the spacecraft membrane 1, from a completely unwrapped starting situation in which the spacecraft membrane 1 has the greatest possible (partial) unpacking length 44, is in this case packed to such an extent that it has its second greatest length
    -21 possible partial unpacking 43. In a step 47, this partial unpacking length 43 is fixed with one or more fixing devices 30i. Each fastening device 30i can in this case be mounted between two or more of two layers 28 of the spacecraft membrane 1 adjacent, opposite (symmetrically) or distant from each other.
    In a step 48, the spacecraft membrane is further wrapped, until it has a subsequent partial unpacking length which is less than the previously fixed partial unpacking length 43. In a step 49, this unpacking length partial is in turn fixed with one or more fixing devices 30ii, 30iii, ... Steps 48 and 49 repeated as frequently as desired until the spacecraft membrane is completely wrapped. Optionally, after the last fixing with fixing devices 30, in this case with the fixing device 30vi, the spacecraft membrane 1 is still packed in a last step 50, this latter packaging no longer being fixed. For example, one or more outermost layers 28 of the spacecraft membrane may be wound, which are not secured with fasteners 30.
    Finally, also as an option, a connection of the corners 4, 5 with deployable masts, carriages, and the like, can be carried out at the level of the spaceship membrane packaging 12, 16, 16 'in a step 51, this which allows to form a spacecraft membrane manipulation unit. By means of masts, carts, and the like, unpacking can be performed at a later time.
    Unpacking, for example using the deployable masts of the spacecraft membrane manipulation unit, can thus take place by performing steps 50 to 46 in reverse, so that the respective fasteners 30 in this case the fastening devices 30vi, 30v, 30iv, 30iii, 30ii, 30i, are loosened actively or passively and that the spaceship membrane 1 is partially unpacked until the next fixed unpacking length.
    FIG. 30 illustrates a flow diagram of a method 21 for packaging the spaceship membrane 1.
    The method 21 has a first packaging step 22 and a second packaging step 23. In the first packaging step 22, the spacecraft membrane 1 is packaged to form the transverse packaging 9, this can occur from the manner illustrated in Figures 3 to 10 by folding two accordion folds 8 with specular symmetry. In particular, the first packaging step 22 can include the process 45 so that the
    -22devices for fixing 30 are mounted on the transverse packaging 9. In each case, the transverse corners 5 remain freely accessible in the transverse packaging 9.
    In the second packaging step 23, the transverse packaging 9 is packaged to form the longitudinal packaging 11, 15, 15 '. This can happen in particular in the manner illustrated in FIGS. 17 and 18, so that the accordion folds 8 of the transverse packaging 9 are wound to form the longitudinal packaging 11. This can also occur in the manner illustrated in the figures 19, 20, 21, an accordion fold 13, 13 ′ of the longitudinal packaging 15, 15 ′ being in this case superimposed on the accordion folds 8 of the transverse packaging 9. In this case, the longitudinal packaging 15 can be created with or without bridge region 14. Optionally, the second packaging step 23 may include the method 45, so that the fastening devices 30 are mounted on the longitudinal packaging 12, 16, 16 ', independently of the whether the process 45 has already been carried out in the first packaging step 22 or not.
    In another optional step 24, a component of the spacecraft, for example a mast 17, can be guided through the packaging of spacecraft membrane 12, 16, 16 ', recesses 54 which can be provided in the spacecraft membrane spacecraft 1 or the spacecraft membrane 1 which may have only a single recess 54 in a lower layer 28i, while other layers are crushed around the mast 17.
    Finally, in an optional step 25, a spacecraft membrane handling unit can be formed with the spacecraft membrane packaging 12, 16, 16 ', for example by fixing deployable masts at the longitudinal corners 4 and transverse corners 5.
    Insofar as, in the context of the present invention, it is a question of corners, in particular longitudinal corners 4 or transverse corners 5, this does not necessarily mean bent corners. On the contrary, these may have any shape, for example be rounded, or they may be ends of the spacecraft membrane 1 at which the unpacking members of the longitudinal packaging 11 engage and / or the transverse packaging 9.
    LIST OF REFERENCE NUMBERS 123456789101112131415161718192122232425262728293031323334353637 Spaceship membraneLongitudinal axisTransversal axisLongitudinal cornerCross cornerFolding lineFolding edgeAccordion foldingCross packagingWinding centerLongitudinal packagingSpaceship membrane packagingAccordion foldingBridge partLongitudinal packagingSpaceship membrane packagingMastCrushingCrushingProcessPacking stepPacking stepStepStepAxis of symmetryDiagonalLayerInflection pointFixing deviceConnectorPliersLoopSupport portionEdge portionAttachment portionOverflow portion
    -24 Direction
    Direction
    Direction
    Partial unpacking length Partial unpacking length Partial unpacking length Unpacking length (partial) Process
    Step
    Step
    Step
    Step
    Step
    Step
    Attachment point
    Folding edge
    Obviously
    Spring element
    权利要求:
    Claims (16)
    [1" id="c-fr-0001]
    1. Method (21) for packaging a spacecraft membrane (1) which has, in a plane of extent, a longitudinal axis (2) between opposite longitudinal corners (4) and a transverse axis (3) extending transversely to the longitudinal axis (2) and through opposite transverse corners (5), to form a spacecraft membrane package (12, 16, 16 ') and to unpack the spacecraft membrane package (12 , 16, 16 '), including
    a) a first packaging step (22) in which the spaceship membrane (1) is wrapped along the transverse axis (3) to form a transverse packaging (9) and
    b) a second packaging step (23) in which the transverse packaging (9) is packaged along the longitudinal axis (2) to form a longitudinal packaging (11, 15, 15 '),
    c) the packaging of the spacecraft membrane (1) comprising, in the first packaging step (22), a packaging of the material of the spacecraft membrane (1) on either side of the axis longitudinal (2),
    d) in the first packaging step (22), the spacecraft membrane (1) being packed so that, in the transverse packaging produced (9), the transverse corners (5) are freely accessible, and
    e) in the second packaging step (23), the transverse packaging (9) being packaged so that, in the longitudinal product packaging (11, 15, 15 '), the longitudinal corners (4) are freely accessible, characterized in that
    f) during unpacking fa) the longitudinal packaging (11, 15, 15 ') is unpacked by pulling on the longitudinal corners (4) and fb) then, the transverse packaging (9) is unpacked by pulling on the transverse corners (5).
    [2" id="c-fr-0002]
    2. Spaceship membrane handling unit comprising a spaceship membrane package (12, 16, 16 ') comprising
    a) a spacecraft membrane (1) aa) which has, in a plane of extent, a longitudinal axis (2) between opposite longitudinal corners (4) and a transverse axis (3) extending transversely to the longitudinal axis (2) and through opposite transverse corners (5) and ab) which is wrapped along the longitudinal axis (2) to form a longitudinal wrapping (11, 15, 15 ') and which is wrapped along of the transverse axis (3) to form a transverse packaging (9), and
    b) deployable masts (17),
    c) the packaging of the spaceship membrane (1) comprising a packaging of the material of the spaceship membrane (1) on either side of the longitudinal axis (2),
    d) in the transverse product packaging (9), the transverse corners (5) being freely accessible, and
    e) in the longitudinal product packaging (15), the longitudinal corners (4) being freely accessible, characterized in that
    f) the longitudinal packaging (11, 15, 15 ') can be unpacked by pulling on the longitudinal corners (4) and
    g) then the transverse packaging (9) can be unpacked by pulling on the transverse corners (5) and
    h) the longitudinal corners (4) and the transverse corners (5) of the spaceship membrane (1) are fixed to the deployable masts (17) so that the traction applied to the longitudinal corners (4) and to the transverse corners ( 5) to unpack the longitudinal packaging and the transverse packaging can be exercised by deploying the masts (17).
    [3" id="c-fr-0003]
    3. Method (21) according to claim 1, characterized in that the longitudinal packaging (11, 15, 15 ') is formed by folds on either side of the transverse axis (3).
    [4" id="c-fr-0004]
    4. Method (21) according to claim 3, characterized in that the folds are folded each time from the longitudinal corner (4) to an unpackaged bridge part (14) of the spacecraft membrane packaging (12, 16 16 ').
    [5" id="c-fr-0005]
    5. Method (21) according to claim 1, characterized in that the longitudinal packaging (11, 15, 15 ') is formed by a central folding, seen along the longitudinal axis (2), of the packaging transverse (9), and a subsequent winding.
    [6" id="c-fr-0006]
    6. Method (21) according to any one of claims 1 and 3 to 5, characterized in that the packaging of the spacecraft membrane (1) is carried out symmetrically on either side of the longitudinal axis (2) in the first packaging step (22).
    [7" id="c-fr-0007]
    7. Method (21) according to any one of claims 1 and 3 to 6, characterized in that the transverse packaging (9) has accordion folds (8) on either side of the longitudinal axis ( 2).
    [8" id="c-fr-0008]
    8. Method (21) according to any one of claims 1 and 3 to 7, characterized in that the spacecraft membrane (1) is square.
    [9" id="c-fr-0009]
    9. Method (21) according to any one of claims 1 and 3 to 8, characterized (e) in that the spacecraft membrane (1) has spring elements (55) which stress the spacecraft membrane ( 1) in a packed or unpacked state.
    [10" id="c-fr-0010]
    10. Method (21) according to any one of claims 1 and 3 to 9, characterized in that the longitudinal corners (4) and the transverse corners (5) of the spacecraft membrane (1) are fixed to masts deployable (17) so that the traction applied to the longitudinal corners (4) and the transverse corners (5) to unpack the longitudinal packaging and the transverse packaging can be exerted by deploying the masts (17).
    [11" id="c-fr-0011]
    11. Spaceship membrane manipulation unit according to claim 2, characterized in that the longitudinal packaging (11, 15, 15 ') is formed by folds on either side of the transverse axis (3) .
    [12" id="c-fr-0012]
    12. Spaceship membrane manipulation unit according to claim 11, characterized in that the folds are folded each time from the longitudinal corner (4) to an unpackaged bridge part (14) of the packaging of spaceship membrane (12, 16 16 ').
    [13" id="c-fr-0013]
    13. Spaceship membrane manipulation unit according to claim 2, characterized in that the longitudinal packaging (11, 15, 15 ') is formed by a central folding, seen along the longitudinal axis (2), of the transverse packaging (9), and a subsequent winding.
    [14" id="c-fr-0014]
    14. Spaceship membrane manipulation unit according to any one of claims 2 and 11 to 13, characterized in that the transverse packaging (9) has accordion folds (8) on either side of the 'longitudinal axis (2).
    [15" id="c-fr-0015]
    15. Spaceship membrane manipulation unit according to any one of claims 2 and 11 to 14, characterized in that the spaceship membrane (1) is square.
    [16" id="c-fr-0016]
    16. Spaceship membrane manipulation unit according to any one of claims 2 and 11 to 15, characterized in that the spaceship membrane (1) has spring elements (55) which stress the spaceship membrane (1) in a packed or unpacked state.
    1/23
    Fie ”. 1
    2/23 ci
    3123
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    同族专利:
    公开号 | 公开日
    DE102017101180B4|2022-02-17|
    US20180208332A1|2018-07-26|
    US10934024B2|2021-03-02|
    DE102017101180A1|2018-07-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    US6585193B1|2000-10-30|2003-07-01|Lockheed Martin Corporation|Spacecraft with integrated pulsed-plasma thrusters|
    DE10241618B4|2002-09-04|2005-10-27|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Method for stowing and unfolding large-area films|
    US9550584B1|2010-09-30|2017-01-24|MMA Design, LLC|Deployable thin membrane apparatus|
    DE102010048054A1|2010-10-12|2012-04-12|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Device for fixing folded sheet, comprises rotated coil body and folded sheet which is wound on coil body, where one end of folded sheet is connected with coil body by mounting device in detached manner|
    FR3015436B1|2013-12-20|2017-12-15|Astrium Sas|INFLATABLE FLYING VEIL|
    WO2015179213A2|2014-05-14|2015-11-26|California Institute Of Technology|Large-scale space-based solar power station: multi-scale modular space power|DE102018111125B4|2018-05-09|2022-02-17|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Spacecraft Diaphragm Coil Bearing System and Spacecraft Diaphragm Coil Assembly|
    DE102018117993B4|2018-07-25|2020-06-18|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Spacecraft membrane unit and spacecraft membrane package with a spacecraft membrane unit|
    DE102020111232B3|2020-04-24|2021-08-12|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Electric roll-and-fold spacecraft membrane, spacecraft spooling device, and method for unpacking an electric roll-and-fold spacecraft membrane|
    法律状态:
    2019-12-26| PLFP| Fee payment|Year of fee payment: 3 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 4 |
    2021-12-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017101180.3|2017-01-23|
    DE102017101180.3A|DE102017101180B4|2017-01-23|2017-01-23|Method of packing a spacecraft membrane, spacecraft membrane pack and spacecraft membrane handling unit|
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