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WO2003003517A1 - Antenne a reflecteur spatiale deployable - Google Patents

Antenne a reflecteur spatiale deployable Download PDF

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Publication number
WO2003003517A1
WO2003003517A1 PCT/GE2002/000004 GE0200004W WO03003517A1 WO 2003003517 A1 WO2003003517 A1 WO 2003003517A1 GE 0200004 W GE0200004 W GE 0200004W WO 03003517 A1 WO03003517 A1 WO 03003517A1
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WO
WIPO (PCT)
Prior art keywords
frame
deployable
reflector
rods
accordance
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Ceased
Application number
PCT/GE2002/000004
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English (en)
Inventor
Elguja Medzmariashvili
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Individual
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Individual
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Filing date
Publication date
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Publication of WO2003003517A1 publication Critical patent/WO2003003517A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
    • H01Q15/161—Collapsible reflectors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas

Definitions

  • the present invention relates to Radio Engineering. According to the present invention, a deployable reflector is provided that can be used in large size space antennas.
  • Rib provided umbrella shape reflector design has considerable advantage due to the deployment reliability, simple design and accuracy of contours of the ribs. These advantages are particularly apparent in the deployable rib-umbrella reflectors having entire ribs designed so that they do not fold locally.
  • the ribs are radially interconnected, are deployed by a common mechanical means and have a common fixation. These advantages are significantly reduced when each of the rib is unable to fall within the allowable dimensions of the folded reflector package by reason of its own length. In such cases "breakings" are needed to be made in special hinges and this is why the design becomes much more complicated.
  • the patent 3286259 (H01Q 15/20, 1964) discloses a design wherein the spiral forms of the ribs are proposed instead of the radial arrangement thereof. Not being fully expanded in this state, each rib keeps the elasticity energy accumulated therein. The fixation of the ribs is performed by the reflector which is in deployed state by the same ribs. The frame obtains much more stiffness being in such a tensioned state.
  • the rib-umbrella shape reflectors with different shapes of their individual ribs give very good opportunity to construct offset type reflectors. This is due to the necessity of different size and shape members to achieve profile of the approximated surface of various sections of reflectors having dissymmetrical double curvature. This is why, when the rib-umbrella reflectors is made of the ribs which are not fixed in any point other then the central unit it becomes simple, in principle, to make these ribs which will have different sizes and shapes.
  • Principal diagram of deployable rim systems is comprised of a deployable rim and flexible framework attached to the rim from inside.
  • the framework is deployed from its stowed state by deploying the rim and is tensioned in its final state by the same rim.
  • the tensioned framework creates the contours of approximated surface having the form of the antenna reflector, whereto a flexible reflector is attached.
  • Many solutions have been proposed as to the individual designs of deployable rim, its deploying energomechanics, synchronization of deployment, fixation of the form in deployed state and the main thing is that various designs of tensioned flexible frameworks and attachment means for attaching the deployable reflector to the spacecraft have also been provided.
  • the framework comprises two “tyres” connected to one another by means of rigid struts.
  • Each tyre is a polygon and is comprised of rigid rods.
  • the rigid rods and the rigid struts of the "tyre” are connected to one another by means of hinged joints. Within the hinged joints, elastic rods are fixed, being tensioned in the center. Metal cables can be used as the elastic rods.
  • Elastic connections are made as a ring and are forming a "web". To obtain the necessary parabolic shape of the antenna, the elastic connections are tensioned to one another by means of the elastic rods arranged in parallel with the rigid strut. Also, elastic rods are applied to avoid the twisting of the "tyres'.
  • Such a framework is connected to the rotative devices by attaching it to a rim.
  • the inventions of the later period are connected with attempts to reduce the deployable rim weight; to increase its stiffness and accuracy, upon which the accuracy of the reflector shape still remains depended in deployable rim systems; to enlarge sizes, accuracy, and stiffness of the frame tensioned by a rim and to which the reflector is attached.
  • principal novelties in deployable rim systems are not achieved.
  • the deployable rim with enhanced stiffness is reduced in weight which is capable of enlarging partially the dimensions of the tensioned frame both inside the rim and outside the one to the extent possible by the design peculiarities.
  • design of the rim though to the limited extents conditioned by the design of the rim, allows to make improvements to obtain more convenient frame of the offset reflector surfaces.
  • the design of the rim is extremely complicated and overloaded with mechanical units, hinges, rods, connections, etc. All of these factors have particular effect on the precision of the deployable ring project position and, of course, on the reliability of deployment.
  • the above-mentioned analog retains the properties characteristic to the rim systems and the tensioned frameworks thereof.
  • the deployable rim systems including the above-mentioned analogs, have the same disadvantages in the system and principal point of view, and they are divided into three groups, namely:
  • the reflector antenna comprises a deployable rim and a tensioned frame.
  • the deployable rim is constructed as outside rim structure surrounding the tensioned frame and being the support therefor.
  • the tensioned frame is constructed in front net and back net made of flexible members and being tensioned by means of flexible ties,
  • the tensioned frame is fastened to the deployable rim by means of its periphery.
  • a reflector is fastened on the side of its internal net, the reflector being constructed, in this specific embodiment, in a thin net.
  • the deployable rim is constructed in struts, rods, and diagonals hinged to one another.
  • the deployable rim is provided with local deployment synchronization and fixation mechanisms.
  • the deployable rim is provided with a power-mechanical deployment system which is made, in this specific embodiment, of a load-bearing cable winding onto a drive means or a pneumatic system.
  • the known reflector antenna as a whole comprises a deployable rim, a tensioned frame fastened thereunto, whereto a reflector is attached, the deployable rim being provided with a local deployment synchronization mechanism, a local deployment fixation mechanism, and a power-mechanical deployment system.
  • the drawback of such a reflector antenna is the limitation in increasing the reflector sizes. This limitation is conditioned by the deformation of the tensioned frame, low frequency of oscillation, big height between the ends of the peripheral portion, direct impact of the deviations from the designed geometry on the inaccuracy of the reflector shape when the deployable rim is in the deployed state. In addition, shape of a particular portion in plan does not correspond to that of a offset reflector antenna.
  • the technical result of the present invention is increase in stiffness and accuracy of the systems with a deployable rim, elimination of the impact of the deviations from the designed shape on the accuracy of the reflector shape in deployed state of the deployable rim, and, particularly, obtantion of new additional essential technical effect by synthesis of deployable rim systems and rib-umbrella shape dome frame systems, i.e.
  • the new deployable reflector antenna to have little weight, big accuracy, big stiffness, simplicity in its manufacturing technology and increased variety of attachment variants of attachment to a spacecraft in the event it is enlarged in size, while maintaining common deployment stability, synchronization, and orientation.
  • the reflector antenna diagram will be in concordance with the requirements imposed for offset reflector antennas.
  • the deployable space reflector antenna "E.V.M.” comprises a tensioned frame and a deployable dome frame attached to the tensioned frame by means of connection joints at the outside of its periphery.
  • the tensioned frame and the deployable dome frame create approximated surface of the entire reflector of the reflector antenna, whereto the reflector is attached.
  • the approximated surface forms symmetrical and dissymetrical structures of offset reflectors having circular, oval, or polygonal outlines in plan.
  • the tensioned frame is attached to the deployable rim by means of fastening joints and movable joint, or by movable joints solely.
  • the deployable dome frame is connected to the deployable rim by means of fixed joints, movable joints, and/or the tensioned frame.
  • the deployable rim is provided with a local deployment synchronization mechanism, local deployment fixation mechanism, and power-mechanical deployment system.
  • the tensioned frame is provided with a common deployment stabilization system and common deployment orientation system.
  • the interconnected tensioned frame, deployable rim, and deployable dome frame are constructed in various design solutions and parts in the specific embodiment.
  • the reflector antenna "E.V.M.” represents a transportable package in its folded state which can be unfolded and fixed in its final form by deploying the deployable rim.
  • the reflector antenna is provided with a variety of design solutions for attaching to a spacecraft.
  • the deployable space reflector antenna "E.V.M.” is illustrated by means of 100 figures, where: Fig 1 is principal view of the space reflector antenna “E.V.M.” in its deployed state; Fig 2 is a flat rib with peripheral dividers arranged in parallel to one another; Fig 3 is a flat rib with its reflector fastening contour differing from that of the opposite contour; Fig 4 is a flat rib with peripheral dividers inclined relative to each other; and with reflector fastening contour length differing from that of the opposite contour; Fig 5 is a flat rib with reflector fastening contour and its opposite contour touching each other; is a radial diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; is a radial-ring diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; is a parallel diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; is a triangle diagram of
  • Fig 100 is ovals arranged outside the rim, which are resting against each other by means of teeth arranged at their edges, and the temperature deformation dampers arranged on the rods.
  • the deployable space reflector antenna "E.V.M.” 1 comprises a reflector
  • the tensioned frame is attached to the deployable rim 5 by the peripheral attaching means 4.
  • the deployable rim is provided with local deployment synchronization mechanism 6, local deployment fixing mechanism 7, and power-mechanical deployment system 8.
  • the tensioned frame has connection to a deployable dome frame 10 by means of connecting joints 9 located outside its periphery.
  • the dome frame, together with the tensioned frame, forms a common approximated surface for fixing the reflector that is applicable in both symmetrical and dissymmetrical offset reflectors having circular, oval and/or polygonal outlines in the plan.
  • the deployable dome frame is connected to the deployable rim by means of fixed joints 11, movable joints 12, and/or the tensioned frame.
  • the sizes of the opposite edge contours of the deployable rim are equal or they may be differed from one another by a constant value or variable in the process of being deployed.
  • the tensioned frame is fixed to the deployable rim by means of movable units 13 or it is fixed by the movable units only.
  • the tensioned frame is equipped with a common deployment synchronization system 14 and common deployment stabilization system or common deployment orientation system (Fig 1).
  • the deployable space reflector antenna "E.V.M.” comprises an extensible or flexible net or membrane constructed as a whole structure or in parts of individual shapes.
  • the tensioned frame is composed of flat ribs 17 (Fig. 2) made of windable and/or foldable sheets or membranes. At the peripheral edges of the ribs, peripheral dividers 18 are mounted.
  • the peripheral dividers are made of stiff rods having equal and/or different lengths. They are arranged in parallel or inclined relative to each other in the tensioned frame (Fig 3,4).
  • the flat ribs as components of the tensioned frame, individually form the reflector fixing contour 19 and the opposite contour 20.
  • the reflector fixing contour and the opposite contour have similar or different outlines in each flat rib with equal or different lengths. These contours touch (Fig 5) or do not touch each other.
  • the flat ribs of the tensioned frame with their spatial relation form radial (Fig 6), radial-ring (Fig 7), parallel (Fig 8), triangle (Fig 9), quadrangle (Fig 10) and/or hexagonal (Fig 11) shapes of the reflector fixing contours.
  • intermediate stiffness dividers 21 are mounted on the flat ribs (Fig 11 and 12) or the intersection line thereof (Fig 14).
  • the ribs made of sheets or membranes, are provided with cut-outs 23 (Fig 17, 18) and perforations 24 (Fig 19, 20).
  • the common deployment synchronization system of the tensioned frame composed of flat ribs radially arranged in space is constructed by fixing long shafts 25 rotatable around the axes opposite the reflector contour on the central unit, the shafts being arranged perpendicular to the direction of winding of the flat ribs onto the central unit (Fig 21).
  • the common deployment stabilization system is constructed in sprockets 26 and drums 27 having cells with recesses. Both the sprockets and the drums are fixed on the rotatable shafts by turns. Between the sprockets and drums, perforated cells 28 applied on the ribs are passing in order during the passage of the flat ribs twisted around the central points.
  • the tensioned frame may be constructed in other structures.
  • the tensioned frame is consisted of a reflector frame 29 forming the reflector shape approximated surface and a support frame 30, the reflector frame and the support frame being connected to one another by means of rod connections 31.
  • peripheral dividers 18 made of stiff rods having equal or different lengths are mounted, the dividers being arranged in parallel or inclined relative each other in the tensioned frame (Fig 22 and 23).
  • the reflector frame and support frame directly touching (Fig 25) or not touching (Fig 24) each other have either similar or different shapes and equal or different sizes in the plan.
  • the rod connections are comprised of struts 32 and/or braces 33 in such a manner that the ends of the braces are connected to the ends of the struts and/or braces, and the edge strut and/or edge brace is connected to the peripheral divider with its one end.
  • the reflector frame and the support frame connected to it by rod connections are arranged, along with the rod connections, in the plane and/or space and form radial (Fig 26), radial-ring (Fig 27, 28), radial-net (Fig 29, 30), parallel (Fig 31), quadrangle (Fig 32, 33), triangle (Fig 34), or hexagonal (fig 35) diagrams and/or combined diagrams thereof in plan (Fig 36).
  • the reflector frame and support frame are made of sheets, membranes, flexible rods and/or stiff rods, and the rod connections are made of flexible and/or stiff rods and/or sheets and/or membranes ( Figures 37-44).
  • the stiff rods of the reflector frame and support frame are attached to the ends of the struts, braces and/or peripheral divider by means of hinge joints 34 and, in addition, they are provided with intermediate "breakage' hinges 35 between the hinge joints.
  • the additional frame is comprised of an additional reflector frame 38 and/or additional stiffening frame 39.
  • the additional frame is arranged in the tensioned frame in such a manner that it forms ring, radial, radial-ring, radial-net and/or ring-net diagrams (Fig 51, 52).
  • the members of the radially arranged flat ribs in the tensioned frame, or of the additional frame connecting the reflector frame are arranged as concentric circles or as a polygon outlined by ovals, or as eccentrically arranged circles, or as polygons outlined by ovals in plan (Fig 53), while the vertexes of each eccentrically arranged polygon are spaced apart at equal distances from the plane passing through the edge contour of the reflector.
  • the additional frame is constructed in flexible rods, stiff rods, sheets and/or membranes and/or combinations thereof (Fig 54).
  • the reflector frame, support frame, additional frame, and the flat ribs of the tensioned frame are provided with dampers 40 of temperature deformation (Fig 55).
  • the deployable rim is composed of stiff rods 43 arranged on the plane 41 of the lateral edges of regular prisms or pyramid frustums. The rods are connected to one another by means of cylindrical units 42 and they are arranged in the form of "scissors" system.
  • the ends of the robs 43 are a attached to the edge rod dividers of the tensioned frame by means of fixing units 44 and/or movable units 45, the rod dividers being arranged on the lateral faces of the above-mentioned prisms or pyramid frustums (Fig 56, 57).
  • the ends of the deployable rim rods arranged on the planes of the lateral faces of the regular prisms or pyramid frustums are connected to the ends of deployable rim rods arranged on the planes of the lateral ribs by means of cylindrical units 46 (Fig 58) or cardan units comprised of the cylindrical units
  • the cardan units are constructed in three cylindrical units, two of which are the sliding cylindrical edge hinges, and the third one is an intermediate flexible-cylindrical hinge 47 (fig 60).
  • the rods connected with one another by means of cylindrical units and arranged on the plane of an individual face form a single “scissors" arrangement (Fig 56, 57) or double “scissors” arrangement (Fig 61, 62).
  • each rod which is the component of single "scissors" arrangement
  • additional rods 49 arranged in the planes of lateral faces are attached by means of cylindrical units 48.
  • the additional rods are connected to one another with their ends by means of cylindrical hinges 50 and are forming quadrangle arrangements in such a manner that two vertexes of the quadrangles are individually connected to the vertexes of the quadrangles arranged on the adjacent ribs by means of cylindrical or cardan units (fig 63, 64), and the remaining two vertexes are connected to the cylindrical unit of the "scissors" by a common rod 51 on which locator members 52 for restricting the reverse motion of the vertexes with respect to the cylindrical unit, are disposed, and, at the same time, the rod is made as a whole member or as a telescopic member 53 (Fig 65, 66).
  • stiff rods arranged as "scissors" and the additional rods arranged as quadrangles are connected with their ends to the peripheral divider by means of fixing units and/or they are attached by means of movable units in such a fashion that peripheral dividers contain dampers 54 and retaining members 55 for restricting the motion thereof after having performed certain displacement (Fig 67).
  • the power-mechanical system of the deployable rim is constructed in a load-bearing cable 56 which is fixed at the end of a rod contained in "scissors" by means of a compensator 57.
  • the load-bearing cable extends along the longitudinal direction of one of the rods which is the component of "scissors" disposed on each rib, and passing over bearings 58 disposed at the ends of the rod it tensions and approaches the end of the rod to the opposite end of the rod on the adjacent rib.
  • distances between the ends of the rods interconnected as a set of "scissors" arranged on the planes of the regular prism lateral faces and the cylindrical units of the "scissors” are equal (Fig 69) or distances between the ends of the rods interconnected as a set of "scissors” arranged on the planes of the pyramid frustum lateral faces and cylindrical units of the "scissors" are different (Fig 70).
  • the deployable dome frame is constructed in various ways. At the end of the peripheral divider of the tensioned frame, on the reflector side, an arm 60 of the deployable dome frame is attached rigidly by means of connection units.
  • the arm has the contour of the approximated surface of the reflector shape for attaching the reflector thereto (Fig 71). If necessary, the arm is made of flexible material allowing to wind (Fig 71).
  • connection unit 72 to bend in the connection unit with respect to the divider (Fig 73) and/or to bend the arm at its end (Fig 74).
  • the arm is hinged to the peripheral dividers of the tensioned frame by connection units, and its rotation is performed by means of the fixed and/or movable connections arranged at the deployable rim.
  • the fixed and movable connections are constructed in hinge-lever rod system 61 which is also connected to the peripheral divider (Fig 75).
  • the stowed package of the reflector structure constructed in such a manner is illustrated on the Fig 76.
  • the members which form the approximated contour of the dome frame reflector are the flexible members having due profile, whose tensioning form creation and form fixing is performed by means of a stiff deployed member 63 hinged 62 to the end of the peripheral divider opposite to the reflector side.
  • Deployment of the stiff deployed member is performed by means of the deployable rim along with fixed and/or movable connections connected thereto and forming hinge-lever system (Fig 77).
  • the stowed package of such a stricture is illustrated on Fig 78.
  • the arms of the radially arranged dome frame are provided with flexible ties 64 arranged as triangles in plan (Fig 79).
  • Tensioning of the flexible member which forms the approximated contour of the dome frame reflector shape and its form creation is defined by a flexible rod 65 hinged to the end of the peripheral divider opposite to the reflector side, whose unfolding from its stowed condition is performed by means of the deployable rim along with the hinge-lever system of fixed or movable connections connected thereto.
  • the flexible rod which is fastened at the peripheral end of a girder forms combined pretension cantilever girder 67 along with flexible diagonals 66 of the dome frame due to the existing elastic force (Fig 80).
  • the stiff member which forms the approximated contour of the dome frame reflector is hinged to the end of the peripheral divider by means of the connection unit and its orientation is fixed by means of the stiff rod 68 hinged thereto and, also, to the another end of the peripheral divider.
  • the stiff rod ensures also that the stiff member is unfolded and the projection form is fixed due to the hinge-lever system connected to the deployable rim and an additional hinge 69 having a lock (Fig 81).
  • the stowed package of the described construction is shown on the Fig 82.
  • the peripheral divider of the tensioned frame, together with the cantilever member of the deployable dome frame (Fig 83), which is rigidly connected to the end of the peripheral divider by means of a connection unit on the reflector side are built in combination as a rod-girder spatial structure 70, whose chords 71, struts 72 and diagonals 73 are made of stiff rods and flexible tensioned rods (Fig 84, 85).
  • peripheral dividers of the tensioned frame with its fixed units and movable units and/or movable units are fixed in and/or fastened to the deployable rim by means of the chords having rod-girder spatial structure.
  • the ends of the deployable rim rods arranged on the plane of the prism or pyramid frustum lateral faces are connected to the deployable rim rods arranged on the plane of the adjacent lateral edges by means of the added members 74 existing on the cylindrical hinges (Fig 86).
  • ribs of the tensioned frame are united in the central unit fixed in the base unit 75 or fastened by means of a rotatable mechanism 76 provided with locators 77 for restricting the rotation (Fig 84, 85).
  • a joint deployment orientation system 16 in the form of an unfoldable stiff guide is hinged by means of a hinge 78.
  • the joint deployment orientation system is connected to the ends of the peripheral dividers and/or stiffness dividers and/or struts, at the opposite side to the reflector, by means of sliding units 80 (fig 87).
  • the given solution ensures that the stiff guide of the joint deployment orientation system is unfolded by means of the deployable rim in the process of being deployed.
  • the stiff guide is strengthened by means of the reinforcing rods 80 connected thereto and fixed in the base unit (Fig 83). While retaining the design simplicity of the reflector structure, the deployable rim has the form of the pyramid frustum lateral faces in the stowed state so as to fall within the sizes of the stowed package, and the vertex of the pyramid constructed thereby is located on the reflector side (Fig 88, 89).
  • the additional frame is disposed also between the frame of the deployable dome frame (Fig 83).
  • connection of the deployable space reflector antenna "E.V.M.” to the spacecraft is performed by means of the basic unit (Fig 90) or deployable dome frame (Fig 91) through the connection structure 81.
  • the cantilever member of the deployable dome which is made as a rod- girder structure, has a stiffened sheet contour 83 (Fig 92) for forming the reflector contour by an edge.
  • the stiffened sheet contour i.e. reflector frame made of flat ribs or sheets, is made with an appendage on the reflector fastening side, as differed from its project outline 84, which is cut by means of controlling fastening of reflector contour standard templates 85 (Fig 93) prior to fastening the reflector thereon in such a condition when the reflector structure is in operation stress- deformed state (Fig 95).
  • the operation stress-deformed state of the reflector antenna as achieved by simulation of weightless state 86 and by deploying the deployable rim in a special meteorological environment, where the reflector antenna is subject to application of forces 87 with values and directions simulating the forces and directions of these forces transmitted after it has been fastened on the approximated surface contours of the reflector (Fig 95).
  • Determination of value and direction of power factors simulation forces transmitted by the tensioned reflector to the reflector antenna is achieved by applying the forces of such values and directions at the fastening points of the reflector to the reflector antenna which provide the project outline of the reflector in tensioned state and which is checked by the standard templates of the reflector contour.
  • the reflector being in tensioned state is bond on 88, sewed on 89, and/or keyed 90 at separate points to the contours of approximated surface having the form of the reflector, which is given by the deployable dome frame and tensioned frame (Fig 97).
  • ends 91 (Fig 98) having oval outline are attached from the both sides of the plane in parallel planes, the ends being rested, by the edge against the edge of analogous ovals made at the analogous ends of the deployable rim rods arranged on the adjacent face, in such a manner that permanent contact between them is maintained during the whole process of deployment of the rim.
  • ovals which are arranged inside the lateral faces of the pyramid frustum are elongated by means of longitudinal guides of the deployable rim rods, and the contours of ovals arranged on the opposite plane are elongated by the transverse guides of the deployable rim rods (Fig 100).
  • the ovals edges have smooth surfaces 92 or teeth 93 thereby creating the local synchronization system of the rim deployment.
  • the deployable rim rods and the additional rods are provided with temperature deformation dampers 94 (Fig 99, 100).
  • the deployable space reflector antenna "E.V.M.” has the form of prism or pyramid frustum in its folded state which, in itself, represents a transportation package. The small base of the truncated pyramid may be located both on the reflector side and its opposite side. In the folded state, the deployable space reflector antenna "E.V.M.” is connected to the spacecraft by means of a connection structure attached to the central unit or deployable dome frame.
  • connection of the reflector antenna to the spacecraft make no difficulties in terms of power and stiffening factors due to the predictability, mechanism, and control of the deployment process, as well as big stiffness in deployed state and structural peculiarities, which will be expressed in the description of the construction, followed herein after.
  • the description of the deployable rim design confirms the fact that its design may be arranged, in any particular case, on the lateral faces surfaces of the regular prism or pyramid frustum.
  • the tensioned frame of the reflector antenna can be made, in particular case, not only with sheets or membranes, but with flexible rods as well.
  • the stiffness of the design in the tensioned frame and deployable dome frame is significantly little, the manufacturing technology is relatively intricate, and both whole and local accuracies of the approximated contours created for attachment of the reflector are reduced. Deterioration of the local accuracy is caused by local convexity of the flexible rods which, in turn, is caused by the forces transferred to them from the tensioned frame. These are added by the difficulties in attachment of the reflector to the flexible rods.
  • the flexible rods made as wires, threads, ropes or ribbons have the property of "catching" which is very dangerous in a deployable structure, particularly in case where connections between the frames are made by stiff rods.
  • the flat ribs, reflector frame, and support frame have very big stiffness in the tensioned state in their plane of arrangement. This conditions the technology for obtaining the high accuracy for the approximated surface, manufacturing simplicity and, particularly, big accuracy of contours created for attaching the reflector by tensioned frame, the repeatness of the accuracy upon multiple deployments and tensioning.
  • the ribs of the tensioned frame or the frame created by it have such stiffness in its own plane that they "force" the deployable rim to take the designed position by forcible deformation thereof notwithstanding any inaccuracies of the geometry of the deployable rim taking place in its manufacturing process.
  • the tensioned frame is provided with an additional frame for increasing accuracy and stiffens, which have high degree of local stiffness in the tensioned state, it will be understood the favorable condition which is created for attaching the reflector and obtaining its precise shape.
  • the deployable space reflector antenna "E.V.M.” provides for adhesion of the reflector to the approximated contour which simplifies the technology and increases local accuracy of the reflector attachment.

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Abstract

L'invention porte sur une antenne à réflecteur spatiale déployable EVM qui comprend un cadre tendu et un cadre en forme de dôme déployable relié au cadre tendu grâce à des joints de connexion situés à l'extérieur de sa périphérie. Le cadre tendu et le cadre en forme de dôme déployable forment approximativement la surface de l'ensemble du réflecteur de l'antenne à réflecteur à laquelle le réflecteur est relié. La surface approximative forme des structures symétriques et asymétriques de réflecteurs excentrés présentant des contours de forme circulaire, ovale ou polygonale dans le plan. Ce cadre tendu est relié au rebord déployable grâce à des joints d'attache et des joints mobiles, ou seulement grâce à des joints mobiles. Le cadre en forme de dôme déployable est relié au rebord déployable grâce à des joints fixes, à des joints mobiles, et/ou au cadre tendu. Au cours du déploiement, les dimensions des contours opposés du rebord déployable sont identiques ou différents les uns des autres de l'ordre d'une valeur variable ou constante. Ce rebord déployable est installé au moyen d'un mécanisme de synchronisation de déploiement local, d'un mécanisme de fixation de déploiement local, et d'un système de déploiement mécanique. De plus, le cadre tendu est installé au moyen d'un système de stabilisation de déploiement commun et d'un système d'orientation de déploiement commun.
PCT/GE2002/000004 2001-06-12 2002-06-12 Antenne a reflecteur spatiale deployable Ceased WO2003003517A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GEAP2001004328 2001-06-12
GEAP2001004328 GEP20053604B (en) 2001-06-12 2001-06-12 Space Deployable Antenna Reflector

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WO2003003517A1 true WO2003003517A1 (fr) 2003-01-09

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CN102733524A (zh) * 2012-04-04 2012-10-17 中国航空规划建设发展有限公司 一种张拉结构和刚性结构的组合结构体系及其组合方法
EP2626951A1 (fr) * 2012-02-09 2013-08-14 NEC TOSHIBA Space Systems, Ltd. Réflecteur d'antenne déployable
WO2013135298A1 (fr) 2012-03-15 2013-09-19 European Space Agency Structure annulaire de support mécanique
WO2014068342A1 (fr) * 2012-10-19 2014-05-08 Datashvili Leri S Réflecteur spatial déployable
CN103786906A (zh) * 2014-02-18 2014-05-14 哈尔滨工业大学深圳研究生院 一种空间可展机构
US9755318B2 (en) 2014-01-09 2017-09-05 Northrop Grumman Systems Corporation Mesh reflector with truss structure
CN109449604A (zh) * 2018-12-18 2019-03-08 中国电子科技集团公司第五十四研究所 一种高精度六边形空间双层反射面天线背架
EP3353855A4 (fr) * 2015-09-25 2019-05-01 MMA Design, LLC Structure déployable destinée à être utilisée dans l'établissement d'une antenne à réseau réflecteur
CN110416741A (zh) * 2019-07-19 2019-11-05 同济大学 一种环向张拉弹性肋可展天线结构
CN112490616A (zh) * 2020-11-06 2021-03-12 东南大学 一种新型固面可展开天线结构
CN114824731A (zh) * 2022-04-21 2022-07-29 燕山大学 扭簧驱动剪铰环肋式可展开天线机构
US12444852B1 (en) 2025-06-20 2025-10-14 Pipl Limited Deployable symmetrical reflector antenna

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EP2626951A1 (fr) * 2012-02-09 2013-08-14 NEC TOSHIBA Space Systems, Ltd. Réflecteur d'antenne déployable
US9774092B2 (en) 2012-02-09 2017-09-26 Nec Space Technologies, Ltd. Deployable antenna reflector
WO2013135298A1 (fr) 2012-03-15 2013-09-19 European Space Agency Structure annulaire de support mécanique
US9153860B2 (en) 2012-03-15 2015-10-06 European Space Agency Mechanical support ring structure
CN102704607A (zh) * 2012-04-04 2012-10-03 中国航空规划建设发展有限公司 一种索穹顶结构与悬挑结构形成的组合结构及其组合方法
CN102733524A (zh) * 2012-04-04 2012-10-17 中国航空规划建设发展有限公司 一种张拉结构和刚性结构的组合结构体系及其组合方法
CN102733524B (zh) * 2012-04-04 2013-08-28 中国航空规划建设发展有限公司 一种张拉结构和刚性结构的组合结构体系的施工方法
CN102704607B (zh) * 2012-04-04 2013-08-28 中国航空规划建设发展有限公司 一种索穹顶结构与悬挑结构形成的组合结构及其组合方法
WO2014068342A1 (fr) * 2012-10-19 2014-05-08 Datashvili Leri S Réflecteur spatial déployable
EP3879626A1 (fr) * 2012-10-19 2021-09-15 Leri S. Datashvili Réflecteur spatial déployable
US9755318B2 (en) 2014-01-09 2017-09-05 Northrop Grumman Systems Corporation Mesh reflector with truss structure
CN103786906B (zh) * 2014-02-18 2017-02-08 哈尔滨工业大学深圳研究生院 一种空间可展机构
CN103786906A (zh) * 2014-02-18 2014-05-14 哈尔滨工业大学深圳研究生院 一种空间可展机构
EP3353855A4 (fr) * 2015-09-25 2019-05-01 MMA Design, LLC Structure déployable destinée à être utilisée dans l'établissement d'une antenne à réseau réflecteur
US10971793B2 (en) 2015-09-25 2021-04-06 M.M.A. Design, LLC Deployable structure for use in establishing a reflectarray antenna
US11677133B2 (en) 2015-09-25 2023-06-13 M.M.A. Design, LLC Deployable structure for use in establishing a reflectarray antenna
CN109449604A (zh) * 2018-12-18 2019-03-08 中国电子科技集团公司第五十四研究所 一种高精度六边形空间双层反射面天线背架
CN109449604B (zh) * 2018-12-18 2024-03-26 中国电子科技集团公司第五十四研究所 一种高精度六边形空间双层反射面天线背架
CN110416741A (zh) * 2019-07-19 2019-11-05 同济大学 一种环向张拉弹性肋可展天线结构
CN112490616A (zh) * 2020-11-06 2021-03-12 东南大学 一种新型固面可展开天线结构
CN112490616B (zh) * 2020-11-06 2022-11-04 东南大学 一种新型固面可展开天线结构
CN114824731A (zh) * 2022-04-21 2022-07-29 燕山大学 扭簧驱动剪铰环肋式可展开天线机构
US12444852B1 (en) 2025-06-20 2025-10-14 Pipl Limited Deployable symmetrical reflector antenna

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