EP1362386B1 - Entfaltbarer elektromagnetischer reflektor - Google Patents

Entfaltbarer elektromagnetischer reflektor Download PDF

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Publication number
EP1362386B1
EP1362386B1 EP02704870A EP02704870A EP1362386B1 EP 1362386 B1 EP1362386 B1 EP 1362386B1 EP 02704870 A EP02704870 A EP 02704870A EP 02704870 A EP02704870 A EP 02704870A EP 1362386 B1 EP1362386 B1 EP 1362386B1
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EP
European Patent Office
Prior art keywords
fact
cloth
support frame
telescopic
deployable
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP02704870A
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English (en)
French (fr)
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EP1362386A1 (de
Inventor
Philippe Mourry
Lionel Garon
Jean-Luc Pinchot
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Etienne LaCroix Tous Artifices SA
Original Assignee
Etienne LaCroix Tous Artifices SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from FR0102485A external-priority patent/FR2821491B1/fr
Priority claimed from FR0102483A external-priority patent/FR2821488B1/fr
Priority claimed from FR0102484A external-priority patent/FR2821490B1/fr
Application filed by Etienne LaCroix Tous Artifices SA filed Critical Etienne LaCroix Tous Artifices SA
Priority to EP04012193A priority Critical patent/EP1458052B1/de
Publication of EP1362386A1 publication Critical patent/EP1362386A1/de
Application granted granted Critical
Publication of EP1362386B1 publication Critical patent/EP1362386B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • H01Q15/141—Apparatus or processes specially adapted for manufacturing reflecting surfaces
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/08—Means for collapsing antennas or parts thereof
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • 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

Definitions

  • the present invention relates to the field of reflectors electromagnetic.
  • document FR-A-2 723 263 describes devices comprising a deployable support frame which carries a plurality of web segments designed to form in combination, in the state deployed, reflective polyhedra.
  • the present invention now aims to propose new means having an efficiency superior to the prior art.
  • the deployable support frame carries a plurality of elements of canvas, designed to form in combination, in the deployed state, polyhedra reflectors.
  • the deployable support frame comprises a central node which carries the extendable telescopic arm.
  • the device comprises a support frame composed of a central node which carries a telescopic main mast associated with four articulated arms.
  • the support frame may comprise a knot carrying six telescopic arms.
  • the device is arranged in octahedron.
  • an electromagnetic reflector comprising a support frame that carries at least one canvas element designed to form a reflective surface, characterized by the fact that the fabric is formed of a knitted fabric.
  • a fabric formed of a knitted fabric makes it possible to fold which leads to a very small storage space, does not present any residual fold after deployment and offers great flexibility.
  • the support frame comprises at least one sling which ensures a optimal deployment of the canvas.
  • the sling is disposed along an edge of the canvas element.
  • the device according to the present invention further comprises preferably means capable of controlling the orientation, or even the rotation, of the device, once it is deployed and dropped in free fall.
  • a reflector electromagnetic device comprising a support frame which carries a plurality of canvas elements designed to form, in combination, polyhedra reflectors, characterized in that it further comprises means for control of the aerodynamic behavior able to impose an orientation of the support frame such that it has at least one outer edge horizontal.
  • the horizontal outer edge is a lower edge of the annotation support.
  • orientation and rotation control means comprise at least a sail of levitation.
  • This frame 100 is designed to serve as support for 200 reflective fabric elements.
  • the frame 100 is also adapted for allow rapid and autonomous deployment of the reflector device according to the invention preferably having the general shape of an octahedron.
  • This frame 100 is adapted to guarantee excellent accuracy geometric (orthogonality of the faces formed by the 200 elements of canvas between them), as well as a good flatness of each panel composed by these elements, to ensure the effectiveness of the reflector.
  • the deployable support frame 100 conforms to the present invention comprises a central node 110 which carries six arms intended, after deployment, to be positioned respectively orthogonal two by two from the central node 110.
  • the deployable support frame 100 thus comprises a central telescopic mast 120 linked to the node 110 and four articulated arm 130 on the node 110.
  • the device according to the present invention in position deployed the device according to the present invention defines a structure to six orthogonal arms two by two distributed in three orthogonal planes between them each coinciding with four of said arms.
  • the central mast 120 is formed of two telescopic elements 122, 124.
  • the element 122 is formed of a rod or tube external main of the mast 120 which receives an internal sliding rod secondary, of smaller section, composing the telescopic element 124.
  • the elements 122, 124 are rectilinear and substantially similarly length.
  • auxiliary arms 130 are also rectilinear and of length substantially equal to that of the elements 122, 124 above.
  • the element 122 of the telescopic mast 120 is fixed by one end on the node 110, by its end at which the element emerges 124.
  • Node 110 is formed of a part having a through channel 112.
  • This channel 112 slidably receives the telescopic element 124 of the mast that is coaxial.
  • Node 110 also carries on its outer periphery four clevises 114 on which the pivoting arms are respectively articulated 130, around axes 116.
  • the axes 116 are transverse to the longitudinal axis of the mast 120 and of the channel 112.
  • the clevises 114 are equidistributed around the axis of the channel 112, at 90 ° from each other.
  • the axes 116 of the yokes 114 are oriented in a peripheral general direction with respect to the axis of the channel 112 and to the axis longitudinal of the mast 120.
  • the axes 116 of the yokes 114 are parallel and orthogonal respectively two by two.
  • Each pair of arms defined by the mast 120 and the auxiliary arms 130 carries a 200 canvas element of triangular general geometry.
  • the device according to the present invention defines eight Concave cube corners, as seen in Figure 17, once deployed.
  • the device according to the present invention corresponds to a octahedron.
  • each arm 130 and elements 122, 124 of the telescopic mast is of the order of 900 mm.
  • FIG. device occupies a cylindrical volume of a length of the order of 1 m and a diameter of about 55 mm.
  • the device according to the present invention is associated with a deployment means comprising a gas generator to base of a pyrotechnic material.
  • a seal such as an O-ring 142 is placed between the two telescopic elements 122, 124.
  • the element main 122 of the mast 120 is associated with a gas generator type pyrotechnic 180, which opens into the internal volume of the element 122.
  • Such a generator 180 may be formed of a structure known in itself under the name of igniter plug, fixed on the second end of the element 122, namely that opposite to the support node 110.
  • Such a generator 180 generates gas under pressure in the element 122 of the telescopic mast. The generation of gas thus applies a pressure on the element 124 and tends to deploy it telescopically in the manner of a cylinder or piston.
  • the generator 180 preferably comprises a body 182 which carries at least one pyrotechnic composition 184 associated with a primer 186 likely to be initiated by a striker 188 itself associated with a control lever or spoon 189.
  • the gas generator 180 is integrated inside the telescopic central mast 120.
  • the gases from the combustion are released in the central mast 120 which elongates (deployment of the element 124 with respect to the section of base 122) under the effect of the pressure (cylinder effect).
  • central mast 120 which ensures the deployment of the structure by pulling on the peripheral arms 130 by intermediate slings 140.
  • a sling 140 between each pair of adjacent vertices of the device, that is, between the ends of the arms 130 and the ends of the mast telescopic 120.
  • each of the six vertices of the device is connected to the four adjacent vertices via a respective sling 140.
  • the device thus comprises a total of twelve slings 140.
  • the slings 140 are preferably formed of a material low elongation such as Kevlar (registered trademark).
  • each sling 140 is equal to the length that separates two adjacent vertices of the structure, in the deployed position, from so that the slings are stretched to the expanded state of the structure and firmly hold the arms 120 and 130 firmly.
  • the gas generator 180 is adapted to define two successive regimes of separate operation: a slow phase, then a fast phase.
  • the initial slow phase allows a slow rise in pressure in the telescopic mast 120, to ensure the deployment of the structure without damage.
  • the effort during this first phase is the order of a few tens of newtons.
  • the following rapid phase corresponds to the tensioning of the reflector and requires a greater effort, typically of the order of 300 newtons.
  • the gas generator 180 may comprise, for example, as illustrated in FIG. 8, a composition packaged in the form of two sets separate 190, 192.
  • the first assembly 190 whose combustion ensures the first phase, slow, is formed of a single cylindrical block conditioned tablet in order to present a relatively slow operating regime (called "cigarette burning").
  • the second set 192 is formed of a plurality of blocks (five for example) of compressed composition which is characterized by a fast burning regime.
  • the telescopic mast 120, as well as the peripheral articulated arms 130 may be made of any suitable material. Preferably they are made of metal or composite material.
  • the deployment of the structure is operated during the displacement of the auxiliary rod 124, by through the traction then exerted on the pivoting arms 130 by the slings 140.
  • means are provided to assist the deployment of the pivoting arms 130, in the form of spring elements 170.
  • these spring elements 170 are interposed between the base element 122 of the mast telescopic 120 and respectively each of the oscillating arms 130.
  • the device can be seen in the folded position, the arms oscillating 130 being contiguous along the base element 122 of the mast telescopic 120 and the auxiliary rod 124 being retracted into the element of base 122.
  • Figure 5 shows the beginning of the deployment of the structure, the rod 124 beginning to be deployed on the outside of the base element 122 and the four arms 130 starting their pivoting, because of the traction exerted by the slings 140, assisted in this by the elastomeric springs 170.
  • the device according to the present invention further comprises a device for locking the arms 130 in position deployed.
  • Such a locking system can be the object of many embodiments.
  • Such a locking device obviously has a function to preserve the geometric precision.
  • Such a locking system also makes it possible to overcome the effects of the internal pressure drop on the telescopic mast 120 following the decrease in the temperature of the gases.
  • the means said locks are formed from a metal ring 160 designed to interfer, once the device is placed in the deployed position, with grooves 123, 125 respectively formed on the base element 122 and the telescopic element 124 of the mast 120.
  • the metal ring 160 is disposed in the node 110. At rest, the ring 160 has a diameter greater than that outside the tube telescopic 124. The ring 160 is thus placed in the groove 123 of the element 122. Thus, there is no friction between the ring 160 and the tube 124 telescopic mast.
  • the telescopic tube 124 is provided at its end internal to the base member 122 of a cone 126 flared towards its end.
  • the O-ring 140 mentioned above is preferably provided at the level of this flared cone 126.
  • the outer diameter of the cone 126 is greater than the diameter internal at rest of the ring 140.
  • the cone 126 comes to solicit and open the ring 140.
  • the cone 126 of the element telescopic 124 is provided with the groove 125 above, on its outer surface.
  • the locking device thus formed presents among other things the advantages: reduced number of parts, reliability and efficiency of locking, good temperature resistance, no friction during mast movement, and good aging.
  • each of the tubes 130, and therefore the basic element 122 and the element 124 itself of the mast 120 are each telescopic, that is to say each formed of at least two elements capable of relative sliding along their axis to ensure an increase in length.
  • This variant makes it possible at the same time to have a structure deployed of great amplitude and a reduced storage volume.
  • the support frame the aforementioned deployable 100 is associated with several canvas elements forming reflector.
  • the support frame 100 carries twelve triangular panels 200 clean to form eight concave cube corners in octahedron.
  • These panels 200 are designed to reflect the waves in a certain frequency range.
  • the panels 200 are fixed four to four on hems or textile sheaths 210 which provide the interface dressing structure in covering the arms 130 of the frame.
  • the edge of the panels 200 adjacent to the telescopic mast 120 is also fitted with a four-panel hem or scabbard.
  • the latch equipping the telescopic portion 122 is, however, wider for allow the tube to slide.
  • this hem is gathered on the folded part.
  • the hem placed on the base element 122 of the telescopic mast is preferably made of a material resistant to elevation of temperature of skin subsequent to the operation of the gas generator 180.
  • each of the panels triangular 200 is provided at its radially outer free edge a small hem 220 in which is engaged respectively one of the slings 140.
  • Each sling 140 can slide in the hem 220 associated.
  • the gas pressure generated by the gas generator 180 results in a thrust in the axis of the central mast 120 which is distributed in the slings 140 and thus allows the tensioning reflective webs 200.
  • Figure 14 illustrates the radially internal angle of a panel 200.
  • each panel 200 is provided with a reinforcement 230 to level of each of its angles.
  • Each reflector element 200 is preferably formed based on of a knitted yarn 240.
  • it is preferably a knit jersey 7 gauge made with a 242 polyester thread wrapped with a nickel thread 244 as shown in FIG. 15 (i.e., a thin strip of nickel 244 is spirally wound around the polyester yarn 242.
  • the metric number of the thread is 22 (22000 m of thread weigh 1 kg).
  • the diameter of the polyester yarn 242 is typically between 200 and 250 ⁇ m.
  • the density of the fabric is typically between 80 and 85 gr / m 2 .
  • the yarn 244 has a section oblong, for example almost rectangular, to allow a good electrical contact at each point of adjacency between two sections of wire 240.
  • This solution is used in the context of the invention because it makes it possible to have a highly conductive wire, to improve the quality of contacts elementary wire to wire while using a wire with good characteristics mechanical.
  • the jersey knitting mode allows a realization simple and inexpensive raw material for a mesh size given.
  • polyester base yarn 242 can be replaced by any equivalent material, for example polyamide.
  • nickel covering yarn 244 can be replaced by any equivalent material, for example steel or copper plus nickel.
  • each triangular panel Reflector 200 can be formed from metallized polyester tulle.
  • Such a panel based on metallized polyester tulle may be formed from cotton, silk, thermoplastic material or equivalent, arranged in a network of stitches, for example generally hexagonal mesh.
  • the metallization can be obtained by nickel deposition, for example of a thickness of the order of 1 micron.
  • the diameter of the base wire is typically of the order of 200 ⁇ m and the panel density of the order of 30 to 40 g / m 2 .
  • the device according to the present invention comprises means 300 designed to control the aerodynamic behavior of the reflector during its fall free.
  • these means 300 have the function of controlling both the orientation and the possible rotation of the reflector during its fall free.
  • the means 300 can be adapted to control a position of equilibrium not on a horizontal edge as shown on Figure 17, but on three horizontal edges.
  • the means Orientation 300 includes a parachute shaped canvas dome 310.
  • This fabric 310 may be formed for example of a very light canvas square and very porous connected to the two upper peripheral nodes 150, 152 and at both ends of the telescopic central pole 120 as seen at According to this figure, the fabric 310 is fixed directly on the knots 150, 152.
  • the fabric 310 is also connected to the ends of the telescopic central mast 120 via slings 312, 314.
  • the fabric 310 is 1060 x 1060 mm and the slings 312, 314 connecting the canvas 310 to the ends of the central mast 120 have a length of the order of 500 mm.
  • the use of a porous material to make the fabric 310 allows to remove the lift in favor of the drag without harming at the speed of fall.
  • control means 300 comprise elements 320 designed to print a rotational movement along a vertical axis during the fall reflector.
  • These means 320 have a symmetry with respect to an axis vertical passing through the center of the node 110 and the middle of one of the edges defined by a sling 140.
  • these means 320 are formed of two small triangles of very light and non-porous fabric 322, 324, arranged on the upper inclined panels arranged respectively at end of the central mast 120 and symmetrical with respect to the central node 110, that is to say placed respectively between the two sections 122, 124 of the telescopic mast 120 and the two arms 130 coplanar in a plane vertical, directed upward from the central node 110.
  • the reflective octahedron previously described can be associated with metallic or metallic flakes (chaff in terminology Anglo-Saxon).
  • octahedrons for example typically from 3 to 10, including octahedra of different size.
  • the present invention is not limited to the embodiment of an octahedron, but extends to the realization of any polyhedron.

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)
  • Optical Elements Other Than Lenses (AREA)
  • Devices For Indicating Variable Information By Combining Individual Elements (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Holo Graphy (AREA)
  • Road Signs Or Road Markings (AREA)

Claims (38)

  1. Vorrichtung, die einen elektromagnetischen Reflektor bildet, der ein faltbares Trägergestell (100) umfaßt, das wenigstens ein Planenelement (200) trägt, das dafür ausgelegt ist, im entfalteten Zustand eine reflektierende Fläche zu bilden, wobei das faltbare Trägergestell (100) wenigstens einen teleskopisch ausfahrbaren Arm (120) mit Betätigungsmitteln umfaßt, die einen Gasgenerator (180) umfassen, der in den Innenraum eines (122) der beiden Elemente (122, 124) des ausfahrbaren Teleskoparms (120) mündet, um in diesen Arm Gase unter Druck freizusetzen und ihn auszufahren, dadurch gekennzeichnet, daß der Gasgenerator ein pyrotechnischer Gasgenerator ist, der dafür ausgelegt ist, zwei Phasen festzulegen: eine erste Phase langsam steigenden Drucks gefolgt von einer Phase schneller steigenden Drucks.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Plane (200) aus einem gewirkten Textilstoff besteht.
  3. Vorrichtung nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß sie Mittel (310, 322, 324) umfaßt, die die Steuerung der Ausrichtung und der Rotation der Konstruktion bereitstellen.
  4. Vorrichtung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß sie Mittel zur Steuerung des aerodynamischen Verhaltens (310, 322, 324) umfaßt, die dafür eingerichtet sind eine solche Ausrichtung des faltbaren Trägergestells herbeizuführen, daß dieses wenigstens eine horizontale äußere Kante hat.
  5. Vorrichtung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß das faltbare Trägergestell (100) mehrere Planenelemente (200) trägt, die dafür konzipiert sind im entfalteten Zustand in ihrem Zusammenwirken Reflektionspolyeder zu bilden.
  6. Vorrichtung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das faltbare Trägergestell (100) einen Zentralknoten (110) umfaßt, der wenigstens den ausfahrbaren Teleskoparm trägt.
  7. Vorrichtung nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß das Trägergestell (100) einen Teleskopmast (120), der mit dem Zentralknoten (110) verbunden ist, und mehrere zentrale schwenkbare Arme, die am Zentralknoten (110) gelenkig montiert sind, umfaßt.
  8. Vorrichtung nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß das Trägergestell (100) einen Teleskopmast (120) umfaßt, der einen Hauptabschnitt (122) umfaßt, in dem wenigstens ein zusätzlicher Abschnitt (124) verschiebbar aufgenommen ist, dadurch gekennzeichnet, daß der Hauptabschnitt (122) mit seinem offenen Ende, aus dem der zusätzliche Arm (124) hervorkommt, am Zentralknoten (110) befestigt ist.
  9. Vorrichtung nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß das Trägergestell (100) einen Teleskopmast (120) und vier schwenkbare Arme (130) umfaßt.
  10. Vorrichtung nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, daß jeder Arm (120, 130) des Trägergestells (100) teleskopisch ist und mit einem Zentralknoten (110) verbunden ist.
  11. Vorrichtung nach Anspruch 10, dadurch gekennzeichnet, daß das faltbare Trägergestell (100) sechs Teleskoparme umfaßt.
  12. Vorrichtung nach einem der Ansprüche 1 bis 11, dadurch gekennzeichnet, daß es Mittel (170) umfaßt, die dafür eingerichtet sind, auf schwenkbare Arme (130) eine Ausbreitungswirkung auszuüben.
  13. Vorrichtung nach Anspruch 12, dadurch gekennzeichnet, daß die Mittel, die auf die schwenkbaren Arme (130) einwirken, Schnüre (140) umfassen.
  14. Vorrichtung nach einem der Ansprüche 12 oder 13, dadurch gekennzeichnet, daß die Mittel, die auf die schwenkbaren Arme (130) einwirken, Elastomerblöcke (170) umfassen.
  15. Vorrichtung nach einem der Ansprüche 1 bis 14, dadurch gekennzeichnet, daß es außerdem Mittel (160) umfaßt, die dafür eingerichtet sind, die Verriegelung des Teleskoparms (120) in der ausgefahrenen Stellung bereitzustellen.
  16. Vorrichtung nach Anspruch 15, dadurch gekennzeichnet, daß die Verriegelungsmittel einen elastischen Sprengring (160) umfassen.
  17. Vorrichtung nach einem der Ansprüche 15 oder 16, dadurch gekennzeichnet, daß eines der Elemente (124) des ausfahrbaren Teleskoparms mit einem Konus (126) ausgestattet ist, der dafür eingerichtet ist, beim Ausfahren des ausfahrbaren Teleskoparms die Spreizung eines Verriegelungssprengrings (160) derart herbeizuführen, daß der Sprengring (160), nachdem er expandiert ist, mit Rillen zusammenwirkt, die jeweils auf den beiden Elementen vorgesehen sind, die zu der relativen Teleskopbewegung fähig sind.
  18. Vorrichtung nach einem der Ansprüche 1 bis 17, dadurch gekennzeichnet, daß sie acht Ecken eines Kubus in Oktaederform definiert.
  19. Vorrichtung nach einem der Ansprüche 1 bis 18, dadurch gekennzeichnet, daß die Plane (200) aus einem Jerseygewebe Teilung 7 besteht.
  20. Vorrichtung nach einem der Ansprüche 1 bis 18, dadurch gekennzeichnet, daß die Plane (200) aus einem metallisierten Polyestertüll besteht.
  21. Vorrichtung nach einem der Ansprüche 1 bis 20, dadurch gekennzeichnet, daß die Plane (200) aus einem thermoplastischen Faden besteht, beispielsweise auf der Basis von Polyester, der metallumsponnen ist, beispielsweise mit Nickel.
  22. Vorrichtung nach einem der Ansprüche 1 bis 21, dadurch gekennzeichnet, daß die Plane einen metallischen Umspinnungsfaden (244) mit länglichem Querschnitt umfaßt.
  23. Vorrichtung nach einem der Ansprüche 1 bis 22, dadurch gekennzeichnet, daß die Plane (200) auf den Armen (120, 130) des faltbaren Trägergestells (100) durch Säume (210) angebracht ist, die im Bereich der Kanten der Plane (200) ausgebildet sind.
  24. Vorrichtung nach einem der Ansprüche 1 bis 23, dadurch gekennzeichnet, daß sie Mittel zu Steuerung des aerodynamischen Verhaltens umfaßt, die ein Auftriebssegel (310) umfassen.
  25. Vorrichtung nach Anspruch 24, dadurch gekennzeichnet, daß das Auftriebssegel (310) aus einer porigen Plane gebildet ist.
  26. Vorrichtung nach einem der Ansprüche 24 oder 25, dadurch gekennzeichnet, daß das Auftriebssegel (310) zum einen an zwei Spitzen (150, 152) des faltbaren Trägergestells (100) und zum anderen über Schnüre (312, 314) an den zwei Enden eines Teleskopmastes (120) aufgehängt ist.
  27. Vorrichtung nach einem der Ansprüche 1 bis 26, dadurch gekennzeichnet, daß sie Mittel zu Steuerung des aerodynamischen Verhaltens umfaßt, die symmetrische Mittel (322, 324) umfassen, die dafür eingerichtet sind, eine Rotation der Konstruktion um eine vertikale Achse herbeizuführen.
  28. Vorrichtung nach Anspruch 27, dadurch gekennzeichnet, daß die Mittel zur Steuerung der Rotation zwei symmetrische Planen (322, 324) umfassen.
  29. Vorrichtung nach Anspruch 27, dadurch gekennzeichnet, daß die Mittel zur Steuerung der Rotation Öffnungen umfassen, die in Planen der Vorrichtung ausgebildet sind.
  30. Vorrichtung nach Anspruch 28, dadurch gekennzeichnet, daß die zwei Planen (322, 324) zwischen einem Teleskopmast (120) und den Schnüren (140) befestigt sind.
  31. Vorrichtung nach einem der Ansprüche 1 bis 30, dadurch gekennzeichnet, daß sie Mittel zu Steuerung des aerodynamischen Verhaltens (310, 322, 324) umfaßt, die dafür eingerichtet sind, eine Ausrichtung des faltbaren Trägergestells herbeizuführen, derart, daß dieses wenigstens eine untere horizontale Kante aufweist.
  32. Vorrichtung nach einem der Ansprüche 1 bis 31, dadurch gekennzeichnet, daß sie Mittel zu Steuerung des aerodynamischen Verhaltens (310, 322, 324) umfaßt, die dafür eingerichtet sind, eine Ausrichtung der faltbaren Trägerkonstruktion (100) herbeizuführen, derart, daß diese drei untere Kanten in einer horizontalen Ebene aufweist.
  33. Vorrichtung nach einem der Ansprüche 1 bis 32, dadurch gekennzeichnet, daß der pyrotechnische Generator zwei Blöcke mit pyrotechnischer Mischung (190, 192) umfaßt, die verschiedene Verbrennungseigenschaften haben, die dafür geeignet sind, zwei aufeinanderfolgende Phasen zu definieren, die eine zu Anfang und mit langsamem Druckanstieg, die andere mit schnellerem Druckanstieg.
  34. Vorrichtung nach einem der Ansprüche 1 bis 33, dadurch gekennzeichnet, daß sie Schnüre (140) umfaßt, die zwischen zwei Spitzen der faltbaren Konstruktion (100) befestigt sind.
  35. Vorrichtung nach Anspruch 34, dadurch gekennzeichnet, daß die Schnüre (140) in Säumen angeordnet sind, die an den Rändern der Plane (200) ausgebildet sind.
  36. Vorrichtung nach einem der Ansprüche 1 bis 35, dadurch gekennzeichnet, daß sie zwölf Schnüre (140) umfaßt.
  37. Vorrichtung nach einem der Ansprüche 1 bis 36, dadurch gekennzeichnet, daß das Trägergestell (100) wenigstens eine Schnur (140) umfaßt, die ein optimales Entfalten der Plane (200) bereitstellt.
  38. Vorrichtung nach Anspruch 37, dadurch gekennzeichnet, daß die Schnur (140) entlang einer Kante des Planenelements (200) angeordnet ist.
EP02704870A 2001-02-23 2002-02-21 Entfaltbarer elektromagnetischer reflektor Expired - Lifetime EP1362386B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04012193A EP1458052B1 (de) 2001-02-23 2002-02-21 Entfaltbarer Elektromagnetischer Reflektor

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
FR0102485A FR2821491B1 (fr) 2001-02-23 2001-02-23 Reflecteur electromagnetique deployable
FR0102483A FR2821488B1 (fr) 2001-02-23 2001-02-23 Reflecteur electromagnetique deployable
FR0102485 2001-02-23
FR0102484A FR2821490B1 (fr) 2001-02-23 2001-02-23 Reflecteur electromagnetique deployable
FR0102484 2001-02-23
FR0102483 2001-02-23
PCT/FR2002/000648 WO2002069441A1 (fr) 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP04012193A Division EP1458052B1 (de) 2001-02-23 2002-02-21 Entfaltbarer Elektromagnetischer Reflektor

Publications (2)

Publication Number Publication Date
EP1362386A1 EP1362386A1 (de) 2003-11-19
EP1362386B1 true EP1362386B1 (de) 2005-11-23

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EP02704870A Expired - Lifetime EP1362386B1 (de) 2001-02-23 2002-02-21 Entfaltbarer elektromagnetischer reflektor
EP04012193A Expired - Lifetime EP1458052B1 (de) 2001-02-23 2002-02-21 Entfaltbarer Elektromagnetischer Reflektor

Family Applications After (1)

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EP04012193A Expired - Lifetime EP1458052B1 (de) 2001-02-23 2002-02-21 Entfaltbarer Elektromagnetischer Reflektor

Country Status (9)

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US (1) US6791486B2 (de)
EP (2) EP1362386B1 (de)
JP (1) JP2004521544A (de)
AT (2) ATE363742T1 (de)
DE (2) DE60207529T2 (de)
DK (2) DK1458052T3 (de)
ES (1) ES2249555T3 (de)
IL (1) IL152430A (de)
WO (1) WO2002069441A1 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE363742T1 (de) * 2001-02-23 2007-06-15 Lacroix Soc E Entfaltbarer elektromagnetischer reflektor
IL158468A0 (en) * 2003-10-19 2004-08-31 Rafael Armament Dev Authority Parachuted radar decoy
JP6184066B2 (ja) * 2012-08-31 2017-08-23 株式会社パスコ 対空標識

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB812376A (en) 1956-01-03 1959-04-22 Anthony Edgar Porter Improvements in radar reflectors
US746300A (en) * 1903-01-14 1903-12-08 Thomas E Davis Cash-register.
US2534716A (en) * 1945-10-08 1950-12-19 Emmett L Hudspeth Inflatable radar reflector buoy
US2576255A (en) * 1948-06-15 1951-11-27 Emmett L Hudspeth Reflecting fabric
GB746300A (en) * 1954-02-12 1956-03-14 Anthony Edgar Porter Improvements in radar reflectors
US3047860A (en) * 1957-11-27 1962-07-31 Austin B Swallow Two ply electromagnetic energy reflecting fabric
US3296617A (en) * 1963-01-23 1967-01-03 Francis M Rogallo Target kite
US3283328A (en) * 1963-11-13 1966-11-01 Bendix Corp Sounding balloon and target assembly
US3618111A (en) * 1967-04-28 1971-11-02 Gen Dynamics Corp Expandable truss paraboloidal antenna
AR209680A1 (es) * 1975-09-22 1977-05-13 Jouanno R Perfeccionamientos introducidos en un reflector de radar plegable
US6507307B1 (en) * 1982-05-14 2003-01-14 Lockheed Martin Corporation Ram-air inflated, passive decoy for millimeter wave frequencies
JPS62168790A (ja) * 1986-01-20 1987-07-25 三菱電機株式会社 飛行体
EP0290124A3 (de) * 1987-05-07 1990-03-21 Trw Inc. Hybrides Netz und Mikrowellenreflector mit einem solchen Netz
JPS63284099A (ja) * 1987-05-15 1988-11-21 株式会社島津製作所 宇宙空間用アンテナ展開形成装置
JP2635812B2 (ja) * 1990-10-25 1997-07-30 株式会社宇宙通信基礎技術研究所 伸長構造体の伸長装置
JP2555982Y2 (ja) * 1991-12-13 1997-11-26 日本飛行機株式会社 レーダ用レフレクタ
FR2690172B1 (fr) * 1992-04-21 1995-05-19 Protecma Structure métallique pouvant être incorporée à l'intérieur de matières plastiques et articles moulés comportant une telle structure.
US5451975A (en) * 1993-02-17 1995-09-19 Space Systems/Loral, Inc. Furlable solid surface reflector
US5864324A (en) * 1996-05-15 1999-01-26 Trw Inc. Telescoping deployable antenna reflector and method of deployment
JP2802368B2 (ja) * 1996-11-26 1998-09-24 防衛庁技術研究本部長 浮遊式電子装置のスピン抑制機構
FR2793608B1 (fr) * 1999-05-10 2001-09-14 Aerospatiale Lanceurs Strategi Surface reflechissant les ondes electromagnetiques et procede pour sa realisation
JP2002111370A (ja) * 2000-09-26 2002-04-12 Japan Aircraft Mfg Co Ltd レーダー用リフレクタ装置
ATE363742T1 (de) * 2001-02-23 2007-06-15 Lacroix Soc E Entfaltbarer elektromagnetischer reflektor

Also Published As

Publication number Publication date
US20030164788A1 (en) 2003-09-04
DE60220440D1 (de) 2007-07-12
DE60220440T2 (de) 2008-05-21
IL152430A (en) 2007-10-31
ATE311019T1 (de) 2005-12-15
EP1458052A1 (de) 2004-09-15
DK1458052T3 (da) 2007-09-10
ES2249555T3 (es) 2006-04-01
ATE363742T1 (de) 2007-06-15
WO2002069441A1 (fr) 2002-09-06
EP1458052B1 (de) 2007-05-30
US6791486B2 (en) 2004-09-14
DE60207529D1 (de) 2005-12-29
DE60207529T2 (de) 2006-08-10
EP1362386A1 (de) 2003-11-19
DK1362386T3 (da) 2006-04-03
IL152430A0 (en) 2003-05-29
JP2004521544A (ja) 2004-07-15

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