EP1458052B1 - Reflecteur electromagnetique deployable - Google Patents

Reflecteur electromagnetique deployable Download PDF

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Publication number
EP1458052B1
EP1458052B1 EP04012193A EP04012193A EP1458052B1 EP 1458052 B1 EP1458052 B1 EP 1458052B1 EP 04012193 A EP04012193 A EP 04012193A EP 04012193 A EP04012193 A EP 04012193A EP 1458052 B1 EP1458052 B1 EP 1458052B1
Authority
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
EP04012193A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1458052A1 (fr
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 FR0102483A external-priority patent/FR2821488B1/fr
Priority claimed from FR0102484A external-priority patent/FR2821490B1/fr
Priority claimed from FR0102485A external-priority patent/FR2821491B1/fr
Application filed by Etienne LaCroix Tous Artifices SA filed Critical Etienne LaCroix Tous Artifices SA
Publication of EP1458052A1 publication Critical patent/EP1458052A1/fr
Application granted granted Critical
Publication of EP1458052B1 publication Critical patent/EP1458052B1/fr
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 electromagnetic reflectors.
  • electromagnetic reflectors such as, and not limited to, the use in the form of marker beacons, for example for mobile vehicles.
  • FR-A-2 723 263 discloses devices comprising a deployable support frame carrying a plurality of web segments adapted to form reflective polyhedra in the expanded state.
  • US 3,296,617 describes a deployable antenna allowing the structure to fly.
  • the Applicant has determined that this characteristic is important for obtaining a high level average response.
  • the horizontal outer edge is a lower edge of the support frame.
  • orientation and rotation control means comprise at least one lift sail.
  • This frame 100 is designed to serve as a support for elements 200 of reflective fabric.
  • the frame 100 is also adapted for allow a rapid and autonomous deployment of the reflector device according to the invention preferably having the general shape of an octahedron.
  • This reinforcement 100 is adapted to guarantee excellent geometric precision (orthogonality of the faces formed by the elements 200 of fabric between them), as well as good flatness of each panel composed by these elements, to guarantee the effectiveness of the reflector.
  • the deployable support armature 100 comprises a central node 110 which carries six arms intended, after deployment, to be positioned respectively orthogonal in pairs from the central node 110.
  • the deployable support armature 100 thus comprises a central telescopic mast 120 connected to the node 110 and four arms 130 articulated on the node 110.
  • the device according to the present invention in the deployed position defines a structure with six arms orthogonal 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 external main tube of the mast 120 which receives at internal sliding a secondary rod, of smaller section, constituting the telescopic element 124.
  • the elements 122, 124 are rectilinear and substantially the same length.
  • auxiliary arms 130 are also straight and of a length substantially equal to that of the elements 122, 124 above.
  • the element 122 of the telescopic mast 120 is fixed at one end to the node 110, at its end at which the element 124 emerges.
  • Node 110 is formed of a part having a through channel 112.
  • This channel 112 slidably receives the telescopic element 124 of the mast which is coaxial with it.
  • the node 110 also carries on its outer periphery four yokes 114 on which the pivoting arms 130 are articulated, respectively, about axes 116.
  • the axes 116 are transverse to the longitudinal axis of the mast 120 and the channel 112.
  • the yokes 114 are evenly distributed around the axis of the channel 112, at 90 ° to each other.
  • the axes 116 of the yokes 114 are oriented in a general peripheral direction relative to the axis of the channel 112 and to the longitudinal axis 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 fabric element 200 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 an octahedron.
  • each arm 130 and the elements 122, 124 of the telescopic mast is of the order of 900 mm.
  • the device according to the present invention occupies a cylindrical volume with 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 based on a pyrotechnic material.
  • a seal such as an O-ring 142 is placed between the two telescopic elements 122, 124.
  • the main element 122 of the mast 120 is associated with a pyrotechnic type gas generator 180, which opens into the internal volume of the element 122.
  • Such a generator 180 may be formed of a structure known per se 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 pressurized gases in the element 122 of the telescopic mast. The generation of gases 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 capable of being 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 into the central mast 120 which elongates (deployment of the element 124 relative to the base portion 122) under the effect of pressure (cylinder effect).
  • a sling 140 between each pair of adjacent vertices of the device, that is to say between the ends of the arms 130 and the ends of the telescopic mast 120.
  • each of the six vertices of the device is connected to the four adjacent vertices by means of a respective sling 140.
  • the device thus comprises a total of twelve slings 140.
  • the slings 140 are preferably formed of a low elongation material such as Kevlar (trademark).
  • each sling 140 is equal to the length between two adjacent vertices of the structure, in the extended position, so that the slings are stretched in the deployed state of the structure and firmly hold the arms 120 and 130 firmly.
  • the gas generator 180 is adapted to define two distinct successive operating regimes: a slow phase, then a fast phase.
  • the initial slow phase allows a rise in slow pressure in the telescopic mast 120, to ensure the deployment of the structure without damaging it.
  • the effort during this first phase is of 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. FIG. 8, a composition packaged in the form of two distinct sets 190, 192.
  • the first assembly 190 whose combustion ensures the first phase, slow, is formed of a single cylindrical block compressed conditioned to have a relatively slow operating regime (combustion called "cigarette").
  • the second set 192 is formed of a plurality of blocks (five for example) of compressed composition which is characterized by a fast combustion 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 based on composite material.
  • the deployment of the structure is made during the displacement of the auxiliary rod 124, by means of the traction then exerted on the pivoting arms 130 by the slings 140.
  • means are provided assisting 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 telescopic mast 120 and respectively each of the oscillating arms 130.
  • an elastomer block 170 close to the central support node 110, between the telescopic mast 120 and each oscillating arm 130.
  • the device is seen in the folded position, the oscillating arms 130 being contiguous along the base element 122 of the telescopic mast 120 and the auxiliary rod 124 being retracted into the base element 122.
  • FIG. 5 the beginning of the deployment of the structure is illustrated, the rod 124 beginning to be deployed on the outside of the base element 122 and the four arms 130 starting their pivoting, due to the traction exerted by the slings 140, assisted in this by the elastomer springs 170.
  • FIG. 6 shows the structure according to the present invention in the deployed state, the four oscillating arms 130 then being coplanar in a plane orthogonal to the axis of the central mast 120 and the twelve slings 140 being placed in position. tense.
  • the device according to the present invention further comprises an arm locking device 130 in the deployed position.
  • Such a locking system can be the subject of many embodiments.
  • Such a locking device obviously has the function of preserving geometric accuracy.
  • Such a locking system also makes it possible to overcome the effects of the internal pressure drop at the telescopic mast 120 following the decrease in the temperature of the gases.
  • the aforementioned locking means are formed based on a metal ring 160 designed to interfere, once the device placed in the deployed position, with grooves 123, 125 formed respectively on the base member 122 and the telescopic member 124 of the mast 120.
  • the metal ring 160 is disposed in the node 110. At rest, the ring 160 has a larger diameter than the outer diameter of the telescopic tube 124. The ring 160 is thus placed in the groove 123 of the base member 122. Thus, there is no friction between the ring 160 and the tube 124 of the telescopic mast.
  • the telescopic tube 124 is provided at its inner end to the base member 122 of a cone 126 flared towards its end.
  • the O-ring 140 mentioned above is preferably provided at this flared cone 126.
  • the outer diameter of the cone 126 is greater than the internal diameter at rest of the ring 140.
  • the cone 126 comes to urge and open the ring 140.
  • the cone 126 of the telescopic element 124 is provided with the groove 125 above, on its outer surface.
  • the locking device thus formed has among others the following advantages: reduced number of parts, reliability and effectiveness of locking, good temperature resistance, no friction during movement of the mast, and good aging.
  • each of the tubes 130, and consequently the base 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 allows both to have a deployed structure of large amplitude and a reduced storage volume.
  • the above-mentioned deployable support armature 100 is associated with several reflective fabric elements.
  • the support frame 100 carries twelve triangular panels 200 adapted to form eight corners of concave cube octahedron.
  • These panels 200 are designed to reflect the electromagnetic waves in a certain frequency range.
  • the panels 200 are fixed four by four on hems or textile sheaths 210 which provide the interface structure covering covering the arms 130 of the frame.
  • the edge of the panels 200 adjacent to the telescopic pole 120 is also provided with a common four-panel hem or sleeve.
  • the latch equipping the telescopic portion 122 is however wider to 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 the elevation of the skin temperature consecutive to the operation of the gas generator 180.
  • each of the triangular panels 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 is reflected in a thrust in the axis of the central mast 120 which is distributed in the slings 140 and thus allows the tensioning of the reflective fabrics 200.
  • Figure 14 illustrates the radially internal angle of a panel 200.
  • each panel 200 is provided with a reinforcement 230 at each of its angles.
  • Each reflective element 200 is preferably formed from a knitted yarn 240.
  • it is preferably a 7 gauge jersey fabric made with a polyester yarn 242 covered with a nickel thread 244 as illustrated in FIG. 15 (that is to say that a thin strip of nickel 244 is wound spirally 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 wrapping wire 244 has a generally oblong, for example almost rectangular, section to allow a good electrical contact at each point of adjacency between two sections of the wire 240.
  • the jersey knitting mode allows a simple and inexpensive realization of raw material for a given mesh size.
  • polyester base yarn 242 may be replaced by any equivalent material, for example polyamide.
  • covering yarn 244 nickel can be replaced by any equivalent material, for example steel or copper plus nickel.
  • each triangular reflector panel 200 may be formed based on 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 free fall.
  • these means 300 have the function of controlling both the orientation and the possible rotation of the reflector during its free fall.
  • the means 300 may be adapted to control an equilibrium position not on a horizontal edge as shown in Fig. 17, but on three horizontal edges.
  • the orientation means 300 comprise a fabric dome 310 in the form of a parachute.
  • This fabric 310 may be formed for example of a very light and very porous fabric square connected to the two upper peripheral nodes 150, 152 and at both ends of the telescopic central pole 120 as can be seen in FIG. 17. According to this figure, the fabric 310 is attached directly to the upper nodes 150, 152. The fabric 310 is also connected to the ends of the central telescopic pole 120 by means of slings 312, 314.
  • the fabric 310 is 1060 x 1060 mm and the slings 312, 314 connecting the fabric 310 to the ends of the central mast 120 have a length of the order of 500 mm.
  • control means 300 preferably comprise elements 320 designed to print a rotational movement, along a vertical axis, during the fall of the reflector.
  • These means 320 have a symmetry with respect to a vertical axis 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 disposed respectively at the 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 vertical plane, directed upwards from the central node 110.
  • the reflective octahedron previously described may be associated with metallic or metallized flakes (chaff in English terminology).
  • octahedrons for example typically from 3 to 10, including octahedra of different size.
  • provision may be made to complete or replace the cloth triangles 322, 324 ensuring the rotation by symmetrical or asymmetrical holes formed in the reflector panels.
  • the present invention is not limited to producing an octahedron, but extends to the production of any polyhedron.

Landscapes

  • 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)
  • Holo Graphy (AREA)
  • Road Signs Or Road Markings (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
EP04012193A 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable Expired - Lifetime EP1458052B1 (fr)

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
FR0102483 2001-02-23
FR0102483A FR2821488B1 (fr) 2001-02-23 2001-02-23 Reflecteur electromagnetique deployable
FR0102484A FR2821490B1 (fr) 2001-02-23 2001-02-23 Reflecteur electromagnetique deployable
FR0102485A FR2821491B1 (fr) 2001-02-23 2001-02-23 Reflecteur electromagnetique deployable
FR0102485 2001-02-23
FR0102484 2001-02-23
EP02704870A EP1362386B1 (fr) 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP02704870A Division EP1362386B1 (fr) 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable

Publications (2)

Publication Number Publication Date
EP1458052A1 EP1458052A1 (fr) 2004-09-15
EP1458052B1 true EP1458052B1 (fr) 2007-05-30

Family

ID=27248746

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04012193A Expired - Lifetime EP1458052B1 (fr) 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable
EP02704870A Expired - Lifetime EP1362386B1 (fr) 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP02704870A Expired - Lifetime EP1362386B1 (fr) 2001-02-23 2002-02-21 Reflecteur electromagnetique deployable

Country Status (9)

Country Link
US (1) US6791486B2 (da)
EP (2) EP1458052B1 (da)
JP (1) JP2004521544A (da)
AT (2) ATE311019T1 (da)
DE (2) DE60220440T2 (da)
DK (2) DK1458052T3 (da)
ES (1) ES2249555T3 (da)
IL (1) IL152430A (da)
WO (1) WO2002069441A1 (da)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DK1458052T3 (da) * 2001-02-23 2007-09-10 Lacroix Soc E Udfoldelig elektromagnetisk 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

Family Cites Families (23)

* 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 (en) * 1987-05-07 1990-03-21 Trw Inc. Hybrid mesh and rf reflector embodying the mesh
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
DK1458052T3 (da) * 2001-02-23 2007-09-10 Lacroix Soc E Udfoldelig elektromagnetisk reflektor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP1458052A1 (fr) 2004-09-15
US20030164788A1 (en) 2003-09-04
IL152430A0 (en) 2003-05-29
DK1458052T3 (da) 2007-09-10
DK1362386T3 (da) 2006-04-03
WO2002069441A1 (fr) 2002-09-06
DE60207529T2 (de) 2006-08-10
EP1362386A1 (fr) 2003-11-19
JP2004521544A (ja) 2004-07-15
ATE311019T1 (de) 2005-12-15
ATE363742T1 (de) 2007-06-15
DE60220440D1 (de) 2007-07-12
EP1362386B1 (fr) 2005-11-23
DE60220440T2 (de) 2008-05-21
ES2249555T3 (es) 2006-04-01
US6791486B2 (en) 2004-09-14
IL152430A (en) 2007-10-31
DE60207529D1 (de) 2005-12-29

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