FR2821491A1 - Unfoldable electro-magnetic reflector incorporating a telescopic arm in the unfoldable support frame for the fabric element which forms the reflector surface - Google Patents

Abstract

A device forming an electro-magnetic reflector, comprising an unfoldable support frame carrying at least one fabric element which unfolds to form a reflector surface, has an unfoldable support frame that includes at least one unfoldable, telescopic arm (120).

Description

<Desc / Clms Page number 1>

 The present invention relates to the field of electromagnetic reflectors.

 It relates to all the potential applications of electromagnetic reflectors, such as, and not limited to, the use in the form of tracking beacons, for example for mobile vehicles.

 Numerous means have already been proposed forming an electromagnetic reflector.

EP 0 182 274, FR 1 226 263, GB 913 547, US 3 217 325, US 3 041 604, US 3 115 631, US 3 568 191, GB 2 188 783, GB 2 189 079, FR 2 073 370, US 4 119 965, US 4 096 479, US 4 072 948, US 3 660 843, US 3 276 017. Reference may be made, for example, to documents FR-A-2 723 263,

EP 0 182 274, FR 1 226 263, GB 913 547, US 3 217 325, US 3 041 604, US 3 115 631, US 3 568 191, GB 2 188 783, GB 2 189 079, FR 2 073 370, US 4,119,965, US 4,096,479, US 4,072,948, US 3,660,843, US 3,276,017.

 For example, in document FR-A-2 723 263, devices have been described comprising a deployable support frame which carries a plurality of fabric segments designed to form, in the deployed state, reflective polyhedra.

 The present invention now aims to propose new means having greater efficiency than the prior art.

déployable qui porte au moins un élément de toile conçu pour former, à l'état déployé, une surface réflectrice, caractérisé par le fait que l'armature support déployable comprend au moins un bras déployable télescopique. These aims are achieved in the context of the present invention by means of an electromagnetic reflector comprising a support frame.

deployable which carries at least one fabric element designed to form, in the deployed state, a reflective surface, characterized in that the deployable support frame comprises at least one telescopic deployable arm.

 The Applicant has in fact found, after numerous tests and studies, that the use of such a telescopic deployable arm allows perfectly flat deployment of each fabric element, leading to a behavior of the reflector which is greater than that of known prior devices.

 According to another advantageous characteristic of the present invention, the deployable support frame carries a plurality of elements of

<Desc / Clms Page number 2>

 canvas, designed to form in combination, in the deployed state, reflective polyhedra.

 According to another advantageous characteristic of the present invention, the deployable support frame comprises a central node which carries the telescopic deployable arm.

 According to an advantageous embodiment of the present invention, the device comprises a support frame composed of a central node which carries a telescopic main mast associated with four articulated arms.

 Alternatively, the support frame may include a node carrying six telescopic arms.

 According to another advantageous characteristic of the present invention, the device is arranged in octahedron.

 According to another advantageous characteristic of the present invention, the canvas is formed of a knitted fabric.

 The Applicant has indeed found that such a fabric accepts a certain elongation to allow optimal deployment.

 Furthermore, a canvas formed of a knitted fabric allows folding which results in very little space during storage, does not have any residual folds after deployment and offers great flexibility.

 The device according to the present invention further preferably comprises means capable of controlling the orientation, or even the rotation, of the device, once it has been deployed and released in free fall.

 According to an advantageous characteristic of the present invention, such means of orientation and rotation control comprise at least one lifting sail.

 Other characteristics, aims and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given by way of nonlimiting example, and in which:

<Desc / Clms Page number 3>

 - Figure 1 shows a general schematic perspective view of a device according to the present invention, - Figure 2 shows a partial view of a support frame according to the present invention, partially deployed, - Figure 3 shows the same support frame according to the present invention, in the folded position, - Figures 4,5 and 6 schematically represent the device according to the present invention at three successive stages of its deployment phase, - Figure 7 shows a curve illustrating the rise in gas pressure of a pyrotechnic generator ensuring deployment, as a function of time, - Figure 8 schematically shows a preferred arrangement of pyrotechnic means capable of generating deployment gases, in accordance with the invention, - Figures 9, 10 , 11 and 12 represent means for locking a telescopic mast according to the present invention during four stages s successive deployment, - Figure 13 shows a partial view of a canvas element according to the invention at one of its radially external angles cooperating with an arm and a sling, - Figure 14 shows a view detail of a fabric in its radially internal angular zone cooperating with two arms, near the central node, - Figure 15 shows a wrapped wire preferably used in the context of the invention for the production of the fabric, - the FIG. 16 schematically represents the stitches of a knitted fabric according to the invention, and

<Desc / Clms Page number 4>

 - Figure 17 schematically illustrates the device according to the present invention in the deployed position, in particular equipped with means for controlling aerodynamic behavior.

 We will first describe the structure of the deployable support frame 100 according to the present invention.

 This frame 100 is designed to serve as a support for elements 200 of reflective fabric. The frame 100 is further adapted to 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 geometric precision (orthogonality of the faces formed by the fabric elements 200 between them), as well as good flatness of each panel made up of these elements, to guarantee the efficiency of the reflector.

 Essentially, the deployable support frame 100 according 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.

 More precisely still, according to the preferred embodiment illustrated in the appended figures, the deployable support frame 100 thus comprises a telescopic central mast 120 linked to the node 110 and four arms 130 articulated on the node 110.

 Thus, as can be seen in the appended FIG. 1, in the deployed position, the device according to the present invention defines a structure with six orthogonal arms two by two distributed in three orthogonal planes between them each coinciding with four of said arms.

 More precisely still, according to the preferred embodiment illustrated in the appended figures, the central mast 120 is formed of two telescopic elements 122,124. The element 122 is formed of an external main rod or tube of the mast 120 which receives, internally sliding, a secondary rod, of smaller section, making up the telescopic element 124.

<Desc / Clms Page number 5>

 The elements 122, 124 are rectilinear and substantially the same length.

 Furthermore, the auxiliary arms 130 are also rectilinear and of length substantially equal to that of the above-mentioned elements 122,124.

 The element 122 of the telescopic mast 120 is fixed by one end to the node 110, by its end at the level of which the element 124 emerges.

The 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 respectively articulated, around axes 116.

 The axes 116 are transverse to the longitudinal axis of the mast 120 and the channel 112. The yokes 114 are equally distributed around the axis of the channel 112, 90 from one another.

 Thus, 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 an element 200 of canvas of general triangular geometry.

Thus, the device according to the present invention defines eight concave cube corners, as seen in Figure 17, once deployed.

Thus, the device according to the present invention corresponds to an octahedron.

 By way of nonlimiting example, the length of each arm 130 and of the elements 122, 124 of the telescopic mast is of the order of 900 mm.

<Desc / Clms Page number 6>

Furthermore, in the folded state, as illustrated in FIG. 3, the device according to the present invention occupies a cylindrical volume with a length of the order of 1 m and a diameter of the order of 55 mm .

 Preferably, the device according to the present invention is associated with a deployment means comprising a gas generator based on a pyrotechnic material.

 For this purpose, a seal, such as an O-ring 142 is placed between the two telescopic elements 122,124. And the main element 122 of the mast 120 is associated with a gas generator of the pyrotechnic type 180, which opens into the internal volume of the element 122.

 Such a generator 180 can 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 the support node 110.

 The general structure of a gas generator 180 being known to those skilled in the art, this will not be described in detail below.

 Those skilled in the art will understand that such a generator 180 generates gases under pressure in the element 122 of the telescopic mast. The generation of gases thus applies pressure to the element 124 and tends to deploy the latter telescopically in the manner of a jack or piston.

 Essentially, 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 use of a pyrotechnic gas generator makes it possible to benefit from an excellent onboard energy / congestion ratio.

 As can be seen in the appended figures, 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 is elongated (deployment of the element 124 relative to the base section 122) under the effect of the pressure (cylinder effect).

<Desc / Clms Page number 7>

 Furthermore, it is the extension of the central mast 120 which ensures the deployment of the structure by pulling on the peripheral arms 130 by means of slings 140.

 In fact, as can be seen in the appended figures, a sling 140 is provided 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.

 Thus, 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 from a material with low elongation such as Kevlar (registered trademark).

sorte que les élingues soient tendues à l'état déployé de la structure et maintiennent fermement avec précision les bras 120 et 130. The length of each sling 140 is equal to the length which separates two adjacent vertices of the structure, in the deployed position, from

so that the slings are tensioned in the deployed state of the structure and hold the arms 120 and 130 firmly with precision.

Preferably, in the context of the present invention, the gas generator 180 is adapted to define two successive distinct operating regimes: a slow phase, then a fast phase.

 The initial slow phase allows a slow pressure rise in the telescopic mast 120, to ensure the deployment of the structure without damaging it. Typically, the effort during this first phase is of the order of a few tens of newtons.

 The rapid phase which follows corresponds to the tensioning of the reflector and requires a greater effort, typically of the order of 300 newtons.

 The increase in pressure is shown diagrammatically in FIG. 7 appended.

 To obtain such operation in two successive sequences, the gas generator 180 can comprise, for example, as illustrated in

<Desc / Clms Page number 8>

 FIG. 8, a composition packaged in the form of two distinct sets 190, 192.

 The first assembly 190, the combustion of which provides the slow first phase, is formed of a single compressed cylindrical block conditioned so as to have a relatively slow operating regime (so-called cigarette combustion).

 The second assembly 192 is formed from a plurality of blocks (five for example) of compressed composition which is characterized by a rapid combustion regime.

 The telescopic mast 120, as well as the peripheral articulated arms 130 can be made of any suitable material. Preferably, they are made of metal or based on composite material.

 As indicated previously, the deployment of the structure is operated during the displacement of the auxiliary rod 124, by means of the traction then exerted on the pivoting arms 130 by the slings 140.

 However, preferably, means are provided to assist the deployment of the pivoting arms 130, in the form of spring elements 170.

 According to the embodiment illustrated in the appended figures, these spring elements 170 are interposed between the base element 122 of the telescopic mast 120 and each of the oscillating arms 130 respectively.

 More precisely still, according to the particular embodiment given in the appended figures, an elastomer block 170 is thus provided, near the central support node 110, between the telescopic mast 120 and each swinging arm 130.

 In the folded position as illustrated in FIG. 3, the elastomeric blocks 170 are compressed.

 The deployment of the device according to the present invention is shown diagrammatically in FIGS. 4,5 and 6.

<Desc / Clms Page number 9>

In FIG. 4, the device can be seen in the folded position, the oscillating arms 130 being joined along the base element 122 of the telescopic mast 120 and the auxiliary rod 124 being retracted in the base element 122.

 In FIG. 5, the beginning of the deployment of the structure has been illustrated, the rod 124 starting to be deployed on the outside of the base element 122 and the four arms 130 starting to pivot, due to the traction exerted by the slings 140, assisted in this by the elastomeric springs 170.

 Finally, we see in Figure 6 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.

 Preferably, the device according to the present invention further comprises a device for locking the arms 130 in the deployed position.

 There are many embodiments of such a locking system.

 Such a locking device obviously has the function of preserving the geometric precision.

 Such a locking system also makes it possible to overcome the effects of the pressure drop internal to the telescopic mast 120 consecutive to the decrease in the temperature of the gases.

 In the context of the present invention, preferably, the aforementioned locking means are formed on the basis of a metal rod 160 designed to come to interfere, once the device placed in the deployed position, with grooves 123, 125 formed respectively on the element base 122 and the telescopic element 124 of the mast 120.

 This results in a blocking of the telescopic mast 120 in both directions.

<Desc / Clms Page number 10>

 The structure of such a locking means and its operation are illustrated in Figures 9 to 12 attached.

 We can see in these figures the central support node 110 provided with yokes 114 as well as the ends of the base element 122 and the telescopic element 124 of the mast 120.

 At rest, the metal rod 160 is placed in the node 110. At rest, the rod 160 has a diameter greater than that of the outer telescopic tube 124. The rod 160 is thus placed in the groove 123 of the base element 122. Thus, there is no friction between the rod 160 and the tube 124 of the telescopic mast.

 However, the telescopic tube 124 is provided at its end internal to the base element 122 with a cone 126 flared towards its end. The aforementioned O-ring 140 is preferably provided at the level of this flared cone 126.

 The external diameter of the cone 126 is greater than the internal diameter at rest of the rod 140.

Thus, during the displacement of the telescopic element 124, the cone 126 comes to urge and open the rod 140. The cone 126 of the telescopic element 124 is provided with the aforementioned groove 125, on its external surface.

When the groove 125 of the piston 124 arrives opposite the rod 140, as can be seen in FIG. 11, the rod closes inside the groove 125, by elasticity, causing the mast to block.

 The locking device thus formed has the following advantages among others: reduced number of parts, reliability and efficiency of locking, good temperature resistance, no friction during movement of the mast, and good aging.

 According to an alternative embodiment according to the present invention, each of the tubes 130, and therefore the base element 122 and the element 124 itself of the mast 120 are each telescopic, that is to say formed

<Desc / Clms Page number 11>

 each of at least two elements capable of relative sliding along their axis to ensure an increase in length.

 This variant makes it possible both to have a deployed structure of large amplitude and a reduced storage volume.

 As indicated above, the above-mentioned deployable support frame 100 is associated with several fabric elements forming a reflector.

 More precisely still, the support frame 100 carries twelve triangular panels 200 suitable for forming eight corners of an octahedron concave cube.

 These panels 200 are designed to reflect electromagnetic waves in a certain frequency range.

 The panels 200 are fixed four to four on hems or textile sheaths 210 which provide the structure covering interface by covering the arms 130 of the frame.

 The edge of the panels 200 adjacent to the telescopic mast 120 is also provided with a hem or sheath common to four panels.

 The latch fitted to the telescopic part 122 is however wider to allow the tube to slide.

 In the folded position, 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 rise in skin temperature following the operation of the gas generator 180.

 As seen in Figure 13, each of the triangular panels 200 is provided at its free radially outer edge with a small hem 220 in which is engaged respectively one of the slings 140. Each sling 140 can slide in the associated hem 220.

 During deployment, the gas pressure generated by the gas generator 180 results in a thrust in the axis of the central mast

<Desc / Clms Page number 12>

 120 which is distributed in the slings 140 and thus allows the tensioning of the reflecting fabrics 200.

 FIG. 14 illustrates the radially internal angle of a panel 200.

 Preferably each panel 200 is provided with a reinforcement 230 at each of its angles.

 Each reflective element 200 is preferably formed from a knitted wire 240.

 In the context of the invention, it is preferably a gauge jersey knit 7 produced with a polyester wire 242 wrapped with a nickel wire 244 as illustrated in FIG. 15 (that is to say that a thin strip of nickel 244 is spirally wound around the polyester wire 242.

 The metric number of the wire is 22 (22,000 m of wire weighs 1 kg).

200 et 250 um. The diameter of the polyester thread 242 is typically between

200 and 250 µm.

The density of the fabric is typically between 80 and 85 gram2.

 Furthermore, preferably, the covering wire 244 has a generally oblong section, for example almost rectangular, to allow good electrical contact at each point of contact between two sections of wire 240.

 This solution is adopted in the context of the invention because it makes it possible to have a very conductive wire, to improve the quality of the elementary contacts wire to wire while using a wire having good mechanical characteristics.

 Furthermore, the jersey knitting mode allows a simple and inexpensive production of raw material for a given mesh size.

 Of course, the present invention is not limited to the particular embodiment which has just been described for each triangular panel 200.

<Desc / Clms Page number 13>

 For example, the base thread 242 made of polyester can be replaced by any equivalent material, for example polyamide.

 Furthermore, the covering wire 244 made of nickel can be replaced by any equivalent material, for example steel or copper plus nickel.

 According to yet another variant, each triangular reflective panel 200 can be formed on the basis of metallized polyester tulle.

métallisation peut être obtenue par dépôt de nickel, par exemple d'une épaisseur de l'ordre de 1 um. Le diamètre du fil de base est typiquement de l'ordre de 200 um et la densité du panneau de l'ordre de 30 à 40 gr/m2. Such a panel based on metallized polyester tulle can be formed on the basis of cotton, silk, thermoplastic material or equivalent, arranged in a network of blocked meshes, for example generally hexagonal. The

metallization can be obtained by depositing nickel, for example with a thickness of the order of 1 μm. The diameter of the base wire is typically of the order of 200 μm and the density of the panel of the order of 30 to 40 gr / m2.

As previously suggested, preferably, the device according to the present invention comprises means 300 designed to control the aerodynamic behavior of the reflector during its free fall.

à la fois l'orientation et la rotation éventuelle du réflecteur lors de sa chute libre. More specifically, these means 300 have the function of controlling

both the orientation and the possible rotation of the reflector during its free fall.

- une vitesse de rotation donnée et régulière du réflecteur sur lui-meme autour d'un axe vertical, - une bonne stabilité autour de la position d'équilibre, - une durée de stabilisation la plus faible possible (phase de retournement), - une vitesse de chute la plus faible possible, et More precisely still, within the framework of the invention, the means 300 are advantageously designed to control: - an equilibrium position on an edge as seen in FIG. 17 (at least one horizontal external edge),

- a given and regular speed of rotation of the reflector on itself around a vertical axis, - good stability around the equilibrium position, - the shortest possible stabilization time (reversal phase), - a lowest possible fall speed, and

<Desc / Clms Page number 14>

 - the smallest possible drift (no aerodynamic lift).

 As a variant, the means 300 can be adapted to control an equilibrium position not on a horizontal edge as illustrated in FIG. 17, but on three horizontal edges.

 It seems important indeed, within the framework of the invention, to avoid a position of equilibrium on an angle, that is to say an orientation of the reflector with an angle directed downwards, that is to say - say one of the arms 130 or the mast 120 vertical.

 Different means of orientation can be used for this purpose.

 In the context of the present invention, preferably, the orientation means 300 comprise a canvas dome 310 in the form of a parachute.

This canvas 310 can be formed for example of a square of very light and very porous canvas connected to the two upper peripheral nodes 150, 152 and to the two ends of the telescopic central mast 120 as seen in FIG. 17. According to this figure, the canvas 310 is fixed directly on the upper nodes 150,152. The fabric 310 is also connected to the ends of the central telescopic mast 120 by means of slings 312,314.

 Typically, 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.

 The use of a porous material to produce the fabric 310 makes it possible to make the lift disappear in favor of the drag without however affecting the speed of fall.

 Furthermore, as can be seen in FIG. 17, preferably the control means 300 comprise elements 320 designed to impart a rotational movement, along a vertical axis, when the reflector falls.

<Desc / Clms Page number 15>

 These means 320 have 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.

 More precisely still, preferably, these means 320 are formed by 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, c ' that is to say disposed respectively between the two sections 122, 124 of the telescopic mast 120 and the two arms 130 situated coplanar in a vertical plane, directed upwards from the central node 110.

 These two small sails, generally adjacent to the top of the octahedron allow to print the rotational movement around the vertical axis previously mentioned.

 Of course, the present invention is not limited to the particular embodiments which have just been described but extends to any variant in accordance with its spirit.

 For example, the previously described reflective octahedron can be associated with metallic or metallized flakes (chaff in English terminology).

 Furthermore, it is possible to associate several octahedra, for example typically from 3 to 10, including octahedra of different size.

According to other alternative embodiments, provision may be made to complete or replace the fabric triangles 322,324 ensuring the rotation by symmetrical or asymmetrical holes formed in the reflective panels.

In addition, the present invention is not limited to the production of an octahedron, but extends to the production of any polyhedron.

Claims (40)

 CLAIMS 1. Device forming an electromagnetic reflector, comprising a deployable support frame (100) which carries at least one fabric element (200) designed to form, in the deployed state, a reflective surface, characterized in that the support frame deployable (100) comprises at least one telescopic deployable arm (120).  2. Device according to claim 1, characterized in that the deployable support frame (100) carries a plurality of fabric elements (200) designed to form in combination, in the deployed state, reflective polyhedra.  3. Device according to one of claims 1 or 2, characterized in that the deployable support frame (100) comprises a central node (110) which carries at least the telescopic deployable arm.  4. Device according to one of claims 1 to 3, characterized in that the support frame (100) comprises a telescopic mast (120) linked to the central node (110) and several central pivoting arms mounted at articulation on the node central (110).  5. Device according to one of claims 1 to 4, characterized in that the support frame (100) comprises a telescopic mast (120) comprising a main section (122) which slidably receives at least one auxiliary section (124 ), characterized in that the main section (122) is fixed to the central node (110) by its opening end through which the auxiliary arm (124) emerges. <Desc / Clms Page number 17>  6. Device according to one of claims 1 to 5, characterized in that the support frame (100) comprises a telescopic mast (120) and four pivoting arms (130).  7. Device according to one of claims 1 to 6, characterized in that each arm (120,130) of the support frame (100) is telescopic and linked to the central node (110).  8. Device according to claim 7, characterized in that the deployable support frame (100) comprises six telescopic arms.

9. Device according to one of claims 1 to 8, characterized in that it comprises means (170) capable of urging pivoting arms (130) in extension.  10. Device according to claim 9, characterized in that the biasing means of the pivoting arms (130) comprise slings (140).  11. Device according to one of claims 9 or 10, characterized in that the biasing means of the pivoting arms (130) comprise elastomer blocks (170).  12. Device according to one of claims 1 to 11, characterized in that it further comprises means (160) capable of ensuring the locking of the telescopic arm (120) in the deployed position.  13. Device according to claim 12, characterized in that the locking means comprise an elastic ring (160). <Desc / Clms Page number 18>  14. Device according to one of claims 12 or 13, characterized in that one of the elements (124) of the telescopic deployable arm is provided with a cone (126) adapted to ensure the extension of a rod locking (160) during deployment of the telescopic deployable arm, so that the rod (160) once expanded interferes with grooves provided respectively on the two elements capable of relative telescopic movement.  15. Device according to one of claims 1 to 14, characterized in that it defines eight cube corners in the form of an octahedron.  16. Device according to one of claims 1 to 15, characterized in that the fabric (200) is formed of a knitted fabric.  17. Device according to one of claims 1 to 16, characterized in that the fabric (200) is formed of a gauge jersey knit 7.  18. Device according to one of claims 1 to 15, characterized in that the fabric (200) is formed of metallized polyester tulle.  19. Device according to one of claims 1 to 18, characterized in that the fabric (200) is formed of a thermoplastic wire, for example based on polyester, covered with metal, for example nickel.  20. Device according to one of claims 1 to 19, characterized in that the fabric comprises a metallic covering wire (244) of elongated section.  21. Device according to one of claims 1 to 20, characterized in that the fabric (200) is mounted on the arms (120,130) of the frame <Desc / Clms Page number 19>  deployable support (100) by means of hems (210) formed at the edges of the fabric (200).  22. Device according to one of claims 1 to 21, characterized in that it comprises means (310,322, 324) ensuring control of the orientation and rotation of the structure.  23. Device according to one of claims 1 to 22, characterized in that it comprises means for controlling the aerodynamic behavior which comprise a lifting sail (310).  24. Device according to claim 23, characterized in that the lifting veil (310) is formed of a porous fabric.  25. Device according to one of claims 23 or 24, characterized in that the lift sail (310) is hung on the one hand on two vertices (150,152) of the deployable support frame (100), and on the other hand, by means of slings (312,314) on the two ends of a telescopic mast (120).  26. Device according to one of claims 1 to 25, characterized in that it comprises means for controlling the aerodynamic behavior comprising symmetrical means (322,324) capable of imposing a rotation of the structure around a vertical axis.  27. Device according to claim 26, characterized in that the rotation control means comprise two symmetrical fabrics (322,324). <Desc / Clms Page number 20>  28. Device according to claim 26, characterized in that the rotation control means comprise orifices formed in fabrics of the device.  29. Device according to claim 27, characterized in that the two fabrics (322,324) are fixed between a telescopic mast (120) and the slings (140).  30. Device according to one of claims 1 to 29, characterized in that) comprises means for controlling the aerodynamic behavior (310, 322, 324) capable of imposing an orientation of the deployable support frame such that it presents to the minus a horizontal external edge.  31. Device according to claims 1 to 30, characterized in that it comprises means for controlling the aerodynamic behavior (310, 322, 324) capable of imposing an orientation of the deployable support frame such that it has at least one horizontal lower edge.  32. Device according to one of claims 1 to 31, characterized by

 the fact that it comprises aerodynamic behavior control means (310, 322, 324) capable of ensuring an orientation of the deployable support structure (100) so that it comprises three lower edges in a horizontal plane.  33. Device according to one of claims 1 to 32, characterized in that it comprises control means comprising a pyrotechnic generator (180). <Desc / Clms Page number 21>  34. Device according to claim 33, characterized in that the pyrotechnic generator is designed to define two phases: a first phase of slow pressure build-up followed by a phase of faster pressure build-up.  35. Device according to one of claims 33 or 34, characterized in that the pyrotechnic generator comprises two buns of pyrotechnic composition (190,192) having different combustion properties capable of defining two successive phases, the initial rise in slow pressure, the other faster pressure build-up.  36. Device according to one of claims 1 to 35, characterized in that it comprises slings (140) fixed between two vertices of the deployable structure (100).  37. Device according to claim 36, characterized in that the slings (140) are placed in hems formed on the edges of the fabric (200).  38. Device according to one of claims 33 or 34, characterized in that it comprises twelve slings (140).  39. Device according to one of claims 1 to 38, characterized in that the support frame (100) comprises at least one sling (140) which ensures optimal deployment of the fabric (200).  40. Device according to claim 39, characterized by the fact that the sling (140) is arranged along an edge of the fabric element (200).