EP2301112A2

EP2301112A2 - Hinged folding structure

Info

Publication number: EP2301112A2
Application number: EP09766016A
Authority: EP
Inventors: Guy Valembois
Original assignee: Conseil et Technique SAS
Current assignee: Conseil et Technique SAS
Priority date: 2008-06-18
Filing date: 2009-06-17
Publication date: 2011-03-30
Also published as: FR2932709A1; WO2009153454A3; WO2009153454A2

Abstract

Hinged folding structure (1) consisting of an assembly of elements (2) hinged together by hinge means (3, 4), where each of the elements (2) has at each end a hinge (3, 4) enabling it to be connected to the end of another element (2) across a hinge axis (X, Y), all the pivot pins of the hinges (3, 4) being so constructed that the structure (1) can adopt two extreme positions, namely an unfolded position where the elements (2) are more or less continuous with each other to form an ellipse, and a folded position where the elements (2) are brought together and approximately parallel with each other. The elements (2) and the hinges (3, 4) are connected both to means for controlling the unfolding of the elements (2), and to assistance means for ensuring simultaneity of the unfolding or folding of the elements (2).

Description

DEPLOYABLE ARTICULATED STRUCTURE.

The present invention relates to a deployable articulated structure. Such a deployable articulated structure can find many applications. For example to deploy remotely a canvas or the like, for the purpose of protection or dissemination of information.

A deployable articulated structure according to the invention will find, without limitation, a particular application in the field of space, whether to deploy sun shields for satellite protection, or satellite dishes for satellite, or photovoltaic solar panels.

Another application can be found in the field of road signs, to allow to deploy, in emergencies, and remotely, large signs or information.

For the purpose of simplification, the description of the invention will be placed in the field of application to the spatial domain.

It is known that the satellite dish antennas must be able to be folded and stored in a small space during the launching of the satellite, and then be able to be deployed once said satellite is in orbit. Many types of deployable parabolic antenna are known, which differ essentially in the technology used to allow the parabola to be deployed and folded. Thus these parables include in most cases, a deployable structure in the manner of an umbrella or a fan, or they are sometimes inflatable.

Such satellite dishes obviously have an uneven parabolic surface which may be detrimental to the use made of them.

Articulated deployable structures are already known, of the type comprising a set of segments abutted two by two through articulation means, and shaped in a loop, each said articulation means having two joints on each of which articulates a segment. These structures have disadvantages, on the one hand the multiplication of the axes of articulation harms the rigidity of the assembly, and on the other hand they are not intended to deploy automatically.

The present invention aims to provide a deployable articulated structure used in the construction of a deployable parabolic antenna, and to overcome the various aforementioned drawbacks. The present invention is not limited to the space domain, but may find utility in all areas requiring the deployment of a web or the like.

The articulated deployable structure according to the invention consists of the assembly of articulated elements in pairs through hinge means, and it is essentially characterized in that each of said elements has at each of its ends a joint allowing connecting the end of another element through a hinge axis, all the pivot axes of said hinges being constructed so that said structure can take two extreme positions, namely an extended position where said elements are two to two more or less in the extension of one another to form an ellipse, and a folded position where said elements are grouped against each other substantially parallel to each other; and in that said elements and said hinges are associated on the one hand with means for controlling the deployment of said elements, and on the other hand with assistance means able to ensure simultaneity of the deployment or folding of said elements.

According to an additional feature of the deployable articulated structure according to the invention, the pivot axes of said hinges are arranged so that for each of the elements constituting the structure, the two pivot axes that it comprises, one at each end, s' extend in parallel planes, perpendicular to the main axis of said element. said two axes of each of said elements being offset angularly with respect to said main axis, and the sum of all the angular offsets of all said elements is equal to 360 °. In function of the expanded form of the structure, which may be non-regular, some offsets may be nil, while others may be negative.

According to a particular embodiment of the articulated deployable structure according to the invention, the elements that compose it are all of the same length, and the offsets are all of the same value.

According to another additional feature of the articulated deployable structure according to the invention, the elements consist of tubes inside which pass cables which constitute the control means and the assistance means.

According to another additional feature of the articulated deployable structure according to the invention, the joints consist of clevises on whose axes are mounted pulleys in which the cables pass.

According to another additional feature of the deployable articulated structure according to the invention, the control means consist of a cable which travels the entire structure passing over a pulley at each of the joints. According to another additional characteristic of the deployable articulated structure according to the invention, on the one hand each of the axes of the articulations comprises, axially threaded, pulleys in free rotation, which constitute guides for the cables which pass through the elements, on the other hand each of the joints comprises two cable guide means constituting the assistance means, each disposed integral with one end of the connected elements and offset transversely to said axes of the joints; and in that said cables constituting the assistance means are two in number per pair of successive articulations, that on the one hand one passes on the pulley of a first articulation of the outer side in cooperation with said guide means, and on the pulley of the second hinge on the inner side, so that its winding on the pulley of the first hinge is minimum, and at most on the pulley of the second hinge in folded position, and vice versa in the deployed position, and that the other cable on the other hand passes over the pulley of said first hinge on the inner side, and on the pulley of said second hinge on the outer side, so that its winding on the pulley of said first articulation is maximum, and at least on the pulley of said second articulation in the folded position, and conversely in the deployed position.

The deployable articulated structure according to the invention, because of the simplicity of its construction and the ease of its handling, makes it possible to consider using it in many applications, and particularly, but not exclusively in the space field.

Canvas already known to be deployed through a deployable structure, these webs to be the reflector of an antenna for example. The disadvantage of these paintings is that they are stored folded, and after deployment, to remove the folds from storage the structure must exert a high tension, which requires that said structure is dimensioned at this level of effort which in fact increases its weight as that of the actuators allowing its deployment, which can be crippling in the space domain.

However, advantageously, when the elements that make up the structure are in the form of bar or tube, they can serve as winding shafts to flexible panels interconnected by their free end, and during deployment of the structure, the unfolding of these panels and their juxtaposition results in the formation of a surface to the dimensions of the structure. The panels are not stored folded, so there is no need for the structure to exert a strong tension to eliminate storage folds.

This technology is not limited to the manufacture of an antenna, it can also make it possible to make a photovoltaic sensor. Indeed, there are flexible solar panels, but they can not be folded, by cons they can be rolled.

A panel consisting of the combination of several parts, each wound on a mandrel, can thus be envisaged, each of the mandrels being secured to the elements of a deployable structure, and said parts being secured to each other by their free end, minus two to two, so that the deployment of said structure causes the unwinding of said parts until the constitution of a panel. Such a configuration can be applied to all existing deployable structures, even for an open deployable structure, however the application to a deployable structure according to the invention has many advantages.

Indeed, on a deployable hinged structure according to the invention, each of the elements that compose it can be shaped into a winding mandrel, so as to be able to receive a piece of flexible or semi-rigid material, which can be partly to be wound on said element when the structure is folded, and secondly to be unwound when said structure is deployed, being connected to at least one other room vis-à-vis, so to constitute with the others parts, a panel extending inside said structure.

The advantages and characteristics of the deployable articulated structure according to the invention will emerge more clearly from the description which follows and which refers to the appended drawing, which represents a non-limiting embodiment thereof.

In the attached drawing: - Figure 1 shows a schematic perspective view of a deployable articulated structure according to the invention, in the intermediate position.

- Figure 2 shows a schematic perspective view of part of the same structure.

- Figure 3 shows a partial schematic perspective view of another part of the same structure.

- Figure 4 shows a partial schematic perspective view of another part of the same structure. - Figures 5a, 5b and 5c show partial views in sections, of a part of the same structure in different configurations of use.

- Figures 6a, 6b and 6c show partial views in sections, of the same part of the same structure in different configurations of use.

- Figure 7 shows a partial sectional view of the same part of the same structure in a particular configuration.

- Figure 8 shows a partial sectional view of another part of the same structure in the same particular configuration. Figures 9a, 9b, 9c and 9d show schematic perspective views of another structure according to the invention, in a particular application and in successive positions of a deployment. Figure 10 shows a schematic perspective view of a variant of the same structure, in the deployed position. Figure 11 shows a schematic perspective view of a portion of the same structure.

Referring to Figure 1, we can see a deployable articulated structure 1 according to the invention, consisting of the assembly of tubes 2 articulated in pairs by means of joints 3 and 4. As can be seen on FIGS. 3 and 4, which respectively represent the joints 3 and 4, these the latter each consist of two yokes 30 and 31, respectively 40 and 41, each secured to a tube 2 and joined by a shaft 32, respectively 42, of axis X, respectively Y.

As can be seen in FIG. 2, as well as in FIG. 1, in this embodiment the X and Y axes of articulation of a tube 2 on the two neighboring tubes 2 are in parallel planes but angularly offset by relative to the main axis of the tube 2, the offset being in the present case an angle of a value equal to 360 ° divided by the number of joints 3 and 4, or tubes 2, in this case twelve , an angle of 30 °.

It will be understood that the articulated deployable structure 1 can take two extreme positions, one where all the joints 3 and 4 are folded to the maximum and the tubes 2 are attached to one another and are all substantially parallel to each other, and another where all the joints are deployed to the maximum, the tubes 2 then being in the extension of each other to form a polygon. In Figure 1, where the deployable articulated structure 1 is in an intermediate configuration, the X axes are radial and arranged in the same plane, while the Y axes are also radial and arranged in another same plane.

The embodiment shown is a special case where the tubes 2 are all the same length and where the joints 2 3 and 4 are all identical, it could of course be otherwise.

In FIGS. 3 and 4, it may be noted that the joints 3 and 4 moreover have freely rotatable pulleys, respectively, 33 and 43, threaded on the shafts, respectively 32 and 42, these pulleys being three in number by articulation. .

As can be seen in FIGS. 5a, 5b, 5c, 6a, 6b, 6c, 7 and 8, the pulleys 33 and 43 constitute guides for three cables which pass through the tubes 2, and which constitute means of maneuvering the deployable articulated structure 1. It will be noted that in these figures 5a, 5b, 5c, 6a, 6b, 6c, 7 and

8, there is shown in section a tube 2 and two joints 3 and

4, and for better understanding, the joints 3 and 4 are shown in section in the same plane, perpendicular to their axis X and Y of pivoting.

With reference to FIGS. 5a, 5b and 5c, as well as FIGS. 6a, 6b and 6c, three different configurations can be seen, namely, respectively, folded, partially deployed and deployed. FIGS. 5a, 5b and 5c also show a cable 5 passing through the tube 2 as well as the two joints 3 and 4 passing over the pulleys 33 and 43, the ends 50 and 51 of which are fixed beyond the joints, respectively 3 and 4. Note that to move from the folded position to the deployed position, the hinge 3 must open at an angle less than that which must open the hinge 4, also to compensate this difference the pulleys 33 and 43 are of different radii, whose ratio is inversely proportional to the ratio of said angles.

The cable 5 passes on the pulley 33 on the outer side, and on the pulley 43 on the inner side, so that its winding on the pulley 33 is minimum, and at most on the pulley 43 in the folded position, and vice versa in the deployed position. It will be noted that the hinge 3 internally has at each of its articulated parts a guide, respectively 34 and 35, over which the cable 5 passes.

It will be understood that the deployment of the hinge 3 causes, under the effect of the traction exerted by the cable 5, the deployment of the hinge 4, and that inversely the folding of the hinge 4 causes the folding of the hinge 4. articulation 3.

FIGS. 6a, 6b and 6c also show that the deployable articulated structure 1 according to the invention comprises a second cable 6 which passes through the tube 2 as well as the two joints 3 and 4 while passing over the pulleys 33 and 43, and whose ends 60 and 61 are fixed beyond the joints, respectively 3 and 4.

The cable 6 passes on the pulley 33 on the inner side, and on the pulley 43 on the outer side, so that its winding on the pulley 33 is maximum, and at least on the pulley 43 in the folded position, and vice versa in the deployed position.

Note that the hinge 4 has internally to each of its hinged portions a guide, respectively 44 and 45, which passes the cable 6. It will be understood that the deployment of the hinge 4 causes, under the effect of the traction exerted by the cable 6, the deployment of the articulation 3, and that inversely the folding of the articulation 3 causes the folding of the articulation 4.

The structure 1 thus comprises several cables 5, one per pair of joints 3 and 4, and several cables 6, one per pair of joints 3 and 4, these cables 5 and 6 make it possible to obtain simultaneity of the folding movements and deployment.

Referring now to FIGS. 7 and 8, it can be seen that the deployable articulated structure 1 according to the invention comprises a third cable 7, which traverses the entire structure 1, one end 70 of which is fixed at one end in a tube 2 while the other end 71 exits the same tube 2 through an orifice 20, visible in Figure 8. The cable 7 passes on the pulleys 33 and 43, on the inner side that is to say that its winding is maximum in folded position. It will be understood that thus a traction T, external to the structure 1, causes the deployment of the latter, while the maintenance of the cable 7 under tension ensures the rigidity of the assembly.

In an application to the realization of a satellite dish, a fabric is fixed by its edge to the elements that make up the structure 1, so that the deployment of the latter ensures the deployment of the fabric. For this purpose, with reference to FIGS. 9a, 9b, 9c and 9d, it is possible to see a deployable structure 1, in accordance with that described previously, mistletoe differs only in that the number of tube 2 is six and not twelve. The tubes 2 are assembled by means of articulation 3 and 4, and are also traversed by cables not shown. Each of the tubes 2 is equipped with a housing device 21, in the form of a tube threaded onto the tube 2, and provided with a longitudinal slot 22 through which a piece 8 of flexible material passes, which is capable of to be wound on the tube 2, inside the housing 21. As can be seen in Figure 9d, the parts 8 are triangular in shape, so that their juxtaposition can reproduce the inner shape of the structure 1 deployed.

Note that the different parts are dimensioned so that in the resulting surface they are dissociated, contiguous, or have a portion of recovery, depending on the need corresponding to the desired function.

In practice, the free end points 80 of the parts 8 are interconnected by means of a link 81 shown only in FIG. 9d. During the deployment of the structure 1, because of the link 81, the parts 8 are unwound to form a panel 82, of course the dimensions of the parts 8 are chosen so as to have a certain tension in the deployed position, knowing that each piece 8 is provided with stop means, not shown, consisting of means for securing either the tube 2 or the housing 21.

Note that the use of a housing 21 is not essential, that the parts 8 can be simply wound on the tubes 2. It is also possible that each of the parts 8 is secured to a sleeve threaded on a tube 2 and in free rotation of it.

It will also be noted that the parts 8 can be secured to the tubes 2 through resilient return means capable of promoting the winding of the parts 8 on the tubes 2, which return means can contribute to the folding of the structure 1. The parts 8 of flexible material may be of different natures depending on the application for which the structure is intended.

In the case of the realization of an occultation screen, it may be a simple opaque canvas, in the case of a solar panel it may be a canvas provided with photovoltaic sensors, and in the case of an antenna it may be a canvas provided with reflective elements.

Referring now to FIG. 10, it is possible to see a deployed structure 1, equipped with parts 8 of flexible material, sufficiently flexible to be able to be rolled up, or semi-rigid, which form a panel 82 having a concave shape, namely a parabola . The shape of this panel 82 is obtained through the characteristics of the parts 8 that compose it, and one of which is shown in FIG.

Thus, each of the parts 8 is preformed and has at rest a certain concavity, materialized by two curved axes V and W.

Claims

1) articulated deployable structure (1), consisting of the assembly of elements (2) articulated in pairs through hinge means (3, 4), characterized in that each of said elements (2) comprises each of its ends a hinge (3, 4) for connecting the end of another element (2) through a hinge axis (X, Y), all axes (32, 42) of pivoting said joints (3, 4) being constructed so that said structure (1) can take two extreme positions, namely an extended position where said elements (2) are two to two more or less in the extension of each other for forming an ellipse, and a folded position where said elements (2) are grouped together substantially parallel to each other; and in that said elements (2) and said joints (3, 4) are associated on the one hand with control means (7) for the deployment of said elements (2), and on the other hand with means (5, 6, 33, 43) capable of ensuring simultaneous deployment or folding of said elements (2).

2) articulated deployable structure (1) according to claim 1, characterized in that the pivot axes

(32, 42) articulations (3, 4) are arranged so that for each of the elements (2) constituting the structure (1), the two axes of articulation (X, Y) that it comprises, one to each end, extend in parallel planes, perpendicular to the main axis of said element (2), said two axes of articulation (X, Y) of each of said elements (2) being angularly offset relative to said main axis, and the sum of all the angular offsets of all said elements (2) is equal to 360 °. 3) articulated deployable structure (1) according to claim 2, characterized in that the elements (2) which the are all of the same length, and the offsets are all of the same value.

4) Deployable articulated structure (1) according to any one of claims 1 to 3, characterized in that the elements (2) consist of tubes inside which pass traction cables (5, 6, 7) which constitute the control means and the means of assistance.

5) articulated deployable structure according to claim 4, characterized in that the joints (3, 4) consist of clevises (30, 31, 40, 41) on the axes (32, 42) of which pulleys are mounted (33, 43) in which the cables (5, 6, 7) pass.

6) deployable articulated structure according to claim 5, characterized in that the control means consist of a cable (7) which runs through the entire structure passing on a pulley (33, 43) to each of the joints (3, 4).

7) articulated deployable structure according to claim 5 or claim 6, characterized in that on the one hand each of the axes (32, 42) of the joints (3, 4) comprises, axially threaded pulleys in free rotation (33, 43), which constitute guides for the cables (5, 6, 7) which pass through the elements (2), on the other hand each of the articulations (3, 4) comprises two guide means (34, 35, 44, 45 ) cables (5, 6) constituting the assistance means, each disposed integral with one end of the elements (2) connected and offset transversely relative to said axes (32, 42) of the joints; and in that said cables (5, 6) which constitute the assistance means are two in number by successive pairs of joints, that on the one hand one (5) passes on the pulley (33) of a first hinge (3) on the outer side in cooperation with said guide means (34, 35), and on the pulley (43) of the second hinge (4) on the inner side, so that its winding on the pulley (33 ) of the first hinge (3) is minimum, and at most on " ¹ the pulley (43) of the second hinge (4) in the folded position, and vice versa in the deployed position, and that other the other cable (6) passes over the pulley (33) of said first hinge (3) on the inner side, and on the pulley (43) of said second hinge (4) on the outer side, so that its winding on the pulley (33) of said first articulation (3) is maximum, and at least on the pulley (43) of said second articulation (4) in the folded position, and conversely in the deployed position.

8) articulated deployable structure according to any one of claims 1 to 7 characterized in that each of the elements that compose it is shaped as a winding mandrel, so as to be able to receive a piece (8) of flexible or semi-material rigid, capable on the one hand to be wound on said element (2) when the structure (1) is folded, and secondly to be unwound when said structure (1) is deployed, being linked to at least another piece (8) vis-à-vis, so as to constitute with the other parts (8) a panel (82) extending inside said structure (1).

9) deployable articulated structure according to claim 8, characterized in that each of the elements (2) which compose it comprises a housing (21), in the form of a tube threaded on the tube (2), and provided with a longitudinal slot (22) through which the piece (8) of flexible material which is wound on the element (2), inside said housing (21). 10) deployable articulated structure according to claim 8 or claim 9, characterized in that the parts (88) of flexible material are preformed and have a certain concavity, so that the panel (82) consisting of the approximation of all said parts ( 8) has, when deployed, a concave shape.