EP2909890B1

EP2909890B1 - Deployable space reflector

Info

Publication number: EP2909890B1
Application number: EP13792420.5A
Authority: EP
Inventors: Leri S. Datashvili
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-10-19
Filing date: 2013-10-18
Publication date: 2021-02-17
Anticipated expiration: 2033-10-18
Also published as: EP2909890A1; WO2014068342A1; GEP201706727B; ES2869299T3; EP3879626A1; PT2909890T; PL2909890T3; WO2014068342A8

Description

FIELD OF THE INVENTION

The present invention relates to radio technique, namely to space structures, for example, large deployable space reflectors (symmetric, asymmetric, offset and other type of reflectors), radio and optical telescopes, energo-concentrators and other structures with analogous purpose.

DESCRIPTION OF RELATED ART

The deployable Space reflector according to the patent US6323827, 2001 , comprises peripheral support framework with two deployable peripheral polygonal rings consisting of interconnected rods, connecting rods of the rings providing a certain separation of the rings, a reflecting surface and a tensioning framework for shaping the reflecting surface, a deployment mechanism and a latching mechanism
This reflector is characterized with a low stiffness and stability, while two polygonal rings and connecting rods of the rings form rectangular ring facets which need additional means for stiffening - diagonal rod or cables in the patent.
The other known deployable space reflector [Novel large deployable antenna backing structure concepts for foldable reflectors, ESA/ESTEC,NOORDWIJK, Netherlands, 2-3 October 2012, V.Fraux, M.Lawton, Reveles, Z.You] comprises a peripheral support framework with two deployable peripheral polygonal rings of interconnected rods, and connecting rods of the rings providing a certain separation of the rings. One of the rings of the supporting framework has pair-wise hinged cross rods and the other ring interconnected hinged rods of V-fold rods.
This reflector is also characterized with a low stiffness and stability, while it has a row of the V-fold rods as one of the ring of the support peripheral framework. In addition, it is characterized with a non-compact stowed package, while the other ring of the framework has angulated cross rods and the V-fold rods fold inside of the package, which limits the folding.
Complexity of reaching the deployed state of the V-fold rods is a characteristic drawback of the mentioned peripheral framework.
The deployable Space reflector according to the patent US5680145 1997 , comprises a peripheral support framework with two deployable peripheral polygonal rings of interconnected rods, and connecting rods of the rings providing a certain separation of the rings, a reflecting surface and a tensioning framework for shaping the reflecting surface, a deployment mechanism and a latching mechanism.
This reflector is also characterized with drawbacks as a low stiffness and stability of the deployed configuration, as well as large height of the stowed package caused by such a folding scheme in which the height is a sum of the lengths of the ring rod and the connecting rod of the rings. This reflector is also characterized with complexity or even impossibility of reaching the large deployed sizes of the reflector. This drawback is a result of a presence of the tensioning framework, which has a shape of facetted double concave lens. Due to the character of the double concave lens, even if it has a near zero thickness at the center, it might reach larger heights at the periphery with large diameters, this fact limits the height of the reflector under the described concept to the small sizes.
The deployable Space reflector according to the "Concept of the Tension Truss Antenna", Koryo Miura and Yasuyuki Miyazaki, The Institute of Space and Astronautical Science, Yoshidai, Sagamihara, Kanagawa, Japan, AIAA Journal, vol. 28, , which consists of a support framework, a reflecting surface, the tensioning framework forming the reflecting surface, a deployable and a latching mechanisms. The tensioning framework is made of front and rear cable networks, which are interconnected by flexible ties WO03/003517 A1 , US2002/063660 A1 , WO2012/065619 A1 disclose also deployable structures comprising interconnected rods.
This reflector is characterized with similar drawbacks as the previous one, namely, low deployed stiffness and stability caused by the radial support frame, as well as large height of the stowed package of the reflector for large diameters. The latter one is caused again by the presence of the tensioning framework, which has a shape of facetted double concave lens.

SUMMARY DESCRIPTION OF THE INVENTION

Advantages of this invention are in increasing deployed stiffness and stability, as well as in increasing reliability of deployment, achieving large deployed seized high accuracy of reflector realization and in decreasing height of the stowed package of the reflector.
The mentioned advantages have been achieved by the features of claim 1, i.e. by the fact that the structure of the deployable space reflector, which comprises a deployable peripheral a deployable peripheral support framework with two deployable peripheral polygonal rings consisting of interconnected rods, connecting rods of the rings providing a certain separation of the rings, a reflecting surface and a tensioning framework for shaping the reflecting surface, a deployment mechanism and a latching mechanism, has been given new features.
Namely, one of the deployable peripheral polygonal rings of the deployable support framework of the reflector is made of hinged full cross-rods placed in different planes and are connected to the connecting rods of the rings with the rotation possibilities in the said planes, so that one end of one of the rods is connected to the end of one of the connecting rod of the rings with a fixed hinge while the other end of the rod is connected to the other connecting rod of the rings with a hinge and with the possibility of translation over its length, and one end of the rod of the other peripheral ring is hinged fixed to the other end of one of the connecting rods of the rings while the other end of the rod is hinged to the other connecting rod of the rings with the translation along the connecting rod, or both peripheral rings of the peripheral support framework consist of a single row of the latter rods and connecting rods of the rings which are inclined to the reflector axis forming trapeze-shaped bays of the so formed pyramidal support framework for increasing of its stiffness.
Further advantageous embodiments of the invention are described with the features of the dependent claims.
In another configuration of the deployable space reflector, the advantages are achieved by the fact that the cross full rods of the peripheral support framework, which are placed in different planes, are not interconnected.
Achieving of the advantages is possible also because of the following configuration, for reducing the height of the stowed package, at least every second connecting rod of the peripheral polygonal rings of the peripheral support framework is made with inner and outer parts so that the cross full rods of the one ring are connected to the inner and outer parts of the connecting rods of the rings, while the ends of the rods of the other polygonal ring are connected to the either inner or outer parts of the connecting rods of the rings.
In another configuration of the deployable space reflector, for compactness of the stowed package, the rods of the polygonal rings, which are hinged to the connecting rods of the rings, either fixed or with translation possibilities, are joined pair-wise with rotation possibility around the axes of the connecting rods of the rings, with the limiting supports of the rotation angle, which in the end defines achieving the advantages of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS, 23 DRAWINGS IN TOTAL

Fig. 1 illustrates a general view of the schematic (wire frame) configuration of the deployable space reflector.
Fig. 2-4 show close views of the bays of the peripheral support structure.
Fig. 5 and 6 show side views of detail of the peripheral support structure of a conical configuration, deployed and partly folded, where the upper ring consist of a cross full rods and the lower ring consists of a row of interconnected rods.
Fig. 7 and 8 show side views of detail of the peripheral support structure of a conical configuration, deployed and partly folded, where the upper ring consist of a cross full rods and the lower ring consists of a row of interconnected rods. In these figures cross rods show a high deployment angle, towards the near-parallel position to the lower rods.
Fig. 9 and 10 show side views of detail of the peripheral support structure of a conical configuration (wire frame scheme), deployed and partly folded, where the lower ring consist of a cross full rods and the upper ring consists of a row of interconnected rods.
Fig. 11 shows an endfitting of the cross full rods which are placed in different planes, enabling the rotation of the rods in that planes, general view.
Fig. 12 and 13 show side views of detail of the peripheral support structure of a conical configuration (wire frame scheme), deployed and partly folded, where the both rings consist of a row of interconnected rods, which doesn't form part of the invention.
Fig. 14-16 show different views of the connecting hinge of the cross full rods, placed in different planes, of the peripheral framework of the reflector.
Fig. 17 and 18 show side views of the peripheral support framework of the reflector in deployed and partly folded states.
Fig. 19 and 20 show general views of the peripheral support framework of the reflector in cylindrical and conical configurations respectively.
Fig. 21 shows side view of the peripheral support structure with its deployment mechanism which comprises e.g. two motors and a system of pulleys and cables.
Fig. 22 and 23 shows joints of the connection of the rods of the rings to the two parts connecting rods of the rings with inner and outer parts.

DETAILED DESCRIPTION OF THE INVENTION

A deployable space reflector comprises a deployable peripheral support framework 1. The support framework 1 has two deployable peripheral polygonal rings 2 consisting of interconnected rods and connecting rods 3 of the rings 2 providing a certain separation of the rings 2. The deployable space reflector has a tensioning framework 4 for shaping the reflecting surface, which comprises a front side network 5, a back side network 6 and connecting ties 7. A reflecting surface 8 is joined to the tensioning framework 4. For increasing of stiffness, stability and deployment reliability of the deployable space reflector, one of the deployable peripheral polygonal rings 2 of the deployable support framework 1 of the reflector is made of hinged full cross-rods 9 and 10 placed in different planes. Cross-rods 9 and 10 are connected to the connecting rods 3 of the rings 2 with the rotation possibilities in the said planes and are provided with angular fittings 11 to enable rotation of the cross-rods 9 and 10 in the said planes, these fittings 11 may be made like fittings that known from patent US5680145 , H01Q15/16, 1997. One end of the rods 9 is connected to the end of one of the connecting rod 3 of the rings 2 with a fixed hinge 12 while the other end of the rods 9 is connected to the other connecting rod 3 of the rings 2 by joint 13 with a hinge and with the possibility of translation over its length. One end of the rod 14 of the other peripheral ring 2 is hinged fixed 12 to the other end of one of the connecting rods 3 of the rings 2 while the other end of the rod 14 is hinged 13 to the other connecting rod 3 of the rings 2 with the translation possibility along the connecting rod 3. Support framework 1 in a conical configuration offers some more advantages like high stiffness and lower mass than cylindrically shaped. These can be emphasized by achieving the size of the opening angle of the ring rods 9 and 10 near zero degrees in deployed configuration (Fig. 1 - 11).
According to the other alternative variant of Figs. 12 and 13, which do not form part of the invention, the both peripheral rings 2 of the peripheral support framework 1 consist of a single row of the rods 14. The support framework 1 has connecting rods 3 of the rings which are inclined to the reflector axis forming trapeze-shaped bays 141 (fig. 12 and 13) of the so formed many-sided pyramidal support framework for increasing of its stiffness. For increasing reliability of deployment of the peripheral support framework 1 different length rods 14 of the trapeze-shaped bays 141 have synchronizers of deployment of the reflector, for example such as known from patent US5680145 , H01Q15/16, 1997, fig. 20 and made as gear set.
The full cross-rods 9 and 10 of the peripheral support framework 1 are joining each other by a hinge 15 which provided which provides high stiffness, transfer of high torsional and bending moments between the rods 9 and 10, and a gap-free rotation. The hinge 15 consist of parts, made for example as hoops 16, which are fixing on the rods 9 and 10 and having stop blocks 17 on the inner sides of them. One stop block 17 has housing 18, other stop block 17 - bearing 19 (fig. 15-16) for rotation in the housing and fixing device between the rods 9 and 10, made for example as a bolt inside the hole (which are known from prior technical art and are not shown in the figures).
In a particular configuration, the cross full rods 9 and 10 of the peripheral support framework 1, which are placed in different planes are not interconnected (fig. 17 and 18).
According to another embodiment of the deployable space reflector the peripheral support framework is inscribed in either cylindrical 20 or conical 21 shapes (fig. 19 and 20).
A deployment mechanism of the peripheral support framework 1 consists of rollers 22 which are installed on the ends of the rods 14 in the fixed 12, and moving 13 joints (rollers 22 are not shown in joints 13), and a cable 23 that is passing through the rollers 22 transmitted in one of bays of the peripheral support framework 1 along the ends of the rods 14, and by analogy transmitted in each next bay. The cables 23 are provided with unwinding/winding drams 24 with drive units, which are mounted on an at least one connecting rod 3 of the rings 2 of the peripheral support framework 1. The deployment mechanism further consists of rollers 25 which are mounted on the ends of the rods 9, 10 in the fixed 12, and moving 13 joints (rollers 25 are not shown in joints 13), and a cable 26 that passes through the rollers 25 and is transmitted in each bays of the peripheral support framework 1 along the cross-rods 9, 10, for example firstly from a fixed joint 12 to the moving joint 13, then along the rod 9 to the fixed joint 12, then to the moving joint 13 and back to the fixed joint 12, then along the rods 10 and by an analogy the cable 26 is transmitted in each next bays. The cables 26 are also provided by unwinding/winding drams 24 with drive units, which are setting on the at least one connecting rod 3 of the rings 2 of the peripheral support framework 1 (Fig. 21). Latching mechanism is known from a previous art and can be performed as springed-teeth on the moving joints 13 and respective holes on the connecting rods 3 of the rings 2 of the support framework 1 of the reflector (not shown in drawings).
According to the next embodiment of the deployable space reflector for decreasing the stowed height, at least every second connecting rod 3 of the rings 2 of the peripheral support framework 1 is made with inner and outer parts 28 and 29 which have coupling bars 30. The cross full rods 9 and 10 of the one ring 2 are connected to the inner part 28 of the connecting rods 3 of the rings 2, while the ends of the rods 14 of the other polygonal ring 2 are connected to the outer 29 of the connecting rods 3 (fig. 22).
For compactness of the stowed package of the deployable space reflector, the rods 9, 10 and 14 of the polygonal rings 2 which are hinged to the connecting rods 3 of the rings, either fixed 12 or with translation possibilities 13, are joined pair-wise with rotation possibility around the axes of the connecting rods of the rings, with the limiting supports of the rotation angle 31 (fig. 23).

Claims

A deployable space reflector comprising: a deployable peripheral support framework (1), a reflecting surface and a tensioning framework (4) for shaping the reflecting surface, a deployment mechanism and a latching mechanism,
wherein
- the peripheral support framework comprises: two deployable peripheral polygonal rings (2) consisting of interconnected rods (9, 10, 14), the peripheral support framework further comprises connecting rods (3), wherein the connecting rods (3) provide a predetermined separation of the polygonal rings,

- the interconnected rods (9, 10, 14) of the first of the polygonal rings are with full cross rods (9, 10), the interconnected rods of the second of the polygonal rings are single interconnected rods (14),
wherein each side of the first polygonal ring comprises two full cross rods (9, 10) and each side of the second polygonal ring comprises one single interconnected rod (14),
- the full cross rods (9, 10) comprise fittings (11),

- each of the interconnected rods (9, 10, 14) is placed in a different plane and each of the interconnected rods (9, 10, 14) is connected to two parallel connecting rods (3),

- one end of each of the full cross rods (9, 10) of the first polygonal ring comprises a fixed hinge and is connected to one of the two parallel connecting rods (3) with the fixed hinge and the other end of each of full cross rods (9, 10) comprises a hinge and is connected to the other parallel connecting rod (3) by the hinge configured to allow translation over the length of the other parallel connecting rod (3),

- one end of each of the single interconnected rods (14) is hinged fixed to one of the two parallel connecting rods (3) and the other end of each of the single interconnected rods (14) is hinged and configured to allow translation along the connecting rod (3),

- the fittings (11) are mounted on the ends of each of the full cross rods (9, 10).
The deployable space reflector according of claim 1, wherein the two full cross-rods (9, 10) of each of the sides of the first polygonal ring are joining each other by a hinge made as hoops (16) having stop blocks (17) on the inner sides of the hoops (16) in which one stop block (17) has a housing (18) and the other stop block (17) has a bearing (19) for rotation in the housing.
The deployable space reflector according of claims 1 and 2, wherein at least every second connecting rod (3) of the peripheral support framework (1) is made with inner and outer parts (28, 29) which have coupling bars (30) so that the interconnected rods (9, 10) of the first polygonal ring are connected to the inner or outer parts (28, 29) of the at least every second connecting rod (3), while the ends of the single interconnected rods (14) of the second polygonal ring are connected to the either outer or inner parts (29, 28) of the at least every second connecting rod (3).
A deployable space reflector in accordance to anyone of claims 1 to 3, wherein the fittings comprising a headpiece to be fitted over the interconnecting rods (9, 10, 14).