WO2013153164A1 - Dispositif de déploiement de concentrateurs ou de raidisseurs, générateur solaire et satellite comportant un tel dispositif - Google Patents
Dispositif de déploiement de concentrateurs ou de raidisseurs, générateur solaire et satellite comportant un tel dispositif Download PDFInfo
- Publication number
- WO2013153164A1 WO2013153164A1 PCT/EP2013/057599 EP2013057599W WO2013153164A1 WO 2013153164 A1 WO2013153164 A1 WO 2013153164A1 EP 2013057599 W EP2013057599 W EP 2013057599W WO 2013153164 A1 WO2013153164 A1 WO 2013153164A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- panels
- stiffening
- main
- panel
- solar generator
- Prior art date
Links
- 239000003351 stiffener Substances 0.000 title description 11
- 238000005192 partition Methods 0.000 claims description 40
- 230000003287 optical effect Effects 0.000 claims description 11
- 230000005855 radiation Effects 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 2
- 241000826860 Trapezium Species 0.000 description 1
- 238000010009 beating Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000007872 degassing Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2222—Folding
- B64G1/2224—Folding about multiple axes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
Definitions
- the present invention relates to a device for deploying concentrators or stiffeners, a solar generator and a satellite comprising such a device. It applies in particular to solar generators mounted on satellites.
- a solar generator composed of rigid panels must have a natural frequency low enough to avoid “beating” at the slightest pressure and cause the satellite in uncontrolled movements. Indeed, these oscillations triggered by positioning control actuators for example, may be detrimental to the pointing antennas or embedded optical instruments.
- These solar generators consist of sufficiently thick or stiff panels and have rigid hinges after opening. Others use pantograph systems that combine control of deployment and ultimate rigidity. In both cases the stiffness of the solar generator results in a penalty in mass. The energy captured by a solar generator is proportional to its exposed surface for the sun.
- Some generators instead of increasing the cell area, have optical concentrators that divide the number of solar cells up to two.
- optical concentrators are deployed on both sides of photovoltaic cells carrying panels and are composed of "flaps” (shutters, in French) reflective sail stretched on frames. These optical concentrators are folded independently on a cell-carrying panel on each side. They are open only after deployment and alignment of the different panels carrying cells. Their effectiveness depends on the accuracy of the opening angle and their flatness.
- the present invention aims to remedy all or part of these disadvantages.
- the present invention is directed to a device for deploying a solar generator between a folded position and an extended position, which comprises: on the one hand, a set of main panels carrying the solar cells, intended, once the solar generator has been deployed, to be aligned and coplanar and
- At least one set of stiffening panels interconnected by at least one hinge intended, once the solar generator has been deployed, to be aligned and coplanar
- each of the stiffening panels being connected by at least one hinge to at least one main panel and each of the main panels being connected, by said hinges, to at least one stiffening panel, each assembly formed by a main panel and the stiffening panels which are connected constituting a bundle, each bundle being connected to each successive bundle in a set of stiffening panels by at least two hinges, positioned on two different panels of the bundle,
- the rigidity of Solar generator in deployed position is very high. Indeed, once deployed, the plan of each set of stiffening panels is at an angle with the plane of the main panels and with the plane of any other stiffening panels.
- the hinges ensure the rigidity of these planes in their two directions and the angle between these planes ensures the rigidity in their orthogonal direction.
- the hinge offset arm made with respect to the connection of said hinge with a stiffening panel, it is obtained that the hinges connecting the bundles are coaxial, especially for two successive bundles which, in the folded position, have their main panels more close as their stiffening panels.
- it allows a complete folding of the bundles since the offset of a hinge can position the axis of the hinge on the plane carrying the outer surface of the main panels, or beyond this plane.
- the stiffening panels will have an additional function of concentrator. In this case, once the device is deployed, they will be positioned laterally on each side of the main cell-carrying panels and the angle will be defined to optimize the amount of solar radiation reflected back to the cells of the main panel. If the stiffener does not have a concentrator function, the position of the stiffener is optimized according to other constraints including mass. The stiffener is then preferably positioned at 90 ° in the middle or laterally relative to the main panels carrying cells, and the opposite side to the cells.
- each stiffening panel is stored on the main panel, cell carrier, to which it is connected by at least one hinge, to form a bundle.
- Each of these bundles consisting of a main panel and at least one stiffening panel, is connected to the next bundle by hinges.
- These hinges are arranged, as we have seen, partly or totally between stiffening panels and partly or not at all between the main panels. In embodiments, all the hinges between two bundles are coaxial when the solar generator is folded into accordion to be stored. It is understood here that it can therefore be hinges between panels stiffeners of different bundles, and, if present, hinges between main panels.
- each stiffening set also planar, can rotate in a single movement around the hinges connecting it to the main panels.
- the "T" shape when the set of stiffening panels passes in the center of the main panels, or "U” when two sets of stiffening panels, forming concentrators, are positioned laterally with respect to the panels.
- main is continuous over the entire length of the device.
- the hinges between bundles are no longer co-aligned and are no longer rotated, which ensures a high rigidity to all.
- the rigidity thus obtained by the shape of the assembly allows a global relief of all the parts composing the device. It is no longer the thickness of the main panels and the stiffness in rotation of the hinges which are stressed as in the prior art. This combination of means can therefore reduce the weight of the device or increase its rigidity, and also to obtain a better flatness of the concentrator panels.
- the deployment device comprises at least two main panels per solar generator wing, and on the other hand at least one stiffening panel per main panel.
- At least two main panels are interconnected by at least one hinge. This hinge is necessary to ensure rigidity when there is only one stiffener panel per main panel.
- at least one stiffening panel comprises means of reflection of the solar radiation towards the cells of the main panel to which he is connected.
- the reflection means have variable or controllable optical characteristics so as to be able to adjust the radiation received by the cells as a function of the solar constant.
- the reflection means comprise thermochromic or electrochromic materials.
- thermochromic use the temperature sensitivity of the product used would be adjusted so as to maximize the solar reflection towards the cells at low temperature and to minimize it at high temperature: the adjustment of the temperature ranges of the thermochromic material will be defined according to the temperature of the concentrator during the mission of the satellite: the high temperature corresponding to the temperature of the concentrator when the satellite is close to sun, and the low temperature when it is far from it., the solar generator being pointed towards the sun in both cases.
- the stiffening panels are composed of a reflective sail stretched on a frame.
- the stiffening panels, forming concentrators, are then particularly light.
- the main panels consist of a canvas stretched over a frame.
- the solar cells are placed on the canvas.
- the main panels are then particularly light.
- the main panels are rigid and accordionally folded prior to deployment.
- the stiffness of the off-plane stiffening panels is greater than that of the main panels working in their plane. We can thus lighten these main panels since the rigidity of the device comes mainly, according to the invention, stiffening panels.
- the present invention relates to a solar generator, which comprises a deployment device object of the present invention.
- This solar generator has the same advantages and characteristics as the deployment device object of the present invention.
- each stiffening panel has, once the deployment device has been deployed, an obtuse angle with the main panel to which said stiffening panel is bonded.
- the stiffening panels then have an optical concentrator function.
- the solar generator further includes:
- a connecting rod connected by two hinges, on the one hand to a fixed partition and, on the other hand, to a said main panel and
- a rigid plate connected by at least one hinge to said fixed partition and, by at least one other hinge, to said main panel
- the lever arm of said plate being smaller than the lever arm of said connecting rod, the hinges being positioned in such a way that, when the plate is in a first support position on the partition, said main panel is parallel to the partition and, when the plate is in a second support position on the partition, said main panel is substantially perpendicular to the partition.
- the solar generator To deploy the solar generator, it turns both the rod and the plate by actuating at least one of them. Because the lever arms are different, the movement of the main panel is not a translation but has a rotation. This rotation causes the passage of the main panel from a first position, parallel to the partition, to a second position, perpendicular to the partition.
- the first position corresponds to a minimum size of the assembly formed by the partition and the panel, for example a space suitable for the launch phases of a satellite comprising the partition and the panel.
- the second position corresponds to a maximum deployment of the main panel so that the cells that it carries collect the maximum of solar energy.
- a single motor rotating the rod or the plate can thus be sufficient for the deployment of the panel.
- the second position of the main panel is stable and rigid because the main panel is supported on the partition, through the plate.
- the rigidity thus obtained allows an overall relief of all the components of the solar generator.
- This combination of means makes it possible to reduce the mass of the solar generator while ensuring the rigidity of the positioning of the main panel relative to the partition.
- the solar generator includes a motor for rotating the plate relative to the partition.
- the solar generator comprises a means for retaining the plate on the partition when said main panel is in the second support position.
- the rotation of the plate covers an angle of 180 degrees.
- the solar generator comprises, for at least one stiffening panel, a spacer spring of said stiffening panel.
- the present invention aims a satellite which comprises at least one solar generator object of the present invention.
- This satellite presents the same features and advantages as the deployment device object of the present invention.
- FIG. 1 represents, schematically and in perspective, a first embodiment of a non-deployed device comprising main panels and stiffening panels, objects of the present invention
- FIG. 2 represents, schematically and in perspective, the device illustrated in FIG. 1 partially deployed
- FIG. 3 represents, schematically and in perspective, the device illustrated in FIG. 1 completely deployed
- FIG. 4 represents, schematically and in perspective, a second embodiment of a non-deployed device comprising main panels and stiffening panels, objects of the present invention
- FIG. 5 represents, schematically and in perspective, the device illustrated in FIG. 4 partially deployed
- FIG. 6 represents, schematically and in perspective, the device illustrated in FIG. 4 completely deployed
- FIG. 7 represents, schematically and in perspective, a third particular embodiment of the device, deployed
- FIGS. 8 to 13 show, schematically and in perspective, different phases of deployment of a particular embodiment of the solar generator that is the subject of the present invention
- FIG. 14 represents a satellite comprising two solar generators object of the present invention.
- FIG. 15 represents, in the form of a logic diagram, the steps implemented in a particular embodiment of the method that is the subject of the present invention. DESCRIPTION OF EXAMPLES OF EMBODIMENT OF THE INVENTION
- FIG. 1 shows an embodiment of a solar generator 10 that is not deployed and in accordion mode.
- This solar generator 10 is composed of stiffening panels 12 connected, by at least one hinge 14, rigid main panels 1 1.
- Each stiffening panel 12 is connected to a single main panel 1 1.
- These stiffening panels 12 are intended to act as optical concentrators for the main panels 1 1.
- the stiffening panels 12 are located on either side of the main panel 1 1 to which they are connected by a hinge 14.
- the stiffening panels 12 located on the same side of two main panels 1 1 consecutive are interconnected by at least one hinge 13.
- FIG. 2 shows a solar generator 10 whose hinges 13 linking the stiffening panels 12 to the main panels 11 have been deployed, thanks to a motor (not shown) so that the main panels 1 1 are juxtaposed and coplanar between them.
- the stiffening panels 12 associated with a main panel 1 1 are thus rotated with respect to the stiffening panels 12 associated with the main panel 1 1 next, around the hinge 13 connecting these stiffening panels 12. angular spacing of the main panels 1 1, which were parallel and superimposed in Figure 1.
- FIG. 3 shows a fully deployed solar generator 10 whose stiffening panels 12 have been separated from the main panels 11 by rotation around the hinges 14, thanks to a motor (not shown) so that the device forms a "U" along its length.
- the main panels 1 1 are rigid and provided with photovoltaic cells (not shown) on the side where the stiffening panels 12 are located.
- FIG. 4 shows another embodiment of an undeployed and accordion-type solar generator 20.
- This solar generator 20 is composed of stiffening panels 22 connected, by at least one hinge 14, rigid main panels 1 1.
- Each stiffening panel 22 is connected to a single main panel 1 1.
- These stiffening panels 22 act as optical concentrators for the main panels 1 1, and are located, when the device is deployed, on either side of the main panel 1 1 to which they are connected by a hinge 14.
- the hinges 13 and Binding the stiffening panels 22 of two successive main panels 1 1 are coaxial when the stiffening panels 22 are parallel to the main panels 1 1, as in the configurations shown in Figures 4 and 5.
- at least one of the hinges 13 and 15 (in Figures 4 to 6, it is hinges 15) is offset by an arm 16 relative to its connection to a stiffening panel 22.
- the stiffening panels 22 located, when the device 20 is deployed, on the same side of two consecutive main panels 1 1 are interconnected by at least one hinge 13 or 15.
- this hinge offset arm 16 made with respect to the connection of said hinge with a stiffening panel, it is obtained that the hinges connecting the bundles are coaxial, especially for two successive bundles which, in the folded position, have their panels. main closer than their stiffening panels.
- the offset arm it is possible with the offset arm, a complete folding of the bundles since the offset of a hinge can position the axis of the hinge on the plane carrying the outer surface of the main panels, or beyond this plane.
- FIG. 5 there is a solar generator 20 whose stiffening panels 22 have been spaced from the main panels 1 1 around the hinges 14 so that the stiffening panels 22 are coplanar with each other.
- FIG. 6 shows a fully deployed solar generator 10, the main panels 11 of which have been spaced apart from the stiffening panels 22 around the hinges 13 so that the device forms a "U" over its entire length.
- the hinges 15 are in abutment, which improves the rigidity of the solar generator.
- the main panels 1 1 are rigid and provided with photovoltaic cells. It is observed that the stiffening panels 22 cover the entirety of a face of a main panel January 1 and thus allow to concentrate more light than the stiffening panels 12 of the first embodiment, illustrated in Figures 1 to 3.
- the stiffness of the stiffening panels working out of plane is greater than that of the main panels working in their plane. We can thus lighten these main panels since the rigidity of the device comes mainly, according to the invention, stiffening panels.
- FIG. 7 shows, in a third embodiment, a solar generator 30 whose deployment device comprises a single set of stiffening panels 32 positioned to pass to the centers of the main panels 31 carrying the solar cells.
- Hinges 33 connect the stiffening panels 32 together.
- Hinges 34 connect each stiffening panel 32 to a main panel 31 and each main panel 31 to a stiffening panel 32.
- the main panels are connected to their neighbors by a hinge to ensure the rigidity of the device.
- two stiffening panels are positioned behind the main panels. In this case the hinges between the main panels are not necessary.
- FIG. 8 shows an embodiment of a solar generator shown in the non-deployed and accordion or "bundle" position.
- This solar generator is mounted on a partition 40, for example an outer wall of a satellite.
- the generator is composed of a main rigid panel 45 connected to the partition 40 and a second rigid main panel 50.
- the main panels 45 and 50 carry on their faces facing each other, solar cells (not shown) adapted to capture solar energy and to provide an electric current.
- the main panel 45 carries, for intermediate hinges (not shown), stiffening panels 55 and 56 (shown in Figure 13).
- the main panel 50 carries, by means of hinges (not shown), stiffening panels 60 and 61.
- the stiffening panel 55 and the stiffening panel 60 are connected by a hinge (not shown) whose axis is parallel to the main panels 45 and 50.
- the stiffening panel 56 and the stiffening panel 61 are connected by a hinge (not shown) with the axis is parallel to the main panels 45 and 50.
- These hinges are coaxial.
- Each stiffening panel is linked to a single main panel. These stiffening panels are intended to stiffen the assembly of the main panels 45 and 50. It is noted that the main panels 45 and 50 are not directly connected to each other.
- FIG. 9 shows a base 70 fixed on the partition 40 and a rigid plate 65 mounted on the base 70 via at least one hinge provided with an engine. (not shown) There is also a connecting rod 75, one end of which is mounted by means of a hinge (not shown) on the partition 40 and the other end of which is mounted via a hinge (not shown) on the main panel 45.
- the lever arm of the rigid plate 65 is smaller than the lever arm of the connecting rod 75.
- the hinge connections are positioned in such a way that, when the plate 65 is in a first bearing position on the partition 40 (FIG. 8) , the main panel 45 is parallel to the partition 40 and, when the plate 65 is in a second support position on the partition 40 (FIGS. 1 to 13), the main panel 45 is substantially perpendicular to the partition 40.
- the hinges carried by the partition 40 are parallel to each other and to the other hinges of the connecting rod 75 and the plate 65.
- a single motor rotating the rod 75 or the plate 65 can thus be sufficient for the deployment of the main panel 45.
- the second position of the main panel 45 is stable and rigid because the main panel 45 is supported on the wall, by through the plate 65.
- the rigidity thus obtained allows an overall relief of all the components of the solar generator. This reduces the mass of the solar generator while ensuring the rigidity of the positioning of the main panel 45 relative to the partition 40.
- the plate 65 rotates about the axis of each hinge which connects it to the base 70 and the connecting rod 75 forces the main panel 45 to follow a kinematic movement away from the partition 40 by rotating it.
- the plate 65 has finished its rotation, here 180 °.
- the main panels 45 and 50, parallel to each other, are perpendicular to the partition 40.
- the plate 65 is clipped or clipped, by means of a retaining means in the position of the plate 65 on the partition 40, which gives the panel main 45 a precise and predetermined position, and a good rigidity to the connection between the partition 40 and the main panel 45.
- a motor (not shown) rotates the main panel 50 relative to the hinges connecting the stiffening panels 55, 56, 60 and 61.
- the stiffening panels deviate automatically from the main panels 45 and 50, under the effect of a motorization of the hinges that connect them to the main panels 45 and 50 or under the effect of a spring.
- the solar generator is then rigid.
- FIG. 14 shows an embodiment of a satellite 90 comprising two solar generators 95 as described above, for which the stiffening panels 98 serve, in addition, optical concentrators for increasing the light energy incident on solar cells.
- the main panels are flexible, type stretched canvas covered with photovoltaic cells.
- stiffening panels are themselves composed of several deployable elements.
- FIG. 15 shows that the operation of such a satellite 90 comprises:
- step 105 during which, for each solar generator, the main panels are positioned in bundle, against the partition which carries them,
- a step 135 during which the stiffening panels deviate from the main panels to which they are connected.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1253332A FR2989355B1 (fr) | 2012-04-11 | 2012-04-11 | Dispositif de deploiement de concentrateurs ou de raidisseurs, generateur solaire et satellite comportant un tel dispositif |
FR1253332 | 2012-04-11 |
Publications (1)
Publication Number | Publication Date |
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WO2013153164A1 true WO2013153164A1 (fr) | 2013-10-17 |
Family
ID=48170439
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2013/057599 WO2013153164A1 (fr) | 2012-04-11 | 2013-04-11 | Dispositif de déploiement de concentrateurs ou de raidisseurs, générateur solaire et satellite comportant un tel dispositif |
Country Status (2)
Country | Link |
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FR (1) | FR2989355B1 (fr) |
WO (1) | WO2013153164A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3033628A1 (fr) * | 2015-03-12 | 2016-09-16 | Sunpartner Technologies | Dispositif de production d'energie solaire optimise en fonction des saisons |
CN110808446A (zh) * | 2019-12-02 | 2020-02-18 | 西南交通大学 | 一种板状天线折叠支架 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5305971A (en) * | 1992-07-14 | 1994-04-26 | Trw Inc. | Spacecraft control by electrochromic devices |
US5520747A (en) | 1994-05-02 | 1996-05-28 | Astro Aerospace Corporation | Foldable low concentration solar array |
EP0977273A1 (fr) * | 1998-07-30 | 2000-02-02 | Hughes Electronics Corporation | Systèmes réflecteurs solaires et méthodes |
EP1270411A1 (fr) * | 2001-06-28 | 2003-01-02 | Dutch Space B.V. | Panneau solaire avec cellules solaires minces ondulées |
EP1501132A2 (fr) * | 2003-07-25 | 2005-01-26 | EADS Astrium GmbH | Générateur solaire pour le déploiement en deux dimensions |
-
2012
- 2012-04-11 FR FR1253332A patent/FR2989355B1/fr active Active
-
2013
- 2013-04-11 WO PCT/EP2013/057599 patent/WO2013153164A1/fr active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5305971A (en) * | 1992-07-14 | 1994-04-26 | Trw Inc. | Spacecraft control by electrochromic devices |
US5520747A (en) | 1994-05-02 | 1996-05-28 | Astro Aerospace Corporation | Foldable low concentration solar array |
EP0977273A1 (fr) * | 1998-07-30 | 2000-02-02 | Hughes Electronics Corporation | Systèmes réflecteurs solaires et méthodes |
EP1270411A1 (fr) * | 2001-06-28 | 2003-01-02 | Dutch Space B.V. | Panneau solaire avec cellules solaires minces ondulées |
EP1501132A2 (fr) * | 2003-07-25 | 2005-01-26 | EADS Astrium GmbH | Générateur solaire pour le déploiement en deux dimensions |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3033628A1 (fr) * | 2015-03-12 | 2016-09-16 | Sunpartner Technologies | Dispositif de production d'energie solaire optimise en fonction des saisons |
CN110808446A (zh) * | 2019-12-02 | 2020-02-18 | 西南交通大学 | 一种板状天线折叠支架 |
Also Published As
Publication number | Publication date |
---|---|
FR2989355A1 (fr) | 2013-10-18 |
FR2989355B1 (fr) | 2016-08-05 |
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