WO2011006506A1 - Structure pliante supportant des collecteurs de rayonnement électromagnétique - Google Patents

Structure pliante supportant des collecteurs de rayonnement électromagnétique Download PDF

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Publication number
WO2011006506A1
WO2011006506A1 PCT/DK2010/050186 DK2010050186W WO2011006506A1 WO 2011006506 A1 WO2011006506 A1 WO 2011006506A1 DK 2010050186 W DK2010050186 W DK 2010050186W WO 2011006506 A1 WO2011006506 A1 WO 2011006506A1
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WO
WIPO (PCT)
Prior art keywords
flexible frame
collector
configuration
electromagnetic radiations
frame
Prior art date
Application number
PCT/DK2010/050186
Other languages
English (en)
Inventor
Anders Schmidt Kristensen
Lars Damkilde
Original Assignee
Aalborg Universitet
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aalborg Universitet filed Critical Aalborg Universitet
Publication of WO2011006506A1 publication Critical patent/WO2011006506A1/fr

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/08—Means for collapsing antennas or parts thereof
    • 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
    • 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
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S25/00—Arrangement of stationary mountings or supports for solar heat collector modules
    • F24S25/50—Arrangement of stationary mountings or supports for solar heat collector modules comprising elongate non-rigid elements, e.g. straps, wires or ropes
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
    • H01Q15/161—Collapsible reflectors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q7/00—Loop antennas with a substantially uniform current distribution around the loop and having a directional radiation pattern in a plane perpendicular to the plane of the loop
    • H01Q7/02—Collapsible antennas; Retractable antennas
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
    • H02S30/00—Structural details of PV modules other than those related to light conversion
    • H02S30/20—Collapsible or foldable PV modules
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S25/00—Arrangement of stationary mountings or supports for solar heat collector modules
    • F24S2025/01—Special support components; Methods of use
    • F24S2025/012—Foldable support elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S80/00—Details, accessories or component parts of solar heat collectors not provided for in groups F24S10/00-F24S70/00
    • F24S2080/01—Selection of particular materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/40—Solar thermal energy, e.g. solar towers
    • Y02E10/47—Mountings or tracking
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/50—Photovoltaic [PV] energy

Definitions

  • the present invention relates to flexible frames supporting electromagnetic radiation collectors which can be folded to be stored and/or transported.
  • EMr collectors such as solar panels and antenna systems, where efficiency of collection is related to surface area, are normally provided in large structures with the disadvantage of not being easily movable.
  • antenna reflectors are designed to facilitate reflector shape modification for stowage.
  • One often-used approach is to use a segmented reflector with a cantilever rib frame which unfolds on deployment as an umbrella unfolds.
  • US 2008/0223431 discloses a foldable solar panel comprising multiple cell assemblies and multiple flexible seams, wherein each folding cell assembly has two symmetric folding cell assembly halves and a flexible secondary seam.
  • US 4,371,134 describes an artificial satellite arrangement with foldable solar generators and antennas. These generators comprises an assembly of panels bearing solar cells articulated on one another in succession so as to occupy either a folded position for launching for which said panels are folded in a zigzag form on one another, or an unfolded position for operation for which said panels are at least substantially in line with one another. Unfolding of the generator is controlled by a drive mechanism receiving orders from the satellite.
  • US 4,555,585 discloses a foldable solar cell panel apparatus which has at least two panel portions which are connected together at a foldable edge to form at least one foldable pair.
  • the panel needs the presence of folding and unfolding system means for folding and unfolding the solar cell panel apparatus.
  • US 5,857,648 discloses a precision deployable boom assembly for terrestrial and celestial applications which comprises an extendable and retractable boom.
  • US 5,574,472 discloses a method for stowing a unitary flexible antenna reflector in a confining envelope.
  • the reflector once deformed for stowing into a U-shaped configuration, is maintained in a deformed state by attaching a restraining element between the diametrically opposed positions on the edge of the reflector.
  • the main disadvantage of the flexible antenna reflector disclosed by US 5,574,472 is that the deformation into a U-shaped configuration of the reflector does not efficiently reduce the encumbrance of the reflector as it simply increases the reflector curvature.
  • this method of stowing an antenna reflector was used on the MSAT-I satellite, launched on April 20, 1996, where two folded spring-back antenna having 6.8 m by 5.25m elliptical shape where stowed.
  • the two antennas were rolled together into a 4.9 m high truncated cone on top of the spacecraft, therefore by only partially reducing the reflector dimension.
  • the invention preferably seeks to mitigate, alleviate or eliminate one or more of the above mentioned disadvantages singly or in any combination by providing a method for stowing a flexible frame which efficiently reduces its size by deforming the electromagnetic radiation collectors supported.
  • the release of this stored strain energy in space provides rapid deployment of the frame without the need of external intervention.
  • An electro-magnetic radiation collector is a device capable of collecting electromagnetic radiation characterized by specific wavelengths, energies and
  • antennas are EMr collectors which are able to collect for example radio
  • An EMr collector is a solar collector or a light collector.
  • Celestial applications are herein defined as application which occurs in planets atmosphere, in controlled or uncontrolled airspace, in the outer space or on objects in the outer space.
  • Terrestrial applications are herein defined as applications which take place on the surface of the planet earth.
  • Reducing size of the flexible frame is herein defined as reducing the space occupied by it, by reducing its dimensions, high, length, width, volume, cross section or area.
  • the method allows for storing in the stressed configuration of the energy needed for deployment.
  • this energy is introduced and stored in gravity conditions and released in non-gravity conditions upon deployment of the flexible frame.
  • the invention is particularly, but not exclusively, advantageous for reducing the size of transportable EMr collectors.
  • the specific twisted and folded position described by the invention avoids problem in unfolding when compared to other method wherein unfolding may cause entanglement, e.g. no wires are present.
  • a further advantage of the invention is that once installed the collectors can be easily, for example in terrestrial application, re-stowed during sudden typhoon, rain, snow, hail or other adverse atmospherical condition, which may produce severe damage to the collectors.
  • a flexible frame supporting a collector of electromagnetic radiations characterized in that, the flexible frame is twistable into at least two loops and the at least two loops are foldable into an overlapping configuration to provide a compact configuration.
  • deforming the flexible frame according to the first aspect of the invention comprises: i) twisting the flexible frame to obtain at least two loops, ii) folding the at least two loops into an overlapping configuration.
  • the deformation by twisting turns the flexible frame into a coil configuration, to which it follows folding of the twisted frame into a closed coil configuration having at least two intermeshing convolution. Closed is defined as having neither beginning nor end.
  • the closed coil configuration is induced by the closed configuration of the frame.
  • deforming of the flexible frame further comprises compressing the at least two loops into a compact configuration.
  • Compressing may comprise pressing, bending, folding or twisting so as to obtain a compact configuration.
  • Compact configuration is herein defined as a configuration where the loops in the overlapping configuration are closely and firmly united, e.g. by pressing the loops together. Compacting the twisted and folded frame is not necessary but
  • the step of maintaining said flexible frame in the stressed configuration includes the use of means for holding the stressed configuration.
  • Means for holding comprises devices with the function of holding tight and securing the stressed configuration, i.e. the overlapping configuration, e.g. a coil configuration, so as to avoid undesired opening during the transport.
  • These devices may be clamps, clips, couplers, tube locks which can be opened by either mechanical intervention, or in particular for celestial application by the use of pyrotechnic devices, such as small explosion charges, or by electrical resistance that can be burned.
  • Means for holding may also include a pouch with the function of securing the stressed configuration during transport.
  • the opening of this pouch allows for self unfolding of the flexible frame with no need of external intervention, as once removed the holding means, the frame return into it initial configuration without needing active or external deployment means.
  • the flexible frame is connected to a carrier structure.
  • Carrier structures are structures carrying the flexible frame, which is connected to them. Examples of these carrier structures, hereafter simply referred as structure, are, for celestial applications, satellites, spacecrafts, and spacestations. In this case the EMr collectors, e.g. solar energy converters, supported on the flexible frames are connected to the structure to provide energy.
  • EMr collectors e.g. solar energy converters
  • these structures can be any structure which can benefit from a reduction of sizes of this flexible frame supporting EMr collectors, for example to obtain an easier transportable structure. For example, where personal
  • a foldable frame supporting a solar collector which can be easily folded for transport and unfolded before use, may provide electricity to sources of light or devices such as mobile phones, computers or other electronic devices.
  • the method further comprises releasing the flexible frame from the stressed configuration. Once released the flexible frame self restores its initial configuration without any external intervention.
  • the method according to the first aspect of the invention describes a way of deforming the frame, by twisting and folding, which allows for storing of the energy necessary for the unfolding so that virtually no external energy, e.g. by external intervention, is needed during the unfolding process.
  • the simple removal of the holding means allows for self restoring of the initial configuration of the flexible frame. Once released the flexible frame restores its initial configuration because it was folded into an unstable configuration, i.e. the stressed
  • the frame is made with materials with properties which allows for storage of the energy introduced through the folding.
  • unfolding without any external intervention may be advantageous as the unfolding process may occur at a certain distance from the user.
  • a pouch holding the frame supporting a solar cell may be thrown at a distance from the user and than unfold into its operative state without user intervention.
  • External intervention is herein defined as an intervention, e.g. an act performed, to the frame by bodies which are not the flexible frame in itself.
  • an intervention e.g. an act performed
  • a deployment performed by an astronaut on the already released flexible frame can be defined as an external intervention.
  • Another example of external intervention is the deployment of the flexible frame into its initial configuration after its release by a boom.
  • the absence of an external intervention is particularly advantageous in celestial application, as generally restoring of the initial operative configuration of a satellite, to which the flexible frame supporting EM collectors is connected, may require deployment means.
  • the flexible frame released from the stressed configuration restores its initial configuration without substantial modification of the structure momentum.
  • This is particularly advantageous in celestial application.
  • space structures connected to the flexible frames are in motion in 1 or 2 dimensions, having a specific momentum which needs to be preserved in order to avoid undesired deviation from their desired orbit.
  • the deployment of the flexible frame can be tested on earth so that the exact deployment movement can be reproduced in space allowing for preservation of the desired system, i.e. carrier structure and frame connected, momentum.
  • Minimal or not significative modifications to the structure momentum induced by the deployment of the flexible frame can be taken in consideration during the test on earth and corrective solutions can be found before the structure is sent in orbit.
  • the opening of the device occurs avoiding introduction of external energy so as to keep the all system into an energy neutral state.
  • the frame is connected to a structure, e.g. a satellite
  • keeping the system, i.e. the structure connected to the frame, into an energy neutral state will avoid undesired acceleration of the system during the deployment of the flexible frame.
  • Vibrations due to the unfolding of the flexible frame may be damped by using damping systems.
  • the speed of unfolding of the flexible frame can also be controlled by constructing the frame using appropriate structural materials.
  • Some structural materials or combination of materials and composites can be devised to exhibit high structural damping. This is advantageous in order to control the speed of unfolding so as to avoid an excessive speed.
  • the collector of electromagnetic radiations is a solar collector.
  • the collector of electromagnetic radiations is a light collector.
  • a solar collector is able to collect the EM radiation emitted by the sun which largely lies in the visible and near infrared area of the EM spectrum.
  • a light collector is able to collect light, e.g. from the sun or from other sources of natural or artificial light, which includes radiations in the UV, visible and near LR. regions of the EM spectrum.
  • a solar or light collector can be for example a material having photovoltaic properties, such as silicon, which is sensible to radiation emitted in a specific region of the EM spectrum, e.g. in the Uv/visible/N.I.R. regions which identify the solar emission.
  • the material having photovoltaic properties may be in the form of thin or thick films of material or blends, e.g. materials having photovoltaic properties and nanoparticles, deposited on substrate.
  • Example of these films may be, inorganic or organic semiconductor materials, for example amorphous Si, CIGS films, CdTe thin films, polymeric or hybrids, i.e. polymeric/inorganic films, polymer blends with bulk hetero junction systems.
  • Collector substrates may be semi-rigid substrate like thin metal, or composite, e.g. metal/polymer, plates, thin films or foils.
  • substrate may be textile materials, including plastified or metalled layers, so as to adjust and tune stiffness, rigidity and elasticity properties of the substrate.
  • the collector of electromagnetic radiations is a part of a solar energy converter.
  • the collector of electromagnetic radiations is a part of a light energy converter.
  • a solar or light collector may also include a device for converting the collected radiation into a different form of energy.
  • the solar collector may be referred as to solar energy converter, for example a solar cell, which converts solar or light radiation into electricity.
  • a solar energy converter may comprise a single solar cell or panel or a module composed by more than one cell or panel assembled together so as to synergically collect solar radiation.
  • Solar energy converters and collectors may have different structures, for example single solar cell, panels or modules may be connected in series or parallel depending on the desired output, i.e. optimized voltage or current. Strategic location of the solar panels or modules in the solar energy converters may also be used to obtain maximum efficiency of conversion. For example panels may be facing opposite direction in order to average light collection independently from the position of the source of light. Cells, panels or modules maybe also arranged into the collector in a way to facilitate the twisting and folding process of frame. For example, cells may be provided so as to leave a central opening in the structure which may facilitate the deformation by twisting and folding.
  • the flexible frame according to the second aspect of the invention further comprises means for holding the overlapping configuration.
  • the flexible frame according to the second aspect of the invention is a foldable solar collector, e.g. for terrestrial or celestial application.
  • electromagnetic radiations e.g. a transducer designed to transmit or receive electromagnetic waves.
  • the collector able to receive and transmit electromagnetic radiations is an antenna.
  • the collector able to receive and transmit electromagnetic radiations is an antenna reflector.
  • an antenna reflector may be a corner reflector which is able to deflect a front of electromagnetic radiations back along a vector that is parallel to but opposite in direction from the radiation's source.
  • antenna reflector may be a parabolic reflector which is the most common antenna reflector mainly due to its high gain, which enables high data rate transmission at low power.
  • mesh antennas composed by for example by RF reflective mesh may be advantageous.
  • mesh antennas are generally composed of a knitted lightweight metallic mesh
  • the flexible frame supporting mesh antennas can be twisted and folded following the method disclosed with no damage to the discontinuous mesh structure.
  • the flexible frame may be supporting inflatable antennas.
  • the flexible frame may support an inflatable antenna made of thin flexible material which is twisted and folded prior to launch and then inflated after deployment in space. Once deployed and inflated the antenna can be made more rigid by either exposing to sun irradiation the flexible material previously impregnated with a resin.
  • electromagnetic radiations is a deflector.
  • a deflector is defined as a device intended to turn aside a flow of electromagnetic radiation.
  • An example of deflector could be a mirror which receives and transmit back electromagnetic radiation in the visible region.
  • Another example of deflector may be a deflector for cosmic radiations, which deployed in space, receives cosmic radiations and bounces them back.
  • the flexible frame according to the second aspect of the invention is functionally connected to a carrier structure.
  • the first and second aspect of the present invention may each be combined with any of the other aspects.
  • Figure Ia is a schematic drawing of the flexible frame.
  • Figure Ib is a schematic drawing of the flexible frame supporting a collector of EMr.
  • Figure 2 is a drawing of the flexible frame in the unfolded configuration.
  • Figure 3a is a drawing of the flexible frame in the twisted configuration.
  • Figure 3b and figure 3c shows two steps of the folding of the flexible frame from the twisted configuration.
  • Figure 3d shows the folded configuration in a compact configuration.
  • Figure 4a and 4b show the twisted and folded configuration with three loops, respectively.
  • Figure 5, 6, 7 show examples of three types of flexible frames supporting a collector of electromagnetic radiations according to embodiments of the present invention.
  • Figure Ia shows a schematic drawing of the flexible frame 1 on which is supported a collector 2 of electromagnetic radiations, shown in figure Ib.
  • the specific outline of the frame is linked to its function.
  • the flexible frame may have any form which has the ability of storing energy in the frame by the method described by the invention and to be folded into a compact configuration. While in this embodiment the flexible frame is shown circular in other embodiments it may assume different forms, e.g. triangular or square.
  • FIG. 2 is a drawing of the flexible frame 1 in the unfolded configuration.
  • the flexible frame may have the characteristics of being light in weight, thin, and highly elastic. It may have a very high yield strength point so that the frame deforms elastically and returns to its original shape, i.e. no plastical deformation is present, even when the high level of mechanical stress is applied.
  • Example of materials that can be used to produce the frame are metal or metal composite such as aluminium or aluminium based alloys, titanium, zinc alloys or magnesium alloys. Polymers, polymer composites or metal/fiber reinforced materials may be also used as flexible frame materials.
  • For celestial applications substantial resistance to cosmic rays is also an important characteristic of the frame and the EMr collector. Therefore, for celestial application polymers or polymer composites maybe not used as frame materials unless presenting sufficient resistance to cosmic rays degradation.
  • FIG 3a is a drawing of the flexible frame in the twisted configuration.
  • the flexible frame may be hold at its diametrically opposed sides 3 and 4 and then twisted along the axis 5 formed between the two holding positions 3 and 4 as indicated by the arrow 6.
  • the frame is twisted by 180° so that the frame assumes a figure-of-eight shape or two loops 7 and 8 which lie in the same plane. This is particularly advantageous for obtaining a configuration with reduced hindrance, so as to allow the folding of the two loops into a compact and closed coil configuration having two
  • Figure 3b and figure 3c show the folding of the flexible frame from the twisted configuration when the two convolutions lie in the same plane.
  • One convolution is folded following the arrow 9 in figure 3b so as to produce a coil configuration where the two intermeshing convolutions are overlapping as shown in figure 3d.
  • the coil configuration may be maintained by the presence of means for holding (not shown).
  • the coil configuration may not require a strong holding means.
  • a single or multiple strap thin wire or for celestial application a burnable resistance or a pyrotechnic device are examples of holding means.
  • Other examples of holding means are pin lock type, magnetic lock system or electrically activated hook devices, e.g. the electricity necessary for the opening may be also provided by the solar energy converter in its folded position.
  • Releasing of the holding means allows for restoration of the initial configuration of the flexible frame.
  • the release will be initially slow but will increase its speed of opening proportionally to the elasticity of the frame.
  • the releasing of the stressed configuration by removal of the holding means would be advantageously carried out virtually without introduction of energy in the structure.
  • energy neutrality is advantageous to avoid influence from the releasing of the flexible frame into a system, e.g. a satellite connected to the frame.
  • the degree of twisting may be different, so that the two loops formed may lie in separate planes. This allows for folding of the two loops formed into a less compact configuration. While the formation of two loops on the same plane is not essential, indeed leads to a very compact folded configuration. The twisting may continue so that formation of more convolutions is possible. For example figure 4a shows the twisted configuration where three loops or
  • FIG. 4b shows the folded compact configuration where the three convolutions formed are folded to create a closed coil, e.g. by interposing the third convolution between the first and the second convolution.
  • more convolutions can be formed with the advantage of reducing the coil diameter and therefore increasing the stowing capacity.
  • Figure 5 shows an example of a flexible frame 1 supporting a collector 2 of electromagnetic radiations which is produced in a continuous film sheet.
  • Film sheets can be provided in materials which are light in weight, not brittle, elastic and can be folded without substantial loss of their mechanical, physical and optical properties.
  • the collector of electromagnetic radiations is formed by units.
  • Figure 6 shows an embodiment where the flexible frame supports a collector of electromagnetic radiations which is formed by units 13.
  • the collector of electromagnetic radiations is formed by units mounted on a substrate along reinforced folding lines.
  • these units are single solar cells, e.g. 13 mounted on a substrate 14, e.g. a solar sail, and may be connected together.
  • This configuration using single units may be advantageous as more robust to the mechanical stress which occurs during the twisting and folding as the solar cells may be mounted on a substrate along reinforced folding lines.
  • Figure 7 shows another embodiment where the collector of electromagnetic radiations 16, e.g. a solar cell is provided in a single film with a central void 15.
  • the presence of the void may facilitate the folding of the frame.
  • a circular self deployable unfolding solar panel supported by the flexible frame according to the invention with frame thickness of 20 mm have, after twisting, folding and compressing, a compact configuration height of 40 mm in the case of two intermeshing convolution or 60 mm in the case of three intermeshing convolution, with a respective diameter ratio of 1,8 or 2,5.
  • the satellite M-SAT 1 launched in 1996 had the dimension of a cone truncated with a top diameter of 1500 mm, a bottom diameter of 3000 mm and a cone height of 4900 mm and storing two solar panels.
  • the present method will allow for storing of 62 solar panels with a diameter ranging between 5500-2700 mm or 40 solar panels with a diameter ranging between 7500-3750 mm respectively for the two or three intermeshing convolution coil configuration.
  • the present method gives an advantage by increasing the storage capacity of a satellite, such M-SATl, by at least 40 times.

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Abstract

La présente invention porte sur des structures flexibles supportant des collecteurs de rayonnement électromagnétique, tels que des antennes, des réflecteurs d'antenne, des déflecteurs ou des collecteurs solaires, pour des applications astronomiques ou terrestres, qui peuvent être pliées pour être stockées et/ou transportées. Le procédé de rangement déforme la structure flexible en une configuration contrainte. Une fois libérée de la configuration contrainte, la structure flexible reprend sa configuration initiale sans aucune intervention externe.
PCT/DK2010/050186 2009-07-15 2010-07-14 Structure pliante supportant des collecteurs de rayonnement électromagnétique WO2011006506A1 (fr)

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DKPA200970063 2009-07-15

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JP2012121392A (ja) * 2010-12-07 2012-06-28 Nec Toshiba Space Systems Ltd 展開物の結合構造
GB2487391A (en) * 2011-01-19 2012-07-25 Chris Coster Portable antenna array formed on a flexible substrate
WO2014024199A1 (fr) * 2012-08-08 2014-02-13 Halsband Arie Micro-satellite de faible volume comprenant panneaux enroulés souples extensibles après lancement
EP2915753A1 (fr) * 2013-03-15 2015-09-09 The Boeing Company Système de déploiement d'un composant
JP2015168422A (ja) * 2014-03-05 2015-09-28 ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ 構造部材展開システム
US20160376037A1 (en) 2014-05-14 2016-12-29 California Institute Of Technology Large-Scale Space-Based Solar Power Station: Packaging, Deployment and Stabilization of Lightweight Structures
WO2018064288A1 (fr) * 2016-09-28 2018-04-05 Stryker Corporation Antenne de détection pliable pour articles chirurgicaux
US10454565B2 (en) 2015-08-10 2019-10-22 California Institute Of Technology Systems and methods for performing shape estimation using sun sensors in large-scale space-based solar power stations
US10696428B2 (en) 2015-07-22 2020-06-30 California Institute Of Technology Large-area structures for compact packaging
CN112072269A (zh) * 2020-09-28 2020-12-11 中国电子科技集团公司第五十四研究所 一种充气天线组成单元
US10992253B2 (en) 2015-08-10 2021-04-27 California Institute Of Technology Compactable power generation arrays
US11128179B2 (en) 2014-05-14 2021-09-21 California Institute Of Technology Large-scale space-based solar power station: power transmission using steerable beams
CN113548201A (zh) * 2021-07-21 2021-10-26 上海宇航系统工程研究所 一种扇形太阳翼重复展开收拢锁定机构
US11362228B2 (en) 2014-06-02 2022-06-14 California Institute Of Technology Large-scale space-based solar power station: efficient power generation tiles
US11634240B2 (en) 2018-07-17 2023-04-25 California Institute Of Technology Coilable thin-walled longerons and coilable structures implementing longerons and methods for their manufacture and coiling
US11772826B2 (en) 2018-10-31 2023-10-03 California Institute Of Technology Actively controlled spacecraft deployment mechanism
US12021162B2 (en) 2014-06-02 2024-06-25 California Institute Of Technology Ultralight photovoltaic power generation tiles

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US20160376037A1 (en) 2014-05-14 2016-12-29 California Institute Of Technology Large-Scale Space-Based Solar Power Station: Packaging, Deployment and Stabilization of Lightweight Structures
US11128179B2 (en) 2014-05-14 2021-09-21 California Institute Of Technology Large-scale space-based solar power station: power transmission using steerable beams
US10144533B2 (en) 2014-05-14 2018-12-04 California Institute Of Technology Large-scale space-based solar power station: multi-scale modular space power
US10340698B2 (en) 2014-05-14 2019-07-02 California Institute Of Technology Large-scale space-based solar power station: packaging, deployment and stabilization of lightweight structures
US11362228B2 (en) 2014-06-02 2022-06-14 California Institute Of Technology Large-scale space-based solar power station: efficient power generation tiles
US12021162B2 (en) 2014-06-02 2024-06-25 California Institute Of Technology Ultralight photovoltaic power generation tiles
US10696428B2 (en) 2015-07-22 2020-06-30 California Institute Of Technology Large-area structures for compact packaging
US10749593B2 (en) 2015-08-10 2020-08-18 California Institute Of Technology Systems and methods for controlling supply voltages of stacked power amplifiers
US10992253B2 (en) 2015-08-10 2021-04-27 California Institute Of Technology Compactable power generation arrays
US10454565B2 (en) 2015-08-10 2019-10-22 California Institute Of Technology Systems and methods for performing shape estimation using sun sensors in large-scale space-based solar power stations
WO2018064288A1 (fr) * 2016-09-28 2018-04-05 Stryker Corporation Antenne de détection pliable pour articles chirurgicaux
US11759263B2 (en) 2016-09-28 2023-09-19 Stryker Corporation Collapsible detection antenna for surgical articles
US11634240B2 (en) 2018-07-17 2023-04-25 California Institute Of Technology Coilable thin-walled longerons and coilable structures implementing longerons and methods for their manufacture and coiling
US11772826B2 (en) 2018-10-31 2023-10-03 California Institute Of Technology Actively controlled spacecraft deployment mechanism
CN112072269B (zh) * 2020-09-28 2023-09-08 中国电子科技集团公司第五十四研究所 一种充气天线组成单元
CN112072269A (zh) * 2020-09-28 2020-12-11 中国电子科技集团公司第五十四研究所 一种充气天线组成单元
CN113548201A (zh) * 2021-07-21 2021-10-26 上海宇航系统工程研究所 一种扇形太阳翼重复展开收拢锁定机构
CN113548201B (zh) * 2021-07-21 2022-08-05 上海宇航系统工程研究所 一种扇形太阳翼重复展开收拢锁定机构

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