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WO2000034123A1 - Generateur solaire deployable pour engin volant spatial - Google Patents

Generateur solaire deployable pour engin volant spatial Download PDF

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Publication number
WO2000034123A1
WO2000034123A1 PCT/DE1999/003769 DE9903769W WO0034123A1 WO 2000034123 A1 WO2000034123 A1 WO 2000034123A1 DE 9903769 W DE9903769 W DE 9903769W WO 0034123 A1 WO0034123 A1 WO 0034123A1
Authority
WO
WIPO (PCT)
Prior art keywords
generator
solar generator
solar
generator according
fields
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/DE1999/003769
Other languages
German (de)
English (en)
Inventor
Jürgen JANSON
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mercedes Benz Group AG
Original Assignee
DaimlerChrysler AG
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 DaimlerChrysler AG filed Critical DaimlerChrysler AG
Publication of WO2000034123A1 publication Critical patent/WO2000034123A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • B64G1/443—Photovoltaic cell 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
    • B64G1/2223—Folding via scissor linkage
    • 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
    • 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
    • B64G1/2229—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 deployment actuating mechanism
    • 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 invention relates to a solar generator for a spacecraft, which can be deployed from a stowed state to an open state, with a generator field which contains a number of movably connected partial fields which lie one on top of the other in the stowed state of the generator and spread out in the open state of the generator, and with a device for unfolding the solar generator.
  • deployable solar generators that contain one or more generator fields that are folded into a jammed state for transport into earth orbit and unfolded into an open state after reaching earth orbit.
  • the solar generator For transport, the solar generator should take up as little space as possible in its stowed state; after unfolding, it should provide as large an area as possible for converting solar radiation into electrical energy.
  • a high degree of reliability of the deployment process is essential for the solar generator.
  • a deployable solar generator for a spacecraft which consists of two accordion-folded generator fields formed by a number of movably connected sub-fields consists. These can be unfolded from a folded position, in which the subfields of the generator field lie compactly on top of one another, into an essentially flat position.
  • Two generator fields initially stowed side by side on the surface of the spacecraft in the folded state are first spread out during the deployment so that they lie in one plane, and then stretched and unfolded by means of a deployable mast.
  • the deployable mast consists of two mast sections connected by means of a hinge, the ends of the mast sections remote from the hinge being coupled to respective end members of the generator fields folded in accordion shape. When the generator fields are deployed, the scissors formed by the two mast sections of the deployable mast describe a movement in a plane perpendicular to the plane of the generator fields.
  • DE 32 10 312 C3 discloses a deployable solar generator for a spacecraft which contains a generator field which is formed from a plurality of carrier film sections connected by hinges in the manner of piano hinge hinges.
  • a deployable solar generator for a spacecraft which in turn contains a generator field formed from a number of sub-fields interconnected in the manner of an accordion.
  • the partial fields are accommodated one on top of the other in a container, from which they are unfolded during the unfolding process by means of a cable pull mechanism and a movable mast, which is coupled to an end member of the generator field.
  • the object of the invention is to provide a simply constructed, light weight and reliably deployable solar generator for a spacecraft.
  • a solar generator for a spacecraft which can be deployed from a stowed state to an open state.
  • the solar generator contains at least one generator field which contains a number of movably connected sub-fields which lie one on top of the other in the stowed state of the generator and spread out in the open state of the generator.
  • a device for unfolding the solar generator is also provided. According to the invention it is provided that the device for unfolding the solar generator contains a number of longitudinally extended elements which are arranged pivotably in a plane parallel to the plane of the generator field and are coupled to the generator field in the sense of spreading the same when the longitudinally extended elements are pivoted.
  • the longitudinally extended elements are preferably movably connected to one another.
  • the longitudinally extended elements are movably connected to one another at their ends.
  • the longitudinally extended elements can be connected to one another by joints or by flexible elements.
  • the elongated elements are arranged in a zigzag shape.
  • the longitudinally extended elements form two zigzag arrangements extending over the length of the spread generator field.
  • the longitudinally extended elements can be arranged in a scissor-shaped manner crossing one or more times.
  • the ends of the arrangement formed by the longitudinally extended elements are preferably movably connected to end members of the generator field by joints or flexible elements.
  • the arrangement formed by the longitudinally extended elements is preferably arranged on the rear of the generator field.
  • the generator field is formed by flexible sub-fields arranged in accordion form or connected to one another by hinges, and at least some of the sub-fields are connected to the longitudinally extended elements by coupling members.
  • the longitudinally extended elements are advantageously designed as lightweight components.
  • the elongated elements are formed by rods.
  • the solar generator contains two diametrically arranged generator fields.
  • the generator feeder (s) are arranged on a holding and actuating device which serves to adjust the position of the generator fields and which is connected to the spacecraft by means of a deployable mast.
  • a further development of the aforementioned embodiment of the invention is particularly advantageous, in which the two generator fields in the stowed state of the solar generator with partial fields lying one on top of the other are arranged in the form of flat packets in a stowed position next to one another on a surface of the spacecraft, the flat packets formed by the partial fields lying on one another are rotatable into an unfolding position by means of the holding and actuating device.
  • This can be further developed in that the flat packets formed by the partial fields lying one on top of the other can be rotated in the unfolded position into a position with partial fields of the respective flat packets rotated essentially parallel to one another.
  • the folded mast is accommodated in the stowed state of the solar generator in a space between the flat packages formed by the partial fields lying one on top of the other.
  • Fig. La and b) in plan view a deployable solar generator for a spacecraft according to a first embodiment of the invention in the folded state or in the unfolded state;
  • FIG. 3 shows a perspective view of a deployable solar generator for a spacecraft according to a third exemplary embodiment of the invention in a state during the deployment of the solar generator;
  • FIG. 4 shows a deployable solar generator for a spacecraft in accordance with a fourth exemplary embodiment of the invention in a state during the deployment of the solar generator;
  • Fig. La) and b) show a plan view of a first embodiment of a deployable solar generator according to the invention.
  • the deployable solar generator used to power a spacecraft such as a telecommunications satellite, contains a generator field, which is provided with the reference number 10.
  • the generator field comprises a number of subfields 11 which are movably connected to one another, so that the generator field 10 can be folded and unfolded in an accordion-like manner.
  • the movable connection of the subfields 11 can take place, for example, by hinges in the manner of piano hinge or in that a substrate forming the generator field consists of a flexible material.
  • the subfields 11 lie flat on one another, so that they form a compact package 18, as shown in FIG.
  • the subfields 11 are spread out so that the generator field 10 reaches its full size, as can be seen in FIG. 1b).
  • a device for unfolding the solar generator, which is coupled to the generator field 10 is formed by a number of elongated elements 12, which are provided by rods in the exemplary embodiment shown.
  • a total of four rods 12 are provided, two of which are movably connected to one another in the region of the center of the generator field 10 by joints 14, while the distal ends of the rods 12 are coupled to end members 17 of the generator field 10 by means of joints 15.
  • the rods 12 are arranged pivotably in a plane parallel to the plane of the (unfolded) generator field 10 and, when pivoted from the stowed position of the generator field 10 shown in FIG. 1 a) into the unfolded position shown in FIG. 1 b), cause the sub-fields to spread out 11.
  • the device for unfolding the solar generator formed by the rods 12 is coupled to at least some of the subfields 11, at least namely via the End elements 17 with the last partial fields 11 of the generator field 10.
  • further partial fields 11 can be coupled to the bars 12 by coupling elements 16 in order to expand the partial fields 11.
  • a generator field designated overall by reference number 20
  • the individual partial fields 21 lie one on top of the other to form a compact flat packet 28, as shown in FIG. 1 a), while FIG. 1 b) shows the unfolded state of the generator field 20 with spread out partial fields 21.
  • a device for unfolding the generator field 20 is formed by elongated elements in the form of bars 22, 23. Of these rods 22, 23, two first rods 22 are arranged in a scissors-like manner, and are connected at their ends to joints 24 with second rods 23. The distal ends of these rods 23 are coupled by means of joints 25 to end members 27, which are each connected to the partial fields 21 located at the ends of the generator field 20.
  • the first rods 22 are pivoted in a scissor-like manner, the subfields 21 are moved in the sense of a spreading thereof, the device formed by the rods 22, 23 for unfolding the generator field via the joints 25 and the end members 27 at least onto the ends of the generator field 20 located subfields 21 acts.
  • coupling members 26 can be provided, with which the device formed by the rods 22, 23 for unfolding the solar generator can be coupled to further subfields 21.
  • FIG. 5a Four phases during the unfolding of the second embodiment of the deployable according to the invention shown in FIG. 2 Solar generators are shown in Fig. 5a) to d).
  • the subfields 21 of the generator field 20 lie one on top of the other so that they form a compact package 28, as shown in FIG. 5a).
  • the device for unfolding the solar generator formed by the rods 22, 23 is completely folded up.
  • the device formed by the rods 22, 23 for unfolding the solar generator is moved in a scissor-like manner by means of a drive (not shown in the figure), so that the end members 27 coupled with the second rods 23 and thus the Move the partial fields 21 located at the respective ends of the generator field 20 apart.
  • FIG. 3 shows a third exemplary embodiment of a deployable solar generator according to the invention, the generator field of which is designated as a whole by reference numeral 30.
  • the generator field 30 consists of a number of subfields 31 which are movably connected to one another in an accordion-like manner.
  • the individual subfields 31 can in turn be connected, for example, by hinges in the manner of piano hinge or by a flexible substrate.
  • a device for unfolding the solar generator is formed in the form of two zigzag arrangements which extend over the length of the generator field 30 and which are each formed from elongated elements 32, 33 in the form of bars.
  • First rods 32 are each connected to one another by joints or flexible elements 34.
  • each of the rods 32 is rotatably coupled to it by means of a coupling member 36 in the area of the hinge-like connections of two adjacent sub-fields 31.
  • the two arrangements formed by the rods 32, 33 each run in the opposite sense in a zigzag shape over the length of the generator field 30.
  • FIG. 4 shows a deployable solar generator according to a fourth exemplary embodiment of the invention.
  • the solar generator contains two diametrically arranged generator fields 40a, b. These are arranged on a common holding and actuating device 80, which is used to adjust the position of the generator fields 40a, b and which is connected to a spacecraft by means of a mast 60, which is merely indicated in FIG. 4 and is usually designed to be deployable.
  • Each of the generator fields 40a, b consists of a number of subfields 41, which in turn are connected to one another in an accordion-like manner, for example via hinges in the manner of piano hinge hinges or by a flexible substrate.
  • a device for unfolding the solar generator is provided, which is formed by elongated elements in the form of bars 42, 43.
  • Two first rods 42 are connected to one another at one end by means of joints 44 and to second rods 43 at the other end, the latter being coupled by means of further joints 45 to end members 47 which are provided on the respective last subfields 41 of the generator fields 40a and 40b .
  • the first rods 42 are rotatably coupled to them by means of coupling members 46 in the region of the connection of two adjacent sub-fields 41 formed by the hinges or the flexible substrate.
  • the generator fields 40a, b are each spread out by spreading the device for unfolding the solar generator formed from the bars 42, 43.
  • each of the generator fields 50a, b consists of sub-fields 51 which are connected to one another in an accordion-like manner by means of hinges or by a flexible substrate.
  • First rods 52 are connected to one another at one end by means of joints 54 and to second rods 53 at the other end.
  • the second rods 53 are coupled at their distal ends by means of further joints 55 to end members 57 of the generator fields 50a, b, which are provided on the last partial fields 51 in each case.
  • the first rods 52 are each rotatably coupled to them by coupling members 56 in the area of the connection of two adjacent sub-fields 51 formed by the hinges or the flexible substrate.
  • the subfields 51 of the generator fields 50a, 50b lie one on top of the other to form compact flat packets 58a, b, wherein they are accommodated in a storage bay 3a of the spacecraft parallel to a surface 3 of the same.
  • the packs 58a, b of the generator fields 50a, b are connected to one another by the holding and actuating device 80, and the folded mast 60 is accommodated in this stowed state of the solar generator in a space which is between the flat packs 58a, b of the generator fields 50a, b available is.
  • the flat packs 58a, b formed by the subfields 51 of the generator fields 50a, b, the holding and actuating device 80 and the foldable mast 60 are stowed on the surface of the spacecraft with the smallest space requirement.
  • the flat packets 58a, b formed by the subfields 51 of the generator fields 50a, b can each be rotated by the holding and actuating device 80 into a position in which the subfields 51 are aligned essentially parallel to one another, cf.
  • the deployable mast 60 which consists of two mast sections 61, 62, is unfolded from the originally folded, stowed position into an extended position by means of a drive (not specifically shown in the figure), cf. Partial 7.
  • the deployable mast 60 is attached with its foot to an anchor joint 70 on the surface 3 of the spacecraft.
  • the generator fields 50a, b are set at an optimal angle to the direction of the solar radiation by means of the holding and actuating device 80 and by moving the mast 60 by means of the drive (not shown) mentioned above.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Photovoltaic Devices (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

L'invention concerne un générateur solaire pour engin volant spatial, déployable en un état d'ouverture, à partir d'un état empilé, et présentant un ou plusieurs champs de générateur (40a, b) comprenant une pluralité de champs partiels (41) reliés entre eux de façon mobile, disposés les uns au-dessus des autres en l'état empilé du générateur, et déployés en l'état ouvert du générateur. Un dispositif destiné à déployer le générateur solaire renferme une pluralité d'éléments s'étendant longitudinalement (barreaux 42, 43) qui sont disposés pivotants dans un plan parallèle au plan de chaque champ de générateur (40a, b) et qui sont couplés avec le champ de générateur (40a, b) dans le sens d'un déploiement de celui-ci lors du pivotement.
PCT/DE1999/003769 1998-12-04 1999-11-27 Generateur solaire deployable pour engin volant spatial Ceased WO2000034123A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19855994.1 1998-12-04
DE19855994A DE19855994A1 (de) 1998-12-04 1998-12-04 Entfaltbarer Solargenerator für einen Raumflugkörper

Publications (1)

Publication Number Publication Date
WO2000034123A1 true WO2000034123A1 (fr) 2000-06-15

Family

ID=7889982

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1999/003769 Ceased WO2000034123A1 (fr) 1998-12-04 1999-11-27 Generateur solaire deployable pour engin volant spatial

Country Status (2)

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DE (1) DE19855994A1 (fr)
WO (1) WO2000034123A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20230064039A1 (en) * 2021-09-01 2023-03-02 Maxar Space Llc Partially flexible solar array structure

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10048846C1 (de) * 2000-10-02 2001-09-13 Astrium Gmbh Ausfahrbarer Solargenerator mit ausfahrbarer Trägerstruktur
WO2011006506A1 (fr) * 2009-07-15 2011-01-20 Aalborg Universitet Structure pliante supportant des collecteurs de rayonnement électromagnétique

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3223839A1 (de) 1981-06-27 1983-02-03 British Aerospace Public Ltd. Co., London Zusammenfaltbarer schirmaufbau
DE3316789C2 (fr) 1983-05-07 1988-03-17 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt, De
DE3210312C2 (fr) 1982-03-20 1990-05-31 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen, De
US5131955A (en) * 1991-01-14 1992-07-21 General Dynamics Corporation/Space Systems Division Depolyable retractable photovoltaic concentrator solar array assembly for space applications
US5487791A (en) * 1994-05-25 1996-01-30 Aec Able Engineering Co., Inc. Stowable and self-deployable parallelogram-type panel array

Family Cites Families (2)

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Publication number Priority date Publication date Assignee Title
FR2081107A1 (fr) * 1970-03-05 1971-12-03 Nal Etu Spatiales Centre
US5857648A (en) * 1997-01-28 1999-01-12 Trw Inc. Precision deployable boom assembly

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3223839A1 (de) 1981-06-27 1983-02-03 British Aerospace Public Ltd. Co., London Zusammenfaltbarer schirmaufbau
DE3210312C2 (fr) 1982-03-20 1990-05-31 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen, De
DE3316789C2 (fr) 1983-05-07 1988-03-17 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt, De
US5131955A (en) * 1991-01-14 1992-07-21 General Dynamics Corporation/Space Systems Division Depolyable retractable photovoltaic concentrator solar array assembly for space applications
US5487791A (en) * 1994-05-25 1996-01-30 Aec Able Engineering Co., Inc. Stowable and self-deployable parallelogram-type panel array

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
CRUIJSSEN H J: "SOLAR ARRAY DESIGNS FOR COLUMBUS ELEMENTS", PROCEEDINGS OF THE EUROPEAN SPACE POWER CONFERENCE,NL,NOORDWIJK, ESA PUBLICATIONS, vol. -, 1989, pages 573 - 584, XP000173833 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20230064039A1 (en) * 2021-09-01 2023-03-02 Maxar Space Llc Partially flexible solar array structure
US11912440B2 (en) * 2021-09-01 2024-02-27 Maxar Space Llc Partially flexible solar array structure

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