US3606211A - Outrigger construction - Google Patents

Outrigger construction Download PDF

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Publication number
US3606211A
US3606211A US837713A US3606211DA US3606211A US 3606211 A US3606211 A US 3606211A US 837713 A US837713 A US 837713A US 3606211D A US3606211D A US 3606211DA US 3606211 A US3606211 A US 3606211A
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United States
Prior art keywords
outrigger
section
parts
main
auxiliary
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Expired - Lifetime
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US837713A
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English (en)
Inventor
Wolfgang Roersch
Gunther La Roche
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Airbus Defence and Space GmbH
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Messerschmitt Bolkow Blohm AG
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    • 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
    • B64G1/222—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
    • B64G1/2227—Inflating
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S136/00—Batteries: thermoelectric and photoelectric
    • Y10S136/291—Applications
    • Y10S136/292—Space - satellite

Definitions

  • An outrigger secured to a space vehicle is displaceable between an inoperative position mounted in a compact arrangement against the vehicle and an operative position in which it is extended outwardly from the vehicle.
  • the outrigger is formed of a main outrigger section which extends outwardly from the vehicle in the operative position and auxiliary outrigger sections which extend laterally from the main outrigger section in the operative position. In the inoperative position the auxiliary outrigger sections are disposed in a folded arrangement on the main outrigger section.
  • the present invention is directed to an outrigger construction secured to the outer surface of a space vehicle and is useful, for example, in mounting solar cells or for acting as an antenna, and, more particularly, it is directed to an outrigger formed of a main section and auxiliary sections which can be disposed in a compact arrangement against the outer surface of the space vehicle and then opened up or unfolded into an operative position extending outwardly from the vehicle.
  • Known outriggers for supporting solar cells have been formed of a number of rigid parts hinged together in a folded arrangement against the vehicle and when they are ready for use the rigid parts can be extended and assembled in the form of a rigid wing-like structure extending outwardly from the vehicle.
  • This type of outrigger has the disadvantage that its width is limited by the maximum length of the space vehicle and, as a result, affords a relatively small surface when extended for use.
  • Another outrigger which has been used, is formed at at least a pair of flexible, longitudinal extending girders which are wound about the space vessel. Extending between the flexible girders are mat-like devices on which the solar cells are mounted.
  • the girders are formed of tubes which can be inflated in the operating position and stiffened with plastic foam. Flexible lines are provided within the tubes forming the girders for conducting pressurized gas to the outer ends of the tubes. When the outrigger is wound about the vehicle the ends of the tubes are located on the outside. Similarly, this outrigger is limited in its width by the maximum length of the space vehicle and it cannot form large-surface outriggers for solar cells.
  • Another outrigger which has been used on space vehicles consists of a wire or strip of a nickel-titanium alice loy having about equal portions of nickel and titanium.
  • the wire cools oif slowly after heating through a certain temperature range of the transposition and stretching into the extended state.
  • the wire is wound below a certain temperature and can resume its original form after it has been heated through the temperature range required for arrangement in the extended state.
  • this outrigger construction is much too heavy to provide a large surfaced outrigger for supporting solar cells on a space vehicle.
  • Another object of the invention is to provide an outrigger construction which can be disposed in varied folded, wrapped or wound arrangements on the exterior surface of the space vehicle.
  • Still another object of the invention is to provide an outrigger construction formed of a main outrigger section made up of rigid parts and auxiliary outrigger sections extending laterally from the main outrigger section and formed of flexible members which can be stiffened to form a stable support structure.
  • Another object of the invention is to afford a simple arrangement for opening the outrigger construction from its inoperative to its operative position.
  • the outrigger construction is formed of a main outrigger section comprised of a number of rigid parts articulated to one another so that they can be arranged in a compact arrangement on the surface of the space vehicle and auxiliary outrigger sections foldable with the main outrigger sections and extendable laterally from the main outrigger section to form a greatly increased surface for supporting solar cells or the like.
  • the main outrigger section is formed of a number of parts of equal length with an auxiliary outrigger section being secured to each side of the parts for extending laterally outwardly from the main outrigger section.
  • a pair of spaced tubular members are secured to brackets mounted along the edge of each of the parts and extend laterally outwardly from the rigid parts on the opposite sides of the main outrigger section for supporting individual auxiliary outrigger sections.
  • the width of the individual auxiliary outrigger sections corresponds approximately to the length of the parts of the main outrigger section and their length is approximately an integral multiple of the width of the parts of the main outrigger section.
  • main outrigger section web members extend around three edges and form a three sided box each with an opening along an opposite edge of the part.
  • the auxiliary outrigger sections are folded into the boxes on the opposite surfaces of the parts and the open sides of the boxes face in the direction in which the auxiliary outrigger sections are extended from the inoperative position to the operative position.
  • the main outrigger section is formed of a number of parts made of light metal or plastic which are articulated together by means of hinges. In the inoperative position the parts of the main outrigger section can be folded in a compact arrangement and then can be opened into the operative position to form a rigid surface.
  • the auxiliary outrigger sections consist of tubular members which extend laterally from the main outrigger section with a sheet of a flexible material, such as polyamide or similar material, extending between the tubular members to provide the auxiliary outrigger surface.
  • the tubular members are provided with a glass fiber-gelatin lamination and initially they are made flexible by steeping in water or glycol. However, when disposed in the operative position the tubular members are automatically stiffened by evaporation of the steeping agent.
  • auxiliary outrigger sections Positioned within the flexible tubular members are small diameter, thin wall tubes formed of polyamide which give the tubular members their generally circular form by passing a pressurized gas through the tubes. Moreover, the pressurized gas within the tubes in the tubular members aids in the unfolding or opening of the auxiliary outrigger sections from the inoperative to the operative position.
  • the tubular members which act to stabilize the auxiliary outrigger sections are covered with a polyamide sheet which prevents the freezing of the water which gives the tubular member its flexibility. However, the sheet does not prevent the evaporation of the water.
  • the parts forming the main outrigger section are articulated together by equilaterally arranged hinges, and one or several of said main outrigger sections are wound side by side or in superimposed relationship in one or a number of polygonal sources about the surface of the space vehicle.
  • the parts of the main outrigger section can be displaced by means of a lifting cable, prestressed springs or by centrifugal forces.
  • the parts forming the main outrigger section are of equal length and a stabilizing tubular member is secured to each of the opposite edges of each part adjacent one end thereof.
  • the length of the tube members corresponds approximately to an integral multiple of the width of the parts of the main outrigger section.
  • the auxiliary outrigger sections are formed by placing a sheet of polyamide across the tubular members so that a continuous auxiliary outrigger section is provided. In the inoperative position the oppositely extending auxiliary outrigger sections are folded into one another in an interleaved arrangement on the parts of the main outrigger section. In this folded construction the portions of the auxiliary outrigger sections secured to the sides of the main outrigger section are located outwardly or on the top of the folded over arrangement.
  • auxiliary outrigger sections are folded on the main outrigger section which is wound about the space vehicle and fits in a correspondingly dimensioned recess in the vehicle so that the auxiliary outrigger sections lie between the parts forming the main outrigger section and the surface of the space vehicle.
  • the auxiliary outrigger sections are secured against displacement and against any friction damage caused by acceleration of the space vehicle.
  • the parts forming the main outrigger section are locked together by spring locks and can be opened by an explosive charge or by an unlocking mechanism.
  • the main outrigger section is formed of a plurality of parts of unequal length and has an auxiliary outrigger section extending laterally from each of its sides.
  • the parts of the main outrigger section are connected to each other by side bars or hinges and can be positioned relative to one another at angles of 90 and 180 degrees respectively.
  • the stabilizing tubular members of the auxiliary outrigger section are divided into two types, the first type extend along the inner and outer edges of the auxiliary outrigger section and have a uniform circular cross-section, the second type of tubular members are located intermediate the edges and extend laterally outwardly from the main outrigger section.
  • the second type of tubular members are provided with reinforcing adjacent the main outrigger section and are folded in flat double layer strips in the inoperative position. Due to their reinforcing, the second type of tubular members have a conical appearance and,
  • the auxiliary outrigger section has the reinforced sections of the second type of tubular members adjacent the parts forming the main outrigger section. Further, in the. inoperative position the main outrigger section and its auxiliary outrigger sections are wound in a manner similar to a rolling shutter providing a compact arrangement against the surface of the space vehicle.
  • the outer surfaces of the main outrigger section in the inoperative position are provided with a lifting cable for displacing the outrigger from its inoperative to its operative position.
  • One or more of these Outriggers can be wound about the space vehicle and nothing is changed in the manner in which the auxiliary outrigger sections are folded on the main outrigger section.
  • auxiliary outrigger sections where the auxiliary outrigger sections are folded so that the portions of the auxiliary outrigger section disposed adjacent the main outrigger section in the operative position are located adjacent the parts forming the main outrigger section, thin tubes of polyamide are inserted into the stabilizing tubular members and these tubes conduct pressurized gas which serves to unfold the auxiliary outrigger sections into the operative positions.
  • the entire surface of the outrigger or certain parts may be covered and protected by a thin foam rubber mat when in the inoperative position. This protective covering prevents displacement and frictional damage which may occur due to the operation of the space vehicle. Since the rubber mat is not connected to the outrigger but is placed between adjacent surfaces in the folded inoperative position it can drop off the outrigger when it is opened into its operative position.
  • FIG. 1 is a view of one embodiment of the present invention illustrating a pair of outriggers secured to a space vehicle;
  • FIG. 2 is a partial view, similar to FIG. 1, with one of the Outriggers extended into its operating position;
  • FIG. 3 is a cross-sectional view through a portion of the outrigger shown in FIG. 1 with the outrigger in its inoperative position;
  • FIG. 4 is an enlarged cross-sectional view of a stablizing tube member shown in FIG. 2;
  • FIG. 5 is a cross-sectional view of the stabilizing tube member displayed in FIG. 4, shown expanded into a circular form;
  • FIG. 6 is a top view of an octagonal space vehicle having the outriggers as shown in FIG. 1 wrapped around the vehicle;
  • FIG. 7 is a perspective view of another embodiment of the present invention, illustrating a hexagonal space vehicle to which two outriggers are secured with one outrigger in the extended operating position and the other outrigger in a position intermediate the inoperative and operative position;
  • FIG. 8 is a transverse view through a part of the outrigger illustrated in FIG. 7 with the outrigger in its folded inoperative position;
  • FIG. 9 is a plan view of another embodiment of the present invention illustrating an outrigger in its extended operating position
  • FIG. 10 is a transverse view of a position of the outrigger illustrated in FIG. 9 with the outrigger disposed in its folded inoperative position;
  • FIG. 11 is a partial top view of a polygonal space vessel having an outrigger secured to it and arranged in its operative position.
  • FIG. 1 a rectangularly shaped space vehicle 1 is shown having an outrigger 2 secured to each of a pair of its opposite sides.
  • the outrigger 2 is arranged in the inoperative folded or collapsed position while in FIG. 2 the outrigger is shown in its opened or operative position.
  • Each of the Outriggers 2 is formed of a main outrigger section comprised of the parts 3 and a pair of auxiliary outrigger sections 6 extending laterally from the parts 3 and disposed in the same plane with the main outrigger section.
  • the main outrigger section is comprised of equal length rigid parts 3 made of a light metal or plastic which are connected by means of hinges 4 and prestressed springs 5 in a serial arrangement extending outwardly from vessel 1.
  • hinges 4 When the outrigger is opened to the operative position the hinges are automatically locked so that the main outrigger section provides a rigid, outwardly extending memher.
  • an auxiliary outrigger section 6 extends from each side of the main outrigger section.
  • one auxiliary outrigger section is mounted or positioned on each face of the parts 3 of the main outrigger section.
  • the auxiliary outrigger sections are made up of separate subsections each consisting of a pair of stabilizing tubular members 7 formed of glass fiber-gelatin-laminates. Initially, before the tubular members 7 are folded into the inoperative position of the outrigger they are steeped in water or glycol which makes them flexible so that they may be folded or collapsed as desired.
  • inflatable tubes made of polyamide act as spacers for the tubular members 7 and afford additional support for the auxiliary outrigger sections as the tubular members stiffen in the operating position.
  • the inner ends of the tubular members 7 are reinforced and are clamped tightly in mounting brackets 8 located at the opposite corners of the side edges of the parts 3.
  • mounting brackets 8 located at the opposite corners of the side edges of the parts 3.
  • a plurality of rectangular surfaces 9 are provided by the polyamide sheets and these surfaces provide support for solar cells and electrical Wiring, not shown.
  • the diameter, wall thickness, length, number and spacing of the stabilizing tubular member 7 and the intermediate support tubes 10 depend on the size of the auxilary outrigger sections and on the load which they support. It will be noted that the interval or spacing between the stabilizing tubular members which define the sides of the individual subsections of the auxiliary outrigger sections 6 are approximately equal to the length of the parts 3 which make up the main outrigger section.
  • FIG. 3 the manner in which the auxiliary outrigger sections are folded on the opposite surfaces of the parts 3 of the main outrigger section is illustrated.
  • web surfaces 12 extend in an upright manner from three of the edges of the part 3 providing an upwardly and a downwardly extending box 13 with the upper box opened on the left hand side and the lower box opened on the right hand side of the part 3.
  • a thin foam rubber mat 14 is indicated in dot-dash lines between a pair of opposed surfaces of the auxiliary outrigger section.
  • the rubber mat 14 is provided as a protective covering for the folded surfaces. The mat 14 prevents displacement and protects against any pressure or frictional damages which might occur during acceleration of the space vehicle. In outer space, when the outrigger is opened up into the operative position, the rubber mat, since it is not secured to the outrigger, will drop off.
  • the auxiliary outrigger sections are folded up so that the outer portion of the auxiliary outrigger section, that is the part most remote from the rigid part 3 in the operative position, is positioned on the outside or is the furthest distant from the part 3.
  • a similar arrangement is provided on both the top and bottom of the part 3, the upper part opens to the left and the lower part opens to the right with the open side of the boxes 13 providing the space through which the auxiliary outrigger sections extend from the parts 3.
  • the stabilizing tubular members 7 are folded over in double layer strips.
  • a thin wall tube 15 of polyamide is inserted into the tubular members.
  • This thin wall tube 15 serves as a passageway for pressurized gas which unfolds the auxiliary outrigger section 6.
  • the pressurized gas is received from a central gas system located within the space vehicle.
  • a sheet 16 of polyamide Covering the exterior of the stabilizing tubular members 7 is a sheet 16 of polyamide.
  • the sheet 16 prevents freezing of water in which the material of the tube has been steeped to make it flexible, however, the sheet does not prevent the evaporation of the water which affords the rigidity of the tubular member 7 so that the auxiliary outrigger sections form a continuation of the plane of the main outrigger section.
  • the outrigger 2 can be provided with hinges ⁇ 17 for connecting the parts 3 of the main outrigger section together.
  • the parts 3 of the main outrigger section are wound or wrapped in a polygonal course about the outer surface of a space vessel 18. While only a single course is shown disposed about the vehicle 18 it would also be possible to wrap the outrigger 2 in I several layers about the vehicle.
  • a cable line 19 operated by means of a motor extends the parts 3 into the operating position outwardly from the vehicle.
  • the opening operation can also be effected by prestressed lockable springs 20 or by centrifugal forces.
  • the main outrigger sections are made up of parts 21 of equal length extending outwardly from the polygonal shaped space vehicle 24. Projecting outwardly from each side of the main outrigger section formed by the parts 21 is an auxiliary outrigger section 22.
  • a stabilizing tubular member 7 extends laterally from each of the parts 21 being secured to the part 21 at the corner of its edge spaced more remote from the vehicle 24. Accordingly. a plurality of tubular members extend laterally from the main outrigger section and are spaced apart approximately the same distance as the length of each of the parts 21.
  • the length of the stabilizing tube members 7 is an integral multiple of the width of the parts 21, see FIG. 8.
  • Extending outwardly from the main outrigger section and secured to the tubular members 7 is a sheet of a flexible material, as disclosed above, which forms the support surface for the auxiliary outrigger sections 2 2.
  • At the ends of the tubular members 7 are provided inflatable tubes 10 made of polyamide acting as spacers for tubular members 7.
  • FIG. 8 thearrangement of the auxiliary outrigger sections in the inoperative position are shown in a folded over interleaved assembly resting on the surfaces of the parts '21.
  • the portions of the auxiliary outrigger section located closest to the main outrigger section in the opened operative position are located on the outer part of the folded construction.
  • the outriggers are wound or wrapped in a specially provided and correspondingly dimensioned recess in the space vehicle 24 in such a way that the parts 21 are located outwardly and the auxiliary outrigger sections are located between the parts 21 and the surface of the space vehicle 2 4. Accordingly, the auxiliary outrigger sections are protected against displacement and friction damage due to the acceleration of the space vehicle.
  • the parts 21 of the main outrigger section are locked in place by spring locks 25, which can be opened by explosive means or by an unfolding mechamsm.
  • the main outrigger sections are unwound or rolled out of the recess 23 in the vehicle by means of a lifting cable with each part of the main outrigger section acting as a lever arm. While the main outrigger section is being opened, the auxiliary outrigger sections '22 remain secured on the parts 21 by bands 26, shown schematically in FIG. 7.
  • the bands 26 are loosened by the lifting cable, and then the auxiliary outrigger sections are opened laterally outwardly from the main outrigger section by inflating the polyamide tubes '15 within the stabilizing tubular member 7 by supplying a pressurized gas into them from a central pressurized gas system located in the space vehicle 24.
  • FIG. 9 still another embodiment of the invention is illustrated, and it has the distinguishing characteristic that the parts 31 of the main outrigger section are of unequal length.
  • the parts 31 are connected together alternately by side bars 32 and by hinges 33 in such a way that the parts can be opened from the inoperative to the operative position so that the parts are disposed relative to one another by 90 or 180 degrees.
  • auxiliary outrigger section 36 Extending laterally from each side of the main outrigger section is an auxiliary outrigger section 36, the auxiliary outrigger sections 36 are supported from the edges of the parts 31 by means of first tubular members 7 and second tubular members 34.
  • the first tubular members are attached at the innermost end and at the outermost end of parts 31 forming the inner and outer edges of the auxiliary outrigger section.
  • second tubular members 34 Located at spaced loca tions between the first tubular members are second tubular members 34 extending outwardly from the sides of the parts 31 to the outer edge of the auxiliary outrigger section.
  • the second tubular members are secured to the parts 31 at the location of a joint between two adjacent parts 31.
  • the first tubular members 7 have a uniform circular cross-section throughout their length.
  • the second tubular members 34 are reinforced at their inner ends adjacent the parts 31 so they have a comically appearing shape with a decreasing cross-sectional size as they proceed outwardly from the main outrigger section.
  • a thin tube 35 formed of polyamide is located in each of the first and second tubular members 7 and 34.
  • a sheet of flexible material such as a sheet of polyamide extends across and is supported by the first and second tubular members 34 which provide a stabilizing and supporting effect for the sheet.
  • FIG. 10 the arrangement of the outrigger illustrated in FIG. 9 is shown in the inoperative or folded position with each of the oppositely extending auxiliary outrigger sections being folded in an interleaved arrangement supported on the par-ts 31 of the main outrigger section.
  • the auxiliary outrigger sections can be easily unfolded by means of the pressurized gas conducted through the tubes 35 to the ends of the stabilizing tubular members 7 and 34 remote from the main outrigger section.
  • the unfolding operation begins with the outer ends of the auxiliary outrigger sections with the two oppositely extending outrigger sections opening in an alternating arrangement.
  • the parts 31 of the main outrigger section which are of unequal length, are wound in a manner similar to a rolling shutter with the outermost part 31 being located in the center of the rolled arrangement.
  • the length of the unequal parts 31 corresponds to the dimensions of the rolled arrangements.
  • the unfolding or unrolling of the main outrigger section is performed, for example, by the lifting cable 37 shown in FIG. ll.
  • this embodiment of the outrigger could be wound in a polygonal course about the space vessel 18 and the folding pattern illustrated in FIG. 10 would still be the same.
  • An outrigger structure mounted on the exterior of a housing such as a space vehicle, comprising means forming a main outrigger section being displaceable between an inoperative position and an operative position, said means comprising a plurality of rectangularly shaped panel-like rigid parts, each said part being articulated to .at least one other said part, in the inoperative position said parts being arranged compactly against the housing, in the operative position said pants extending in a serially arranged manner outwardly from the housing and presenting oppositely facing rectangularly shaped surfaces which extend both in the direction outwardly from the housing and in the direction transverse to the outwardly extending direction of said parts, and auxiliary outrigger sections being connected to said parts of said main outrigger section and being displaceable between an inoperative position disposed in a compact arrangement on the surfaces of said parts of said main outrigger section to an operative position extending outwardly from. said rigid parts arranged in the operative position with said auxiliary outrigger sections extending in a direction transversely of the out
  • a cable secured about the exterior of said main outrigger section in the wound position and connected to each of said parts for assisting in extending said parts into the opened operative position.
  • An outrigger structure as set forth in claim 1, wherein said rigid parts being formed of a light metal or a plastics material.
  • tubular members are formed of glass fibergelatin-laminates, in the inoperative position said tubular members being made flexible by a steeping agent, such as water or glycol, whereby in the operative position the evaporation of the steeping agent causes the tubular members to become rigid.
  • a steeping agent such as water or glycol
  • An outrigger structure as set forth in claim 7, wherein an inner inflatable tube being located within said tubular member and being arranged to receive a pressurized gas for inflating said tubular member and for assisting in extending said auxiliary outrigger section from its inoperative to its operative position.
  • each said part of said main outrigger section having a leading edge more remote from the housing than a trailing edge there of and said longitudinally extending sides extending between the trailing edge and the leading edge of said part
  • each said auxiliary outrigger section comprising a pair of tubular members associated with one side of said part and one of said tubular members extending laterally from the trailing edge of said part and the other said tubular member extending laterally from the leading edge of said part, and a flexible material extending between and interconnecting said tubular members.
  • An outrigger structure as set forth in claim 10, characterized in that inflatable tubes being disposed in parallel relationship with the longitudinally extending sides of said parts and extending between and acting as spaces for the pair of said tubular members of said auxiliary outrigger section for forming support means therefor, and said inflatable tubes being arranged in spaced relationship.
  • An outrigger structure as set forth in claim 10, characterized in that one auxiliary outrigger section extends laterally outwardly from each of said longitudinally extending sides of said main outrigger section, and in the inoperative position each of said auxiliary outrigger sections being disposed in a folded over pattern on one of the oppositely facing rectangularly shaped surfaces of said parts of said main outrigger section.
  • An outrigger structure as set forth in claim 12, characterized in that web means secured to and extending outwardly from each of three edges of the oppositely facing rectangularly shaped surfaces of said parts so that a three sided box-like member is formed enclosing the folded arrangement of one of said outrigger sections on three sides with the fourth open side of said box-like member being on the side of said part from which the folded said auxiliary outrigger section extends.
  • An outrigger structure as set forth in claim 10, wherein a thin rubber mat being positioned between opposing faces of said auxiliary outrigger section in the folded inoperative position whereby said opposing faces are protected in the inoperative position of the outrigger and said rubber mat is displaceable from the outrigger structure when said auxiliary outrigger section is extended from its inoperative to its operative position.
  • An outrigger structure as set forth in claim 10, wherein said sheet of flexible material is formed of a polyimide.
  • An outrigger structure as set forth in claim. 1, where-in hinges articulating said parts together, and prestressed springs being positioned at the joint between adjacent said parts for assisting in positioning said parts in the operative position.
  • auxiliary outrigger section comprising a plurality of tubular members extending laterally from said main outrigger section and being disposed in substantially parallel relationship with one another, said tubular members being spaced apart by approximately the length of said parts forming said main outrigger section, and a sheet of flexible material extending between said tubular parts and forming the surface for said auxiliary outrigger section.
  • An outrigger structure as set forth in claim 18, characterized in that in the inoperative position said. main outrigger section being wrapped about the housing, said auxiliary outrigger sections arranged along the opposite sides of said main outrigger section being folded in an interleaved manner on the rectangularly shaped surfaces of said parts of said main outrigger section whereby after unwinding said main outrigger section from the inoperative position about the housing into its operative position said auxiliary outrigger sections can be unfolded laterally from said main outrigger section for completing the outrigger structure.
  • auxiliary outrigger section comprising a pair of first tubular members with one of said first tubular members extending laterally from the trailing edge of said parts of said main outrigger section located adjacent the housing and the other one extending laterally from the leading edge of said parts of said main operative section located at the outermost end thereof in the operative position, and at least one second tubular member extending laterally from the side of said main outrigger section in substantially parallel relationship with said first tubular members and being spaced from said first tubular members, and a sheet of flexible material secured between said first and second tubular members and extending laterally outwardly from said main outrigger section for forming the support surface for said auxiliary outrigger section.
  • An outrigger structure as set forth in claim 21, wherein an inner inflatable tube extending axially through said first and second tubular members for supplying a pressurized gas to the outer ends thereof for opening said 1 1 auxiliary outrigger sections from the inoperative to the operative position.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Tents Or Canopies (AREA)
  • Aerials With Secondary Devices (AREA)
  • Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
US837713A 1968-10-08 1969-06-30 Outrigger construction Expired - Lifetime US3606211A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19681801777 DE1801777B2 (de) 1968-10-08 1968-10-08 Ausleger zur aufnahme von sonnenzellen

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US4787580A (en) * 1985-06-27 1988-11-29 General Electric Company Large solar arrays with high natural frequencies
US20030173467A1 (en) * 2002-03-15 2003-09-18 Mitsubishi Denki Kabushiki Kaisha Satellite deployment structure
FR2853624A1 (fr) * 2003-04-14 2004-10-15 Eads Launch Vehicles Ensemble d'elements, pliable et deployable, monte a bord d'un engin spatial
FR2902764A1 (fr) * 2006-06-27 2007-12-28 Alcatel Sa Structure deployable comportant des elements rigides, embarquee sur un engin spatial
US20120234982A1 (en) * 2011-03-17 2012-09-20 Thales Retractable Plane Structure, and Satellite Comprising Such a Structure
FR3014848A1 (fr) * 2013-12-18 2015-06-19 Thales Sa Dispositif antichoc pour structure depliable
WO2022182904A1 (en) * 2021-02-26 2022-09-01 Trans Astronautica Corporation Pneumatically supported towers for low gravity applications
US11643930B2 (en) 2015-04-22 2023-05-09 Trans Astronautica Corporation Optics and structure for space applications
US11725513B2 (en) 2018-08-07 2023-08-15 Trans Astronautica Corporation Systems and methods for radiant gas dynamic mining of permafrost for propellant extraction
US11748897B1 (en) 2022-06-24 2023-09-05 Trans Astronautica Corporation Optimized matched filter tracking of space objects
CN118004451A (zh) * 2024-04-02 2024-05-10 北京航空航天大学 一种基于盘绕式伸展臂二次展开的多太阳翼同步展开装置
US12025006B2 (en) 2020-09-22 2024-07-02 Trans Astronautica Corporation Systems and methods for radiant gas dynamic mining of permafrost
US12025078B2 (en) 2020-04-27 2024-07-02 Trans Astronautica Corporation Omnivorous solar thermal thruster, cooling systems, and thermal energy transfer in rockets

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DE10334352A1 (de) * 2003-07-25 2005-02-24 Eads Astrium Gmbh Solargenerator zur Entfaltung in zwei Raumrichtungen
JP5080222B2 (ja) * 2007-11-30 2012-11-21 古河ユニック株式会社 車両搭載用の道路交通規制標識表示装置
WO2014024199A1 (en) 2012-08-08 2014-02-13 Halsband Arie Low volume micro satellite with flexible winded panels expandable after launch
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Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3735942A (en) * 1970-03-05 1973-05-29 Centre Nat Etd Spatiales Space station with solar generators
US3735943A (en) * 1970-03-05 1973-05-29 Centre Nat Etd Spatiales Space station with solar generators
US4787580A (en) * 1985-06-27 1988-11-29 General Electric Company Large solar arrays with high natural frequencies
US20030173467A1 (en) * 2002-03-15 2003-09-18 Mitsubishi Denki Kabushiki Kaisha Satellite deployment structure
US6722614B2 (en) * 2002-03-15 2004-04-20 Mitsubishi Denki Kabushiki Kaisha Satellite deployment structure
FR2853624A1 (fr) * 2003-04-14 2004-10-15 Eads Launch Vehicles Ensemble d'elements, pliable et deployable, monte a bord d'un engin spatial
EP1468910A1 (de) * 2003-04-14 2004-10-20 EADS SPACE Transportation SA Faltbarer und ausfahrbarer Satz von Elementen in einem Raumfahrzeug
JP2004314944A (ja) * 2003-04-14 2004-11-11 Eads Space Transporation Sa 宇宙船搭載用展開構造体の折畳連結構造
US20040245402A1 (en) * 2003-04-14 2004-12-09 Eads Space Transportation Sa Foldable and deployable assembly of elements mounted on board a spacecraft
US7093804B2 (en) 2003-04-14 2006-08-22 Eads Space Transportation Sa Foldable and deployable assembly of elements mounted on board a spacecraft
FR2902764A1 (fr) * 2006-06-27 2007-12-28 Alcatel Sa Structure deployable comportant des elements rigides, embarquee sur un engin spatial
EP1873061A1 (de) * 2006-06-27 2008-01-02 Thales Entfaltbare Struktur, die starre Elemente umfasst und auf einem Raumflugkörper untergebracht ist
US20120234982A1 (en) * 2011-03-17 2012-09-20 Thales Retractable Plane Structure, and Satellite Comprising Such a Structure
FR3014848A1 (fr) * 2013-12-18 2015-06-19 Thales Sa Dispositif antichoc pour structure depliable
EP2886467A1 (de) * 2013-12-18 2015-06-24 Thales Stoßdämpfende Vorrichtung für aufklappbare Struktur
US9969509B2 (en) 2013-12-18 2018-05-15 Thales Knock prevention device for unfurling structure
US11643930B2 (en) 2015-04-22 2023-05-09 Trans Astronautica Corporation Optics and structure for space applications
US11725513B2 (en) 2018-08-07 2023-08-15 Trans Astronautica Corporation Systems and methods for radiant gas dynamic mining of permafrost for propellant extraction
US12025078B2 (en) 2020-04-27 2024-07-02 Trans Astronautica Corporation Omnivorous solar thermal thruster, cooling systems, and thermal energy transfer in rockets
US12025006B2 (en) 2020-09-22 2024-07-02 Trans Astronautica Corporation Systems and methods for radiant gas dynamic mining of permafrost
WO2022182904A1 (en) * 2021-02-26 2022-09-01 Trans Astronautica Corporation Pneumatically supported towers for low gravity applications
US11702857B2 (en) 2021-02-26 2023-07-18 Trans Astronautica Corporation Pneumatically supported towers for low gravity applications
US11748897B1 (en) 2022-06-24 2023-09-05 Trans Astronautica Corporation Optimized matched filter tracking of space objects
CN118004451A (zh) * 2024-04-02 2024-05-10 北京航空航天大学 一种基于盘绕式伸展臂二次展开的多太阳翼同步展开装置
CN118004451B (zh) * 2024-04-02 2024-06-04 北京航空航天大学 一种基于盘绕式伸展臂二次展开的多太阳翼同步展开装置

Also Published As

Publication number Publication date
FR2020089B1 (de) 1974-05-24
JPS4750475B1 (de) 1972-12-18
FR2020089A1 (de) 1970-07-10
GB1268841A (en) 1972-03-29
DE1801777A1 (de) 1970-05-21
DE1801777B2 (de) 1971-12-30

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