US3717879A - Collapsible reflector - Google Patents

Collapsible reflector Download PDF

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US3717879A
US3717879A US00780771A US3717879DA US3717879A US 3717879 A US3717879 A US 3717879A US 00780771 A US00780771 A US 00780771A US 3717879D A US3717879D A US 3717879DA US 3717879 A US3717879 A US 3717879A
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reflector
panels
hub member
reflecting material
collapsible
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US00780771A
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E Ganssle
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NEOTEC Corp A CORP OF DE
Pacific Scientific Co
NEOTEC CORP
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Assigned to PACIFIC SCIENTIFIC COMPANY reassignment PACIFIC SCIENTIFIC COMPANY MERGER (SEE DOCUMENT FOR DETAILS). 6-4-82 Assignors: PACIFIC SCIENTIFIC INSTRUMENTS COMPANY
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    • 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
    • H01Q15/162—Collapsible reflectors composed of a plurality of rigid panels

Definitions

  • the reflector of the present invention is intended for use as a means for reflecting radiant energy.
  • the radiant energy may be either in the visible light spectrum or it may be microwave energy in which case the reflector may be used as an antenna assuming the shape of a paraboloid of revolution, for example. Since, for normal operating frequencies, the size of the reflector must be quite large, certain problems with respect to handling arise. For use in space, for example, it is desirable that such an antenna be foldable for storage in a launch vehicle and easily and automatically erectable when it reaches its destination.
  • the present invention not only overcomes the disadvantages of those antennas which are not suited for space application due to their construction using sliding parts and auxiliary means for erecting and locking the reflector in its erected configuration, but it also is superior to other known space antennas in that it is constructed to provide the necessary rigidity and contour control which is lacking in devices suggested heretofore.
  • the reflector of this invention takes the form of an automatically erecting surface of revolution which consists of a plurality of substantially rigid panels spaced around a central hub member and connected thereto by hinge means so that they may be folded adjacent the hub member for storage.
  • the reflecting surface of the panels can be solid skin, a supported flexible reflecting material or any combination thereof.
  • the panels are each articulated at approximately the center thereof and hinge means are provided so that the outer portion thereof may be folded adjacent the inner portion of the panel hinged to the hub member.
  • Flexible reflecting material is located between the adjacent sets of panels. Contoured radial formers may be spaced across this area sufficiently often to provide an additional degree of contour control for the flexible reflecting material. The formers are each split and the parts hinged together to allow them to be folded adjacent the hub in a manner similar to that of the panels.
  • Deployment energy can be provided by springs, electric motors, hydraulic, pneumatic or pyrotechnic pressure, or other equivalent means.
  • Restraining means are usually provided which are released at the moment it is most advantageous for the reflector to deploy itself in its operational configuration.
  • Another object of this invention is to provide a reflector which is automatically erectable when it reaches a predetermined destination.
  • the invention accordingly comprises the apparatus possessing the construction, combination of elements and arrangement of parts which are exemplified in the following detailed disclosure, and the scope of. the application of which will be indicated in the claims.
  • FIG. 1 is a perspective view of the reflector of this invention shown in its erected configuration
  • FIG. 2 is a front view of the reflector partially broken away to show the internal structure
  • FIG. 3 is a side view of the reflector shown in its collapsed condition and in dotted lines in its open position;
  • FIG. 4 is a back view of the reflector shown in its collapsed condition
  • FIG. 5 is a segmented view of the outside support ring.
  • FIG. 6 are schematic representations of some of the other possible configurations the reflector may have in its collapsed condition.
  • FIG. 1 a reflector 10 erected in operational configuration for use as a reflector of microwave energy.
  • the reflector comprises a plurality of panels 12 spaced around a central hub 14.
  • the panels 12 consist of a substantially rigid frame composed of struts 16., as shown exposed in FIG. 2, and each panel is covered with a reflecting material 18.
  • the reflecting material 18 may be a relatively stiff copper or aluminum mesh, for example, or even a solid sheet of metal stretched across the frame.
  • a sheet of flexible reflecting material 20 which may be composed, for example, of a flexible mesh of expanded aluminum fixed to a sheet of Mylar.
  • Contoured radial formers 22, as shown in FIG. 2 are spaced sufficiently often to provide the desired degree of contour control for the flexible reflecting material 20.
  • FIG. 2 shows the internal structure of the antenna in detail.
  • the hub structure is substantially circular in shape and is composed of supports 24 covered by a solid skin 26 which is a reflecting material.
  • the hub has a diameter no larger than the diameter of the antenna in its collapsed condition.
  • the panel struts 16 are hinged at joints 28 to the hub 14 and each panel 18 is articulated at approximately its midpoint and is hinged to itself at joints 30.
  • the articulation joints 30 as well as joints 28 comprise spring biased hinge means 31, shown schematically in FIG. 3, which supply energy for erecting the antenna.
  • the formers 22 are also articulated at approximately their midpoint and the two portions of each former may similarly be joined by spring biased hinge means 31.
  • the formers are also hinged to the panels 12 and/or to the hub 14 where they intersect these structures.
  • Restraining means 32 may comprise a simple link cable which with connecting cables 33 attach to a number of latches 34 which engage holding means 36 on the outer portions of panels 12, more clearly shown in FIG. 3.
  • the cables may be released by detonating upon signal an exploding link 39 which will release latches 34 and allow the antenna to deploy itself to its operational configuration.
  • Alternate means of restraining the panels include individual solenoid released latches, individual pyrotechnical releases, or pushrod actuated latches, or the like.
  • a hydraulic damper 35 or equivalent structure is provided on hub 14 as shown in FIG. 2.
  • Other means of rate control include pneumatic dampers, escapement mechanisms or a centrifugal brake.
  • the cable system consists of two cables attached to the panels 12.
  • Cable 47 as shown in FIG. 3, extends from the common rotating fitting 37, through the hubQaround pulley 35 and attaches to the inboard section 43 of the panels 12 thus constraining all inboard sections to the motion of the rotating fitting 37.
  • Cable 49 is attached at one end to the hub structure, passes around pulleys 48 and 50 and is attached at its other end to outboard section 45 of the panels 12, thus constraining the motion of the outboard sections to that of the inboard sections.
  • Deployment energy can be provided by springs such as the spring biased hinge means mentioned and additionally by electric motors or hydraulic, pneumatic, or pyrotechnic pressure or other means which will be apparent to those familiar with such deployment systems.
  • FIG. 4 of the drawing shows the collapsed reflector from the rear with all the panels 12 folded substantially flat upon themselves and against the hub as shown in solid lines in FIG. 3. Between the panels 12 the flexible material 20 is shown forming radial pleats 40 and also folded upon itself. The formers 22 supporting the flexible material are also folded at joints 38 substantially flat against themselves and against hub 14.
  • the outboard tips of the formers 22 should be structurally interconnected by a peripheral set of links as shown in the enlarged fragmentary view of FIG. 5.
  • Each link 41 and 42 is pivotally connected to the formers 22 and to each other to allow the formers to come together when the reflector is collapsed with the flexible material 20 radially pleated between the pair of formers.
  • a pair of stop members 44 and 46 are provided on links 41 and 42, respectively. The two stop members will come into abutment with each other, as shown in FIG. 5, as the formers spread apart to their proper deployed positions. It should be understood that other means such as support wires or expandable metal members might also be used interconnecting the former tips.
  • FIG. 6 is a series of schematic representations of some of the other possible configurations the reflector may have in its collapsed condition. These are only some of the variations of the invention which may become apparent from this disclosure.
  • One other extremely important variation of the invention is the aspect that within a given allowable stowed diameter in a space vehicle, for example, further growth in reflector size is achievable by adding outboard sections to a panel such as panel 12 in a radial direction, i.e., going from a two section panel to a panel having three, four or more sections as shown in FIG. 6.
  • a collapsible reflector adapted to automatically erect to the operational configuration of a surface of revolution, comprising:
  • a collapsible reflector as described in claim 1 including a plurality of formers supporting said flexible reflecting material when said reflector is in its erected configuration, an inner portion of said formers being hinged to said hub member and folded substantially flat against said hub member when said reflector is collapsed and said formers being articulated so that an outer portion thereof may be folded substantially flat against the inner portion when said reflector is in its collapsed condition.
  • a collapsible reflector as described in claim 2 including linking members connecting the outer tips of said formers with one another to enhance the rigidity of said reflector, said linking members being foldable when said reflector is collapsed and having stop members thereon to aid them in unfolding to their proper connecting position as said reflector unfolds from its collapsed condition to its operational configuration.
  • a collapsible reflector as described in claim 1 including at least one other set of substantially rigid folding panels connected to the outer portion of said folding panels connected to said hub member.
  • a collapsible reflector as described in claim 2 including means for providing the force required to cause said reflector to automatically erect to its operational configuration from its collapsed condition.
  • said panels to the inner portion thereof to provide the force required to cause said reflector to automatically erect to its operational configuration.
  • a collapsible reflector as described in claim 9 including link cable means to releasably restrain said reflector in its collapsed condition and exploding link means which are exploded to release said restraining means to allow said reflector to erect to its operational configuration.

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

This disclosure is directed to a collapsible reflector including a number of substantially rigid foldable panels covered with a reflecting surface spaced around a central hub and flexible reflecting material located between adjacent panels; the substantially rigid panels being folded adjacent the hub in a small volume for stowing and upon deployment providing the required stiffness and contour control for the reflector.

Description

United States Patent Ganssle 1 Feb. 20, 1973 [54] COLLAPSIBLE REFLECTOR [72] Inventor: Eugene R. Ganssle, Silver- Spring,
[73] Assignee: Neotec Corporation, Rockville, Md.
[22] Filed: Dec. 3, 1968 211 App]. No.: 780,771
52 u.s.c| ..343/915,350/292 51 Int.Cl. ..H0lq 15 20 58 FieldofSearch ..343/915;350/292,302
[5 6] References Cited UNITED STATES PATENTS Balton ..343/915 Holland et a1. ..343/9l5 Mason et al. ..343/9l5 Carman et al. ..343/915 Primary Examiner-Herman Karl Saalbach Assistant Examiner-Saxfleld Chatmon, Jr. Attorney-Leonard S. Selman [57] ABSTRACT This disclosure is directed to a collapsible reflector including a number of substantially rigid foldable panels covered with a reflecting surface spaced around a central hub and flexible reflecting material located between adjacent panels; the substantially rigid panels being folded adjacent the hub in a small volume for stowing and upon deployment providing the required stiffness and contour control for the reflector.
10 Claims, 6 Drawing Figures Pmmwr 3717. s19
sum 2 or 4 INVENTOR. EUGENE R GANSSLE AT TORNE Y PATENTED FEBZU i975 SHEEI 3 0F 4 INVENTCR. E UGENE R. GANSS LE W dam ATTORNEY PATEnmFtseoma v 7 ,879
I snmuora Fls. 6
f /1NVENTOR EUGENE R. GANSSLE ATTORNEY COLLAPSIBLE REFLECTOR The reflector of the present invention is intended for use as a means for reflecting radiant energy. The radiant energy may be either in the visible light spectrum or it may be microwave energy in which case the reflector may be used as an antenna assuming the shape of a paraboloid of revolution, for example. Since, for normal operating frequencies, the size of the reflector must be quite large, certain problems with respect to handling arise. For use in space, for example, it is desirable that such an antenna be foldable for storage in a launch vehicle and easily and automatically erectable when it reaches its destination.
The present invention not only overcomes the disadvantages of those antennas which are not suited for space application due to their construction using sliding parts and auxiliary means for erecting and locking the reflector in its erected configuration, but it also is superior to other known space antennas in that it is constructed to provide the necessary rigidity and contour control which is lacking in devices suggested heretofore.
The reflector of this invention takes the form of an automatically erecting surface of revolution which consists of a plurality of substantially rigid panels spaced around a central hub member and connected thereto by hinge means so that they may be folded adjacent the hub member for storage. The reflecting surface of the panels can be solid skin, a supported flexible reflecting material or any combination thereof. The panels are each articulated at approximately the center thereof and hinge means are provided so that the outer portion thereof may be folded adjacent the inner portion of the panel hinged to the hub member. Flexible reflecting material is located between the adjacent sets of panels. Contoured radial formers may be spaced across this area sufficiently often to provide an additional degree of contour control for the flexible reflecting material. The formers are each split and the parts hinged together to allow them to be folded adjacent the hub in a manner similar to that of the panels.
Deployment energy can be provided by springs, electric motors, hydraulic, pneumatic or pyrotechnic pressure, or other equivalent means. Restraining means are usually provided which are released at the moment it is most advantageous for the reflector to deploy itself in its operational configuration.
Accordingly, it is an object of this invention to provide a reflector which is collapsible into a minimum space, but which when erected has the required rigidity of structure to provide the optimum contour of the reflector when in operation.
Another object of this invention is to provide a reflector which is automatically erectable when it reaches a predetermined destination.
Other objects of the invention will in part be obvious and will in part appear hereinafter.
The invention accordingly comprises the apparatus possessing the construction, combination of elements and arrangement of parts which are exemplified in the following detailed disclosure, and the scope of. the application of which will be indicated in the claims.
2 BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view of the reflector of this invention shown in its erected configuration;
FIG. 2 is a front view of the reflector partially broken away to show the internal structure;
FIG. 3 is a side view of the reflector shown in its collapsed condition and in dotted lines in its open position;
FIG. 4 is a back view of the reflector shown in its collapsed condition;
FIG. 5 is a segmented view of the outside support ring; and
FIG. 6 are schematic representations of some of the other possible configurations the reflector may have in its collapsed condition.
DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to the drawings, there is shown in FIG. 1 a reflector 10 erected in operational configuration for use as a reflector of microwave energy. The reflector comprises a plurality of panels 12 spaced around a central hub 14. The panels 12 consist of a substantially rigid frame composed of struts 16., as shown exposed in FIG. 2, and each panel is covered with a reflecting material 18. The reflecting material 18 may be a relatively stiff copper or aluminum mesh, for example, or even a solid sheet of metal stretched across the frame. Between each alternating pair of substantially rigid panels 12 is a sheet of flexible reflecting material 20 which may be composed, for example, of a flexible mesh of expanded aluminum fixed to a sheet of Mylar. Contoured radial formers 22, as shown in FIG. 2, are spaced sufficiently often to provide the desired degree of contour control for the flexible reflecting material 20.
The broken away portion of FIG. 2 shows the internal structure of the antenna in detail. The hub structure is substantially circular in shape and is composed of supports 24 covered by a solid skin 26 which is a reflecting material. In the preferred embodiment of the invention the hub has a diameter no larger than the diameter of the antenna in its collapsed condition. The panel struts 16 are hinged at joints 28 to the hub 14 and each panel 18 is articulated at approximately its midpoint and is hinged to itself at joints 30. The articulation joints 30 as well as joints 28 comprise spring biased hinge means 31, shown schematically in FIG. 3, which supply energy for erecting the antenna. The formers 22 are also articulated at approximately their midpoint and the two portions of each former may similarly be joined by spring biased hinge means 31. The formers are also hinged to the panels 12 and/or to the hub 14 where they intersect these structures.
Restraining means 32, as shown in FIG. 2, may comprise a simple link cable which with connecting cables 33 attach to a number of latches 34 which engage holding means 36 on the outer portions of panels 12, more clearly shown in FIG. 3. The cables may be released by detonating upon signal an exploding link 39 which will release latches 34 and allow the antenna to deploy itself to its operational configuration. Alternate means of restraining the panels include individual solenoid released latches, individual pyrotechnical releases, or pushrod actuated latches, or the like. To control the rate of deployment, a hydraulic damper 35 or equivalent structure is provided on hub 14 as shown in FIG. 2. Other means of rate control include pneumatic dampers, escapement mechanisms or a centrifugal brake. Most reliable deployment will occur if all the panels 12 are synchronized to deploy at the same rate. This can be accomplished by a cable system which is constrained to deploy simultaneously by attachment to a common rotating fitting 37, as shown in FIG. 2, or other means such as synchronized motors, push rods,
torque rods, or the like. The cable system consists of two cables attached to the panels 12. Cable 47, as shown in FIG. 3, extends from the common rotating fitting 37, through the hubQaround pulley 35 and attaches to the inboard section 43 of the panels 12 thus constraining all inboard sections to the motion of the rotating fitting 37. Cable 49 is attached at one end to the hub structure, passes around pulleys 48 and 50 and is attached at its other end to outboard section 45 of the panels 12, thus constraining the motion of the outboard sections to that of the inboard sections. Deployment energy can be provided by springs such as the spring biased hinge means mentioned and additionally by electric motors or hydraulic, pneumatic, or pyrotechnic pressure or other means which will be apparent to those familiar with such deployment systems.
FIG. 4 of the drawing shows the collapsed reflector from the rear with all the panels 12 folded substantially flat upon themselves and against the hub as shown in solid lines in FIG. 3. Between the panels 12 the flexible material 20 is shown forming radial pleats 40 and also folded upon itself. The formers 22 supporting the flexible material are also folded at joints 38 substantially flat against themselves and against hub 14.
For optimum stiffness and contour control, the outboard tips of the formers 22 should be structurally interconnected by a peripheral set of links as shown in the enlarged fragmentary view of FIG. 5. Each link 41 and 42 is pivotally connected to the formers 22 and to each other to allow the formers to come together when the reflector is collapsed with the flexible material 20 radially pleated between the pair of formers. To provide a positive restraint for the formers upon deployment of the reflector, a pair of stop members 44 and 46 are provided on links 41 and 42, respectively. The two stop members will come into abutment with each other, as shown in FIG. 5, as the formers spread apart to their proper deployed positions. It should be understood that other means such as support wires or expandable metal members might also be used interconnecting the former tips.
FIG. 6 is a series of schematic representations of some of the other possible configurations the reflector may have in its collapsed condition. These are only some of the variations of the invention which may become apparent from this disclosure. One other extremely important variation of the invention is the aspect that within a given allowable stowed diameter in a space vehicle, for example, further growth in reflector size is achievable by adding outboard sections to a panel such as panel 12 in a radial direction, i.e., going from a two section panel to a panel having three, four or more sections as shown in FIG. 6.
Since certain changes may be made in the above apparatus without departing from the scope of the invention herein involved, it is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense.
I claim:
1. A collapsible reflector adapted to automatically erect to the operational configuration of a surface of revolution, comprising:
a substantially circular hub member, said hub member having a diameter no larger than said reflector in its collapsed condition;
a plurality of substantially rigid folding panels spaced around said hub member and connected thereto by hinge means so that they may fold substantially flat against said hub member when said reflector is collapsed, each of said panels being articulated so that the outer portion thereof may also be folded substantially flat against the inner portion of said panels hinged to said hub member;
flexible reflecting material spaced between said panels; and
relatively stiffer reflecting material than said flexible reflecting material covering said folding panels, said flexible reflecting material being pleated when said reflector is in its collapsed condition in contrast to said relatively stiffer reflecting material on said panels which remains stretched sheet-like across said folding panels when said reflector is either collapsed or in its operational configuration, the rigidity of said folding panels providing the required stiffness and contour control for the reflector.
2. A collapsible reflector as described in claim 1 including a plurality of formers supporting said flexible reflecting material when said reflector is in its erected configuration, an inner portion of said formers being hinged to said hub member and folded substantially flat against said hub member when said reflector is collapsed and said formers being articulated so that an outer portion thereof may be folded substantially flat against the inner portion when said reflector is in its collapsed condition.
3. A collapsible reflector as described in claim 2 including linking members connecting the outer tips of said formers with one another to enhance the rigidity of said reflector, said linking members being foldable when said reflector is collapsed and having stop members thereon to aid them in unfolding to their proper connecting position as said reflector unfolds from its collapsed condition to its operational configuration.
4. A collapsible reflector as described in claim 1 including at least one other set of substantially rigid folding panels connected to the outer portion of said folding panels connected to said hub member.
5. A collapsible reflector as described in claim 1 wherein its operational configuration assumes the shape of a paraboloid of revolution.
6. A collapsible reflector as described in claim 1 wherein said hub member is covered with reflecting material.
7. A collapsible reflector as described in claim 2 including means for providing the force required to cause said reflector to automatically erect to its operational configuration from its collapsed condition.
said panels to the inner portion thereof to provide the force required to cause said reflector to automatically erect to its operational configuration.
10. A collapsible reflector as described in claim 9 including link cable means to releasably restrain said reflector in its collapsed condition and exploding link means which are exploded to release said restraining means to allow said reflector to erect to its operational configuration.

Claims (10)

1. A collapsible reflector adapted to automatically erect to the operational configuration of a surface of revolution, comprising: a substantially circular hub member, said hub member having a diameter no larger than said reflector in its collapsed condition; a plurality of substantially rigid folding panels spaced around said hub member and connected thereto by hinge means so that they may fold substantially flat against said hub member when said reflector is collapsed, each of said panels being articulated so that the outer portion thereof may also be folded substantially flat against the inner portion of said panels hinged to said hub member; flexible reflecting material spaced between said panels; and relatively stiffer reflecting material than said flexible reflecting material covering said folding panels, said flexible reflecting material being pleated when said reflector is in its collapsed condition in contrast to said relatively stiffer reflecting material on said panels which remains stretched sheet-like across Said folding panels when said reflector is either collapsed or in its operational configuration, the rigidity of said folding panels providing the required stiffness and contour control for the reflector.
1. A collapsible reflector adapted to automatically erect to the operational configuration of a surface of revolution, comprising: a substantially circular hub member, said hub member having a diameter no larger than said reflector in its collapsed condition; a plurality of substantially rigid folding panels spaced around said hub member and connected thereto by hinge means so that they may fold substantially flat against said hub member when said reflector is collapsed, each of said panels being articulated so that the outer portion thereof may also be folded substantially flat against the inner portion of said panels hinged to said hub member; flexible reflecting material spaced between said panels; and relatively stiffer reflecting material than said flexible reflecting material covering said folding panels, said flexible reflecting material being pleated when said reflector is in its collapsed condition in contrast to said relatively stiffer reflecting material on said panels which remains stretched sheet-like across Said folding panels when said reflector is either collapsed or in its operational configuration, the rigidity of said folding panels providing the required stiffness and contour control for the reflector.
2. A collapsible reflector as described in claim 1 including a plurality of formers supporting said flexible reflecting material when said reflector is in its erected configuration, an inner portion of said formers being hinged to said hub member and folded substantially flat against said hub member when said reflector is collapsed and said formers being articulated so that an outer portion thereof may be folded substantially flat against the inner portion when said reflector is in its collapsed condition.
3. A collapsible reflector as described in claim 2 including linking members connecting the outer tips of said formers with one another to enhance the rigidity of said reflector, said linking members being foldable when said reflector is collapsed and having stop members thereon to aid them in unfolding to their proper connecting position as said reflector unfolds from its collapsed condition to its operational configuration.
4. A collapsible reflector as described in claim 1 including at least one other set of substantially rigid folding panels connected to the outer portion of said folding panels connected to said hub member.
5. A collapsible reflector as described in claim 1 wherein its operational configuration assumes the shape of a paraboloid of revolution.
6. A collapsible reflector as described in claim 1 wherein said hub member is covered with reflecting material.
7. A collapsible reflector as described in claim 2 including means for providing the force required to cause said reflector to automatically erect to its operational configuration from its collapsed condition.
8. A collapsible reflector as described in claim 7 including means for releasably restraining the reflector in its collapsed condition and means for releasing said restraining means to allow said reflector to unfold to its operational configuration.
9. A collapsible reflector as described in claim 8 wherein spring biased hinge means connect said folding panels to said hub and also connect the outer portion of said panels to the inner portion thereof to provide the force required to cause said reflector to automatically erect to its operational configuration.
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Cited By (30)

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US4291677A (en) * 1977-12-27 1981-09-29 Monk Robert J Solar energy collector
US4315265A (en) * 1980-06-11 1982-02-09 Trw Inc. Rigid collapsible dish structure
US4352113A (en) * 1980-07-11 1982-09-28 Societe Nationale Industrielle Aerospatiale Foldable antenna reflector
DE3315111A1 (en) * 1982-04-28 1983-11-03 British Aerospace Plc, London FOLDABLE REFLECTOR, IN PARTICULAR FOR SPACE VEHICLES
DE3333013A1 (en) * 1983-09-13 1985-03-21 Autoflug Gmbh, 2084 Rellingen Radar reflector of flat shape
FR2566588A1 (en) * 1984-06-26 1985-12-27 Messerschmitt Boelkow Blohm ANTENNA REFLECTOR DEPLIABLE AND REPLIABLE
US4612550A (en) * 1982-04-02 1986-09-16 Thomson Csf Inverted Cassegrain antenna for multiple function radars
US4646102A (en) * 1984-09-28 1987-02-24 Kabushiki Kaisha Toshiba Deployable antenna reflector apparatus
US4761655A (en) * 1984-11-30 1988-08-02 British Telecommunications Plc Transportable antenna for an earth station
US4780726A (en) * 1984-12-03 1988-10-25 Trw Inc. Depolyable reflector
US4845511A (en) * 1987-01-27 1989-07-04 Harris Corp. Space deployable domed solar concentrator with foldable panels and hinge therefor
US4862190A (en) * 1987-05-15 1989-08-29 Trw Inc. Deployable offset dish structure
US4989015A (en) * 1987-10-26 1991-01-29 Hughes Aircraft Company Unfurlable mesh reflector
US5642122A (en) * 1991-11-08 1997-06-24 Teledesic Corporation Spacecraft antennas and beam steering methods for satellite communciation system
US5864324A (en) * 1996-05-15 1999-01-26 Trw Inc. Telescoping deployable antenna reflector and method of deployment
US5898529A (en) * 1997-06-20 1999-04-27 Ball Aerospace & Technologies, Inc. Deployable space-based telescope
FR2778028A1 (en) * 1998-04-23 1999-10-29 Daimler Chrysler Ag REFLECTOR AND REFLECTOR ELEMENT FOR SPATIAL APPLICATION ANTENNAS AND A METHOD FOR DEPLOYING A REFLECTOR
US6191757B1 (en) * 1999-04-08 2001-02-20 Hughes Electronics Corporation System for compact stowage of segmented dish reflectors
WO2001022530A1 (en) * 1999-09-21 2001-03-29 The Johns Hokpins University Hybrid inflatable antenna
EP1168498A3 (en) * 2000-06-30 2002-09-18 Lockheed Martin Corporation Semi-rigid bendable reflecting structure
US20090180204A1 (en) * 2005-09-05 2009-07-16 Thales Deployable reflector in the form of a reuleaux triangle for a space observation instrument
CN102005635A (en) * 2010-12-01 2011-04-06 宁波森富机电制造有限公司 Composite parabolic antenna with octagonal central loading slice structure
RU2447550C2 (en) * 2010-05-04 2012-04-10 Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнева" Umbrella antenna for spacecraft
RU2449437C1 (en) * 2010-10-04 2012-04-27 Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнева" Deployable large-size spacecraft reflector and method of its manufacturing
US9331394B2 (en) 2011-09-21 2016-05-03 Harris Corporation Reflector systems having stowable rigid panels
US10236590B1 (en) * 2016-12-21 2019-03-19 The United States Of America, As Represented By The Secretary Of The Air Force Foldable segmented structure and deployable reflector antenna comprised thereof
US20190214737A1 (en) * 2018-01-08 2019-07-11 Umbra Lab, Inc. Articulated folding rib reflector for concentrating radiation
US10411363B2 (en) * 2017-05-15 2019-09-10 The Boeing Company Foldable dipole array antennas
WO2020002938A1 (en) * 2018-06-28 2020-01-02 Oxford Space Systems Limited Deployable membrane structure for an antenna
EP3654452A1 (en) * 2018-11-13 2020-05-20 Eagle Technology, LLC Mesh antenna reflector with deployable perimeter

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Cited By (39)

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US4291677A (en) * 1977-12-27 1981-09-29 Monk Robert J Solar energy collector
US4315265A (en) * 1980-06-11 1982-02-09 Trw Inc. Rigid collapsible dish structure
US4352113A (en) * 1980-07-11 1982-09-28 Societe Nationale Industrielle Aerospatiale Foldable antenna reflector
US4612550A (en) * 1982-04-02 1986-09-16 Thomson Csf Inverted Cassegrain antenna for multiple function radars
DE3315111A1 (en) * 1982-04-28 1983-11-03 British Aerospace Plc, London FOLDABLE REFLECTOR, IN PARTICULAR FOR SPACE VEHICLES
DE3333013A1 (en) * 1983-09-13 1985-03-21 Autoflug Gmbh, 2084 Rellingen Radar reflector of flat shape
US4658265A (en) * 1984-06-26 1987-04-14 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Foldable and unfoldable antenna reflector
FR2566588A1 (en) * 1984-06-26 1985-12-27 Messerschmitt Boelkow Blohm ANTENNA REFLECTOR DEPLIABLE AND REPLIABLE
US4646102A (en) * 1984-09-28 1987-02-24 Kabushiki Kaisha Toshiba Deployable antenna reflector apparatus
US4761655A (en) * 1984-11-30 1988-08-02 British Telecommunications Plc Transportable antenna for an earth station
US4780726A (en) * 1984-12-03 1988-10-25 Trw Inc. Depolyable reflector
US4845511A (en) * 1987-01-27 1989-07-04 Harris Corp. Space deployable domed solar concentrator with foldable panels and hinge therefor
US4862190A (en) * 1987-05-15 1989-08-29 Trw Inc. Deployable offset dish structure
US4989015A (en) * 1987-10-26 1991-01-29 Hughes Aircraft Company Unfurlable mesh reflector
US5642122A (en) * 1991-11-08 1997-06-24 Teledesic Corporation Spacecraft antennas and beam steering methods for satellite communciation system
US5864324A (en) * 1996-05-15 1999-01-26 Trw Inc. Telescoping deployable antenna reflector and method of deployment
US5898529A (en) * 1997-06-20 1999-04-27 Ball Aerospace & Technologies, Inc. Deployable space-based telescope
FR2778028A1 (en) * 1998-04-23 1999-10-29 Daimler Chrysler Ag REFLECTOR AND REFLECTOR ELEMENT FOR SPATIAL APPLICATION ANTENNAS AND A METHOD FOR DEPLOYING A REFLECTOR
US6191757B1 (en) * 1999-04-08 2001-02-20 Hughes Electronics Corporation System for compact stowage of segmented dish reflectors
WO2001022530A1 (en) * 1999-09-21 2001-03-29 The Johns Hokpins University Hybrid inflatable antenna
US6373449B1 (en) 1999-09-21 2002-04-16 The Johns Hopkins University Hybrid inflatable antenna
EP1168498A3 (en) * 2000-06-30 2002-09-18 Lockheed Martin Corporation Semi-rigid bendable reflecting structure
US6624796B1 (en) * 2000-06-30 2003-09-23 Lockheed Martin Corporation Semi-rigid bendable reflecting structure
US20090180204A1 (en) * 2005-09-05 2009-07-16 Thales Deployable reflector in the form of a reuleaux triangle for a space observation instrument
US7839567B2 (en) * 2005-09-05 2010-11-23 Thales Deployable reflector in the form of a reuleaux triangle for a space observation instrument
RU2447550C2 (en) * 2010-05-04 2012-04-10 Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнева" Umbrella antenna for spacecraft
RU2449437C1 (en) * 2010-10-04 2012-04-27 Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнева" Deployable large-size spacecraft reflector and method of its manufacturing
CN102005635A (en) * 2010-12-01 2011-04-06 宁波森富机电制造有限公司 Composite parabolic antenna with octagonal central loading slice structure
US9331394B2 (en) 2011-09-21 2016-05-03 Harris Corporation Reflector systems having stowable rigid panels
US10236590B1 (en) * 2016-12-21 2019-03-19 The United States Of America, As Represented By The Secretary Of The Air Force Foldable segmented structure and deployable reflector antenna comprised thereof
US10411363B2 (en) * 2017-05-15 2019-09-10 The Boeing Company Foldable dipole array antennas
US20190214737A1 (en) * 2018-01-08 2019-07-11 Umbra Lab, Inc. Articulated folding rib reflector for concentrating radiation
US10847893B2 (en) * 2018-01-08 2020-11-24 Umbra Lab, Inc. Articulated folding rib reflector for concentrating radiation
WO2020002938A1 (en) * 2018-06-28 2020-01-02 Oxford Space Systems Limited Deployable membrane structure for an antenna
CN112514161A (en) * 2018-06-28 2021-03-16 牛津空间系统有限公司 Deployable film structure for antenna
US11552406B2 (en) 2018-06-28 2023-01-10 Oxford Space Systems Limited Deployable membrane structure for an antenna
US11909114B2 (en) 2018-06-28 2024-02-20 Oxford Space Systems Limited Deployable membrane structure for an antenna
EP3654452A1 (en) * 2018-11-13 2020-05-20 Eagle Technology, LLC Mesh antenna reflector with deployable perimeter
EP4131656A1 (en) * 2018-11-13 2023-02-08 Eagle Technology, LLC Mesh antenna reflector with deployable perimeter

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