US3064534A - Reflector for space vehicle - Google Patents

Reflector for space vehicle Download PDF

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Publication number
US3064534A
US3064534A US21988A US2198860A US3064534A US 3064534 A US3064534 A US 3064534A US 21988 A US21988 A US 21988A US 2198860 A US2198860 A US 2198860A US 3064534 A US3064534 A US 3064534A
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United States
Prior art keywords
reflector
sectors
base plate
cam
shaft
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.)
Expired - Lifetime
Application number
US21988A
Inventor
Julius W Tumavicus
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Raytheon Technologies Corp
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United Aircraft Corp
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Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US21988A priority Critical patent/US3064534A/en
Priority to FR858531A priority patent/FR1286296A/en
Priority to GB13376/61A priority patent/GB920530A/en
Application granted granted Critical
Publication of US3064534A publication Critical patent/US3064534A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B5/00—Optical elements other than lenses
    • G02B5/08—Mirrors
    • G02B5/10—Mirrors with curved faces
    • 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
    • B64G1/2222—Folding
    • 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
    • B64G1/446—Thermal solar power generation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S23/00—Arrangements for concentrating solar-rays for solar heat collectors
    • F24S23/70—Arrangements for concentrating solar-rays for solar heat collectors with reflectors
    • F24S23/71—Arrangements for concentrating solar-rays for solar heat collectors with reflectors with parabolic reflective surfaces
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/40—Solar thermal energy, e.g. solar towers

Definitions

  • the present invention relates to a reflector device. More particularly it relates to a reflector device which can be retracted into a small package for transportation.
  • a reflector device is used.
  • a parabola has the distinguishing characteristic that it will reflect all parallel impinging signals to a common focal point and is probably the most desirable shape. Also, any signals originating at that point and impinging on the reflector will leave the reflector along parallel paths.
  • a boiler can be placed adjacent to the focal point of the parabola and the rays of the sun will be reflected from the parabolic surface to provide a concentrated heat source at the boiler.
  • the reflector In many situations it may be desired to transport the reflector from place to place. For instance, if the reflector is to be used in space vehicle applications it must be launched by suitable means to its desired location in space. Since the reflecting parabola is rather large and is difficult to transport thro-ugh the atmosphere in its operative condition, it is necessary to collapse the parabola during flight.
  • One feature of this invention is a construction whereby a reflector of revolution is divided into sectors which can be retracted into a small package for transportation and extended into operating position at its destination.
  • Another feature of this invention is a retractable parabolic reflector which has a true parabolic reflecting surface when the reflector is extended.
  • Another feature of this invention is a collapsible parabolic reflector in which the amount of reflection can be controlled by moving part of the reflector out of focus.
  • FIG. l is a perspective view of the reflector in its closed position.
  • FIG. 2 is a view showing the reflector in an intermediate position between open and closed.
  • FIG. 3 is a view showing the reflector in its extended position.
  • FIG. 4 is a sectional view of the extended reflector, including the actuating mechanism.
  • FIG. 5 is a view taken on line 5 5 of FIG. 4.
  • FIG. 6 is a plan view of an enlarged detail of the actuating cam.
  • FIG. 7 is a View taken on line 7 7 of FIG. 4.
  • FIG. 8 is a view of one of the reflector sectors.
  • FIG. 9 is a side view of one of the reflector sectors.
  • FIG. l0 shows a detail of the base on which the reflector sectors are mounted.
  • base plate 2 contains a plurality of holes 4 around its periphery. Each hole houses a shaft 6 which rotates in the hole. An arm or finger 8 extends from each shaft 6 and is fastened to the reflector sector 10 to support the sector. An arm 12 extends from each shaft 6 and a ball 14 is attached to each arm.
  • the 4balls 14 are positioned in the grooves 16 of a cam 18 as is best shown in FIG. 7.
  • Cam 18 is cylindrical and is composed of lands 20 and substantially radial grooves 16. As best shown in FIG. 5, a gear 24 is mounted on cam 18 and the cam is rotated by a motor 26 and a gear 28 in contact with gear 24.
  • Cam 18 is mounted on the centrally extending portion 30 of base plate 2 by bearings 32.
  • Motor 26 is mounted in a cavity in centrally extending portion 30 and gear 28 is mounted on a shaft 34 which extends through an opening 36 in centrally extending portion 30 and a slot 22 in the body of cam 18.
  • the centrally extending portion 38 of base plate 2 is threaded to a sleeve 38 and sleeve 38 is connected by a universal joint 40 to a plate 42 which is mounted directly on a vehicle.
  • holes 4 are inclined toward the axis of base plate 2, and are also angled with respect to the face 44 of base plate 2.
  • shafts 6 are mounted in holes 4 which act as bearings for the shafts and define the axis of rotation of reflector sectors 10.
  • FIGS. 2 and 3 show a boiler 46 connected to base plate 2 by the struts 48.
  • yStruts 48 are hollow and also serve as conduits for the flow of fluid to and from the boiler,
  • shaft 6 extends at a compound angle to finger 8. That is, it has an angle A in the plan view and an angle B in the side v1ew.
  • the sectors 10 which are of identical size and shape and are curved parabolically, are aligned across the face 44 of base plate 2 so that the sectors are axial along substantially radial lines of base plate 2 in the retracted position.
  • the distance between corresponding points on any two neighboring sectors is the same for all pairs of neighboring sectors.
  • the sectors form a sleeve or ring of Width varying according to the width of any one sector, and boiler 46 is located adjacent to the focal point of the parabola which is formed when the sectors are extended.
  • the closed reflectors can be encased for transportation in a container 50 of diameter substantially equal to the diameter of -base plate 2.
  • Motor 26 is energized by a signal from a suitable control mechanism and rotates cam 18 through gears 28 and 24. Clockwise rotation of cam 18 rotates shafts 6 in holes 4 through movement of ball cam followers 14 and arms 12. Reflector sectors 10 connected to shafts 6 move in identical paths inclined to face 44 of base plate 2. The paths are, of course, determined by the compound angle of shaft 6 and the inclination of shaft 6 to base plate 2. The sectors move outward from the axis of base plate 2 and downward toward base plate 2 until they form a parabolic surface of revolution as shown in FIGS. 3 and 4. The sectors can be retracted by reversing the rotation of cam 18.
  • the reflector When the reflector is in its extended position, the rays of the sun which impinge on the parabolic reflector surface parallel to the axis of the surface are reflected to the focal point of the parabola thereby heating boiler 46 which is positioned by struts 48 adjacent to the focal point of the parabola.
  • the axis of the parabola is made to coincide With the axis of base plate 2, and base plate 2 can be moved through universal joint 48 so that the reflecting surface will always be pointed directly at the sun.
  • FIGS. 6 and 7 parts 20a and 20b of adjoining lands 20 have been cut and made movable with respect to the remainder of cam 18. Raised portions 52 and 54 protruding from parts 20a and 2llb, respectively, ride in tracks 56 and 58.
  • the parts 20a and 2Gb are joined by a cut portion 60 of the base of groove 16, and are cut at an angle so that groove 16 becomes movable.
  • the lands are cut at an angle so that axial movement of the movable groove 16 will,
  • a reector sector 10 toward the closed position.
  • Four such movable grooves are provided spaced 90 apart. Each groove isindependently moved by actuating aA solenoid 62 which moves a rod 64 attached to the movable groove.
  • the solenoids are mounted on a plate 66 which is connected to the body of cam 18, and the rods extend throughV holes 68 in the cam body.
  • the solenoids are independently actuated by a suitable control mechanism to move one or more reflector sectors 10 toward the closed position to be out of focus. Movement of any one sector out of focus in this way will actually affect the amount of reection from two reflectors, because the sector being moved is no longerpart of the reecting parabola, and an adjacent sector is at least partially covered by this movement.
  • a collapsible reflector device comprising: a base having an axis and a face, and a plurality of openings disposed in a circle about said axis, said openings beingv inclined toward the axis of the base and angled with respect to the face of said base; a plurality of reector sectors; a plurality of compound angle shafts, each shaft connected with one of said reflector sectors and mounted forrot'ation in each of said openings, each compound angle shaft having a pair of arms, one arm extending outwardly from the openings and connected with a reflector sector; and means, connected with said other arm of each compound angle shaft, concurrently moving said reflector sectors.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Energy (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Sustainable Development (AREA)
  • Thermal Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Optics & Photonics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mounting And Adjusting Of Optical Elements (AREA)
  • Optical Elements Other Than Lenses (AREA)
  • Aerials With Secondary Devices (AREA)
  • Non-Portable Lighting Devices Or Systems Thereof (AREA)

Description

Nov. 20, 1962 J. w. TUMAvlcUs 3,064,534
REELECTOR FOR SPACE VEHICLE Filed April 15, 1960 s sheets-sheet 2 INVEN'T'OF JUl-IUS W- TLJMAVICUS Nov. 20, 1962 J. w. TuMAvlcUs 3,064,534
REFLECTOR FOR SPACE VEHICLE Filed April 13, 1960 3 Sheets-Sheet 5 F' IG- 4 iwf/f FIG-6 g INVENTOR .Jumus vv. 'ruMAvlcus www 54 52 BY ATTORNEY nited States "atet lice 3,064,534 REFLECTOR FOR SPACE VEHICLE Julius W. Tumavicus, Old Saybrook, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware Filed Apr. 13, 1960, Ser. No. 21,988 3 Claims. (Cl. 88-84) The present invention relates to a reflector device. More particularly it relates to a reflector device which can be retracted into a small package for transportation.
In many situations it is desirable to transmit signals, originating at a common point, along parallel paths. Conversely, it may also be desirable to collect signals traveling along parallel paths and concentrate them at a common point. In order to accomplish these aims a reflector device is used. A parabola has the distinguishing characteristic that it will reflect all parallel impinging signals to a common focal point and is probably the most desirable shape. Also, any signals originating at that point and impinging on the reflector will leave the reflector along parallel paths.
One situation in which such a device is applicable is a solar heater for space vehicles. A boiler can be placed adjacent to the focal point of the parabola and the rays of the sun will be reflected from the parabolic surface to provide a concentrated heat source at the boiler.
In many situations it may be desired to transport the reflector from place to place. For instance, if the reflector is to be used in space vehicle applications it must be launched by suitable means to its desired location in space. Since the reflecting parabola is rather large and is difficult to transport thro-ugh the atmosphere in its operative condition, it is necessary to collapse the parabola during flight.
One feature of this invention is a construction whereby a reflector of revolution is divided into sectors which can be retracted into a small package for transportation and extended into operating position at its destination.
Another feature of this invention is a retractable parabolic reflector which has a true parabolic reflecting surface when the reflector is extended.
Another feature of this invention is a collapsible parabolic reflector in which the amount of reflection can be controlled by moving part of the reflector out of focus.
Other features and advantages will be apparent from the specification and claims and from the accompanying drawings which illustrate an embodiment of the invention.
FIG. l is a perspective view of the reflector in its closed position.
FIG. 2 is a view showing the reflector in an intermediate position between open and closed.
FIG. 3 is a view showing the reflector in its extended position.
FIG. 4 is a sectional view of the extended reflector, including the actuating mechanism.
FIG. 5 is a view taken on line 5 5 of FIG. 4.
FIG. 6 is a plan view of an enlarged detail of the actuating cam.
FIG. 7 is a View taken on line 7 7 of FIG. 4.
FIG. 8 is a view of one of the reflector sectors.
FIG. 9 is a side view of one of the reflector sectors.
FIG. l0 shows a detail of the base on which the reflector sectors are mounted.
4Referring to FIGS. 4, 8 and 9, base plate 2 contains a plurality of holes 4 around its periphery. Each hole houses a shaft 6 which rotates in the hole. An arm or finger 8 extends from each shaft 6 and is fastened to the reflector sector 10 to support the sector. An arm 12 extends from each shaft 6 and a ball 14 is attached to each arm. The 4balls 14 are positioned in the grooves 16 of a cam 18 as is best shown in FIG. 7. Cam 18 is cylindrical and is composed of lands 20 and substantially radial grooves 16. As best shown in FIG. 5, a gear 24 is mounted on cam 18 and the cam is rotated by a motor 26 and a gear 28 in contact with gear 24. Cam 18 is mounted on the centrally extending portion 30 of base plate 2 by bearings 32. Motor 26 is mounted in a cavity in centrally extending portion 30 and gear 28 is mounted on a shaft 34 which extends through an opening 36 in centrally extending portion 30 and a slot 22 in the body of cam 18. The centrally extending portion 38 of base plate 2 is threaded to a sleeve 38 and sleeve 38 is connected by a universal joint 40 to a plate 42 which is mounted directly on a vehicle. As shown in' FIG. 10, holes 4 are inclined toward the axis of base plate 2, and are also angled with respect to the face 44 of base plate 2. As was stated above, shafts 6 are mounted in holes 4 which act as bearings for the shafts and define the axis of rotation of reflector sectors 10.
FIGS. 2 and 3 show a boiler 46 connected to base plate 2 by the struts 48. yStruts 48 are hollow and also serve as conduits for the flow of fluid to and from the boiler,
Referring to FIGS. 8 and 9, it can be seen that shaft 6 extends at a compound angle to finger 8. That is, it has an angle A in the plan view and an angle B in the side v1ew.
Referring to FIGS. l and 4, the sectors 10, which are of identical size and shape and are curved parabolically, are aligned across the face 44 of base plate 2 so that the sectors are axial along substantially radial lines of base plate 2 in the retracted position. The distance between corresponding points on any two neighboring sectors is the same for all pairs of neighboring sectors. The sectors form a sleeve or ring of Width varying according to the width of any one sector, and boiler 46 is located adjacent to the focal point of the parabola which is formed when the sectors are extended. The closed reflectors can be encased for transportation in a container 50 of diameter substantially equal to the diameter of -base plate 2.
Motor 26 is energized by a signal from a suitable control mechanism and rotates cam 18 through gears 28 and 24. Clockwise rotation of cam 18 rotates shafts 6 in holes 4 through movement of ball cam followers 14 and arms 12. Reflector sectors 10 connected to shafts 6 move in identical paths inclined to face 44 of base plate 2. The paths are, of course, determined by the compound angle of shaft 6 and the inclination of shaft 6 to base plate 2. The sectors move outward from the axis of base plate 2 and downward toward base plate 2 until they form a parabolic surface of revolution as shown in FIGS. 3 and 4. The sectors can be retracted by reversing the rotation of cam 18.
When the reflector is in its extended position, the rays of the sun which impinge on the parabolic reflector surface parallel to the axis of the surface are reflected to the focal point of the parabola thereby heating boiler 46 which is positioned by struts 48 adjacent to the focal point of the parabola. The axis of the parabola is made to coincide With the axis of base plate 2, and base plate 2 can be moved through universal joint 48 so that the reflecting surface will always be pointed directly at the sun.
A provision has been made for individual movement of several of the reflector sectors from the open position .toward the closed position. Referring to FIGS. 6 and 7 parts 20a and 20b of adjoining lands 20 have been cut and made movable with respect to the remainder of cam 18. Raised portions 52 and 54 protruding from parts 20a and 2llb, respectively, ride in tracks 56 and 58. The parts 20a and 2Gb are joined by a cut portion 60 of the base of groove 16, and are cut at an angle so that groove 16 becomes movable. The lands are cut at an angle so that axial movement of the movable groove 16 will,
through ball 14 and arm y12, rotate a reector sector 10 toward the closed position. Four such movable grooves are provided spaced 90 apart. Each groove isindependently moved by actuating aA solenoid 62 which moves a rod 64 attached to the movable groove. As seen in FIG. 4 the solenoids are mounted on a plate 66 which is connected to the body of cam 18, and the rods extend throughV holes 68 in the cam body. The solenoids are independently actuated by a suitable control mechanism to move one or more reflector sectors 10 toward the closed position to be out of focus. Movement of any one sector out of focus in this way will actually affect the amount of reection from two reflectors, because the sector being moved is no longerpart of the reecting parabola, and an adjacent sector is at least partially covered by this movement.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described but may be used in other Ways without departure from its spirit as defined by the following claims.
I claim:
1. A collapsible reflector device, comprising: a base having an axis and a face, and a plurality of openings disposed in a circle about said axis, said openings beingv inclined toward the axis of the base and angled with respect to the face of said base; a plurality of reector sectors; a plurality of compound angle shafts, each shaft connected with one of said reflector sectors and mounted forrot'ation in each of said openings, each compound angle shaft having a pair of arms, one arm extending outwardly from the openings and connected with a reflector sector; and means, connected with said other arm of each compound angle shaft, concurrently moving said reflector sectors.
`2. A collapsible reflector device as defined in claim 1, including means for selectively rotating some of said rellector sectors.
3. A collapsible reilector device as defined in claim 1, in which the compound angle of each shaft and the inclination of cach shaft to the base are such that said reector sectors move in identical paths inclined to the face of the base from an open position, forming a parabolic surface of revolution wherein saidf sectors are disposed in edge-to-edge relationship, to a retracted position wherein said sectors are disposed axially along substantially radial lines of the base, and vice versa.
References Cited in the le of this patent UNITED STATES PATENTS 669,185 See Mar. 5, 19011 707,982 Taylor Aug. 26, 1902 1,992,233 Norwood Feb. 26, 1935 2,182,222 Courtis et al Dec. 5, 1939 2,586,583 Wagner Feb. 19, 1952 2,806,134 Tarcici Sept. 10, 1957 2,945,234 Y` Driscoll Y= July 1.2, 1960
US21988A 1960-04-13 1960-04-13 Reflector for space vehicle Expired - Lifetime US3064534A (en)

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US21988A US3064534A (en) 1960-04-13 1960-04-13 Reflector for space vehicle
FR858531A FR1286296A (en) 1960-04-13 1961-04-12 Folding reflector device
GB13376/61A GB920530A (en) 1960-04-13 1961-04-13 Improvements relating to collapsible reflector devices

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US3109608A (en) * 1960-12-21 1963-11-05 Boehm Josef Vision skirt
US3174397A (en) * 1962-09-10 1965-03-23 Rayan Aeronautical Co Deployment mechanism for satellite mirror structure
US3176303A (en) * 1962-02-21 1965-03-30 Whittaker Corp Collapsible antenna with plurality of flexible reflector petals releasably retained
US3229579A (en) * 1961-12-27 1966-01-18 Aerojet General Co Solar energy collector
US3247840A (en) * 1963-06-07 1966-04-26 Bendix Corp Solar energy collector means
US3258598A (en) * 1966-06-28 Center of pressure for absorber
US3286259A (en) * 1964-04-30 1966-11-15 Goodyear Aerospace Corp Unfurlable reflector
US3337871A (en) * 1965-03-22 1967-08-22 Telar Associates Inc Space reflector device
US3496941A (en) * 1966-11-14 1970-02-24 David Clough Ketner Sun-bathers reflector device
US3513822A (en) * 1969-09-10 1970-05-26 Otto Korngold Space heaters
US3540048A (en) * 1966-10-19 1970-11-10 Nasa Deep space-monitor communication satellite system
US3541569A (en) * 1968-03-08 1970-11-17 Trw Inc Expandable parabolic reflector
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US4422446A (en) * 1979-08-07 1983-12-27 Strickland Benjamin W Solar furnace apparatus
US4627418A (en) * 1980-09-08 1986-12-09 Geruldine Gibson Apparatus for the carbothermic reduction of metal oxides using solar energy
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US4862190A (en) * 1987-05-15 1989-08-29 Trw Inc. Deployable offset dish structure
US4947825A (en) * 1989-09-11 1990-08-14 Rockwell International Corporation Solar concentrator - radiator assembly
US5345238A (en) * 1990-03-13 1994-09-06 Teledyne Industries, Inc. Satellite signature suppression shield
US5898529A (en) * 1997-06-20 1999-04-27 Ball Aerospace & Technologies, Inc. Deployable space-based telescope
EP1386838A1 (en) * 2002-07-31 2004-02-04 Astrium GmbH Deployable antenna reflector
US20040233554A1 (en) * 2000-12-25 2004-11-25 Mikio Kinoshita Solar radiation condensing device
US7557995B1 (en) 2006-07-11 2009-07-07 Itt Manufacturing Enterprises, Inc. Deployable telescope shade
US20110108019A1 (en) * 2008-08-18 2011-05-12 Pratt & Whitney Rocketdyne., Inc. Heliostat joint
US20120146873A1 (en) * 2010-12-14 2012-06-14 Murphey Thomas W Deployable Shell With Wrapped Gores
CN104953229A (en) * 2014-12-25 2015-09-30 黄天生 Retractable satellite receiving pot
CN105539880A (en) * 2016-01-13 2016-05-04 广西大学 Large-area unfoldable solar energy turnover plate
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US10153559B1 (en) * 2016-06-23 2018-12-11 Harris Corporation Modular center fed reflector antenna system
US10797400B1 (en) 2019-03-14 2020-10-06 Eagle Technology, Llc High compaction ratio reflector antenna with offset optics
US10811759B2 (en) 2018-11-13 2020-10-20 Eagle Technology, Llc Mesh antenna reflector with deployable perimeter
US11139549B2 (en) 2019-01-16 2021-10-05 Eagle Technology, Llc Compact storable extendible member reflector

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US9331394B2 (en) * 2011-09-21 2016-05-03 Harris Corporation Reflector systems having stowable rigid panels
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US20040104861A1 (en) * 2002-07-31 2004-06-03 Manfred Schmid Deployable antenna reflector
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US7557995B1 (en) 2006-07-11 2009-07-07 Itt Manufacturing Enterprises, Inc. Deployable telescope shade
US20110108019A1 (en) * 2008-08-18 2011-05-12 Pratt & Whitney Rocketdyne., Inc. Heliostat joint
US20120146873A1 (en) * 2010-12-14 2012-06-14 Murphey Thomas W Deployable Shell With Wrapped Gores
US8462078B2 (en) * 2010-12-14 2013-06-11 The United States Of America As Represented By The Secretary Of The Air Force Deployable shell with wrapped gores
CN104953229A (en) * 2014-12-25 2015-09-30 黄天生 Retractable satellite receiving pot
CN104953229B (en) * 2014-12-25 2018-06-08 黄天生 A kind of telescopic satellite reception ancient cooking vessel
CN105539880A (en) * 2016-01-13 2016-05-04 广西大学 Large-area unfoldable solar energy turnover plate
US10153559B1 (en) * 2016-06-23 2018-12-11 Harris Corporation Modular center fed reflector antenna system
DE102016012402A1 (en) * 2016-10-17 2018-04-19 Stefan Alfred Maier Device (45) arranged as a precision mirror / parabolic mirror of segment parts and a method that the mirror segments set in motion to the total mirror surface differently structured to take in the rest position, wind forces the attack surface.
US10811759B2 (en) 2018-11-13 2020-10-20 Eagle Technology, Llc Mesh antenna reflector with deployable perimeter
US11139549B2 (en) 2019-01-16 2021-10-05 Eagle Technology, Llc Compact storable extendible member reflector
US11862840B2 (en) 2019-01-16 2024-01-02 Eagle Technologies, Llc Compact storable extendible member reflector
US10797400B1 (en) 2019-03-14 2020-10-06 Eagle Technology, Llc High compaction ratio reflector antenna with offset optics

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