US2805974A - Method of making radar reflector - Google Patents
Method of making radar reflector Download PDFInfo
- Publication number
- US2805974A US2805974A US540796A US54079655A US2805974A US 2805974 A US2805974 A US 2805974A US 540796 A US540796 A US 540796A US 54079655 A US54079655 A US 54079655A US 2805974 A US2805974 A US 2805974A
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- impregnating
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- fiberglass
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- 238000004519 manufacturing process Methods 0.000 title claims description 13
- 229920005989 resin Polymers 0.000 claims description 40
- 239000011347 resin Substances 0.000 claims description 40
- 239000011152 fibreglass Substances 0.000 claims description 34
- 229910052751 metal Inorganic materials 0.000 claims description 31
- 239000002184 metal Substances 0.000 claims description 31
- 239000004744 fabric Substances 0.000 claims description 26
- 239000000463 material Substances 0.000 claims description 10
- 230000001413 cellular effect Effects 0.000 claims description 6
- 238000005488 sandblasting Methods 0.000 claims description 6
- 238000005507 spraying Methods 0.000 claims description 6
- 238000009966 trimming Methods 0.000 claims description 4
- 229920001187 thermosetting polymer Polymers 0.000 claims description 3
- 239000012260 resinous material Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 description 12
- 239000004033 plastic Substances 0.000 description 7
- 229920003023 plastic Polymers 0.000 description 7
- 238000010276 construction Methods 0.000 description 5
- 229910000831 Steel Inorganic materials 0.000 description 3
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- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- MTHSVFCYNBDYFN-UHFFFAOYSA-N diethylene glycol Chemical compound OCCOCCO MTHSVFCYNBDYFN-UHFFFAOYSA-N 0.000 description 3
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- 229920000180 alkyd Polymers 0.000 description 2
- -1 e. g. Polymers 0.000 description 2
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- NDKWCCLKSWNDBG-UHFFFAOYSA-N zinc;dioxido(dioxo)chromium Chemical compound [Zn+2].[O-][Cr]([O-])(=O)=O NDKWCCLKSWNDBG-UHFFFAOYSA-N 0.000 description 2
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- FPYJFEHAWHCUMM-UHFFFAOYSA-N maleic anhydride Chemical compound O=C1OC(=O)C=C1 FPYJFEHAWHCUMM-UHFFFAOYSA-N 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000009972 noncorrosive effect Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- XNGIFLGASWRNHJ-UHFFFAOYSA-L phthalate(2-) Chemical compound [O-]C(=O)C1=CC=CC=C1C([O-])=O XNGIFLGASWRNHJ-UHFFFAOYSA-L 0.000 description 1
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
- B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D24/00—Producing articles with hollow walls
- B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
- B29D24/005—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled the structure having joined ribs, e.g. honeycomb
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/03—Details of HF subsystems specially adapted therefor, e.g. common to transmitter and receiver
-
- 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
- H01Q15/141—Apparatus or processes specially adapted for manufacturing reflecting surfaces
- H01Q15/142—Apparatus or processes specially adapted for manufacturing reflecting surfaces using insulating material for supporting the reflecting surface
- H01Q15/144—Apparatus or processes specially adapted for manufacturing reflecting surfaces using insulating material for supporting the reflecting surface with a honeycomb, cellular or foamed sandwich structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
- B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
- B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/34—Electrical apparatus, e.g. sparking plugs or parts thereof
- B29L2031/3456—Antennas, e.g. radomes
-
- 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
- Y10S138/00—Pipes and tubular conduits
- Y10S138/10—Metal foil
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
- Y10T156/1003—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by separating laminae between spaced secured areas [e.g., honeycomb expanding]
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
- Y10T156/1028—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith
- Y10T156/103—Encasing or enveloping the configured lamina
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49002—Electrical device making
- Y10T29/49016—Antenna or wave energy "plumbing" making
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]
- Y10T428/131—Glass, ceramic, or sintered, fused, fired, or calcined metal oxide or metal carbide containing [e.g., porcelain, brick, cement, etc.]
- Y10T428/1314—Contains fabric, fiber particle, or filament made of glass, ceramic, or sintered, fused, fired, or calcined metal oxide, or metal carbide or other inorganic compound [e.g., fiber glass, mineral fiber, sand, etc.]
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24149—Honeycomb-like
Definitions
- This invention relates to a method for constructing a radar reflector. More particularly, it relates to a method of making a radar reflector of new and improved light weight and rigidity containing a minimum of metal while obtaining all the advantages normally attributed to allmetal reflectors. It likewise relates to an improved method of making the desired reflector, largely of plastic and fibrous materials.
- Yet another object of the invention is the provision of a. method of making a new and improved plastic construction for radar reflectors incorporating metal as the electronically eflective ingredient, and the plastic as a durable, weather-resistant and non-corrosive structural foundation.
- Yet another object of the invention is to provide a method of making a plastic radar reflector construction capable of satisfying the rigid standards of the Armed Forces of the United States, as well as commercial requirements, and Whose utility is susbtantially unaffected by increases in size, said increase being accompanied by disproportionate increases in weight, foundation, and reinforcement.
- Yet another object of the invention is the provision of a new and improved method for insuring suflicient I'lgld-' ity of the metal reflector portion of the device of the 1n-- stant invention.
- Figure l is a perspective view, partially in section, of a mold and radar reflector constructed thereon in accordance with the teaching of this invention.
- FIG. 2 is a flow diagram of the method of this invention.
- Figure 3 is a fragmentary sectional view of one edge of a finished reflector made by the method of this invention.
- a mold is of plastic or the like, having a base 11 by which the same is supported in any suitable fashion, as upon a floor, and provided with any reinforcing rim, as of wood or steel, 12.
- the upper surface 13 of the mold is convex to conform to the desired reflective shape of the intended reflector surface.
- the mold is further preferably provided with an annular flange portion 14 for a purpose to be described.
- a layer of fiberglass cloth 15, thoroughly impregnated with a resin is closely laid over the upper surface of the convex portion 13 of the mold, and also to the upper surface 16 of the flange 14 thereof.
- the resin is preferably also applied, prior to the application of the impregnated fiberglass sheet 15, to the mold surfaces 13 and 16, as by means of a brush, a spatula, by spraying, or by hand.
- Said resin is most desirably an unsaturated polyester selected from any of those commercially available products more specifically, styrene copolymers of unsaturated alkyd resins, e. g., alkyd made from diethylene glycol with maleic anhydride and phthalate, soluble in styrene, or from diallyl phthalate.
- unsaturated alkyd resins e. g., alkyd made from diethylene glycol with maleic anhydride and phthalate, soluble in styrene, or from diallyl phthalate.
- the purpose of the first layer of cloth 15 is to provide a weather-proof coating for the reflective side of the reflector, to protect the metal coating 17 from oil and corrosion, and to provide a body which is conveniently and easily removed from the mold upon completion of the product.
- a fiberglass woven mat of approximately ten thousandt'ns of an inch thickness is used.
- the initial layer of fiberglass 15, together with the resin impregnated therein and thereunder, is next cured as under an ultraviolet lamp, which assists the activity of the lightactivated catalysts, if any, which may be incorporated in the resin, within the skill of those familiar with the art, or such curing may be accomplished in any conventional fashion, as in an oven for approximately an hour, at approximately 200 degrees Fahrenheit, or other satisfactory temperature.
- an ultraviolet lamp which assists the activity of the lightactivated catalysts, if any, which may be incorporated in the resin, within the skill of those familiar with the art, or such curing may be accomplished in any conventional fashion, as in an oven for approximately an hour, at approximately 200 degrees Fahrenheit, or other satisfactory temperature.
- the exposed upper surface of the fiberglass mat is subjected to a sandblasting.
- sandblasting provides a satisfactory surface for the; next operation, which is the application, by means ofa, metal spray, of alayer of metal of substantially uniform thickness over the entire convex surface of the mold and cloth layer 15.
- Alayer of aluminum has been found satisfactory forthe instant purposes if deposited, for example, in a layer pf approxi mately ten thousandths of an inch.
- Other metals may also be employed, but if so, they should be selected from those which. do not require such a high temperature for spraying that the resultant heat of the sprayed metal willdeleteriously or otherwise afiectthe resin.
- a layer of said resin over which is similarly laid a fiberglass mat 18, preferably of woven fiberglass.
- Said layer 18 has been found satisfactory if comprised of three layers of such fiberglass fabric of about thirty thousandths of an inch combined thickness. Also satisfactory is a single fiberglass mat of woven fiberglass fibers of approximately the same total thickness.
- honeycomb core 19 Over the last named layer 18 is placed a preferably honeycomb core 19. If it be assumed in the instant example that the diameter of the reflecter is to be approximately eight to nine feet, a honeycomb core of approximately one and three-quarter inches in thickness has been found suitable.
- the honeycomb itself comprises woven fiberglass impregnated with a polyester resin.
- the individual cells of the core by way of example, may be hexagonal and extend continuously from the inside to the outside walls of the core.
- the walls of the core defining the honeycomb-like chambers are approximately three thousandths of an inch in thickness and are impregnated with said resin to give them a total thickness, including said resin, of about five thousandths of an inch.
- a further backing 20 of woven fiberglass fabric impregnated with said resin is laid over the .core 19.
- Such a backing has been found satisfactory. in the form of approximately four layers or plies of woven fiberglass, each of which ply has an approximate thickness of ten thousandths of an inch, the whole backing 20 thereby having. an over-all thickness of approximately forty thousandths of an inch.
- the upper surface of the mold is covered with a flexible bag 21 of any material such as polyvinyl acetate, or the like, non-compatible material which 'does not, like rubber, inhibit curing of the resin,
- Said bag 21 is laid also over the upper surface of the corresponding layers 16 through 29 disposed upon the flange 14, and if desired, also over'the outermost edge 22 of the flange 12, but prior to the positioning of the bag 21, a porous or otherwise open tube 23 is coiled about the mold.
- Such tube 23 may take the form merely of a coil spring or other coil of material comprising a helix.
- a layer of sealing compound such as zinc chromate, is employed, having the desired quality that it does not flow under the contemplated heat to which the mold is to be subjected.
- the bag 21 is pressed into position over the zinc chromate seal, which seal, however, is not deposited inwardly, as at 26, between the tube 23 and the convex portion 13 of the mold.
- a vacuum is next interconnected with the tube 23.
- the vacuum heretofore employed has been that required to subjectth'e dome 27, or convexity, to a pressure of approximately nine pounds per square inch; While the vacuum is applied, any air under the dome portion 27 is rubbed out as by brushing, rubbing, rolling or the like,
- the cured part is removed from the mold by physical stripping after the bag 21 has been removed.
- the edges designated collectively at 28 overlying the flange 14 are trimmed off, and the raw edges 29 thus exposed are capped as by two layers 3.0.31 of woven fiberglass mat, each having a thickness of approximately ten thousandths of an inch, impregnated with said resin, as under a heat lamp, to approximately 200 degrees Fahrenheit, for approximately an hour.
- the over-all thickness which may be substantially the.
- the reflector may be made in any diameter, as for example, from two inches to fifty or even feet in diameter.
- the curve of the reflector surface is preferably parabolic.
- the weight of a corresponding steel frame of effective nine-foot diameter is approximately 350 pounds; whereas, the corresponding weight of an effective nine-foot reflector made in accordance with this invention is only. ninety pounds. Even the cost of the instant reflector is substantially less than that of its steel counterpart.
- a reflector made in accordance with the teaching of this invention has, under test, withstood a mile-per-hour gale directed axially at same, or while rotating the same, with less than one-eighth of an inch deflection while mounted on a standard support.
- a radar reflector comprising forming and retaining a layer of resinous material in a generally dish-shaped condition, curing said resin, sandblasting the outer' curved surface of said resin, spraying a metal uniformly over the sandblasted surface, permitting said metal to' harden on said surface, impregnating the" surface of said sprayed layer of metal with such thermosetting resin, impregnating a fiberglass cloth with said resin and applying the impregnated cloth to said impregnated sprayed metal surface, applying a cellular substantially rigid member on the outer surface of the impreg-.
- nated fiberglass cloth layer impregnating a second fiberglass cloth with said resin and applying said cloth over said cellular member, removing entrapped air and pressing.
- thermo-setting resin is an unsaturated polyester.
- a radar reflector of the character described comprising forming a dome-shaped mold, positioning said mold with said dome shape uppermost upon a solid foundation, forming an annular flange around said dome at the base thereof, impregnating with a thermosetting resin and applying over said dome a layer of fiberglass cloth, curing said thermo-setting resin in and upon said cloth, sandblasting the upper cured surface of said resin, spraying a substantially uniform layer of aluminumlike metal over said sandblasted surface, impregnating with a thermo-setting resin and laying thereover a second fiberglass cloth, laying over said second fiberglass cloth a rigid material to a substantial thickness, impregnating with a thermo-setting resin and laying thereover a third fiberglass cloth, laying thereover an impervious flexible sheet, providing a vacuum under said last sheet substantially entirely around said dome at said flange, and wiping said dome downwardly toward said flange and vacuum while curing the resin, removing the cured reflector from the mold and trimming and finishing the edges thereof.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Manufacturing & Machinery (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Aerials With Secondary Devices (AREA)
- Laminated Bodies (AREA)
Description
p 1957 M. BRUCKER 2,805,974
METHOD OF MAKING RADAR REFLECTOR Original Filed June 20, 1952 @020 PLASTEI? MOLD APPLY s/mv METAL f'F/BPE GLASS CURE SAND BLAST COAT/N6 540x w/n/ saw/.0 UP APPLY A Z; A P '-;:g FIBRE GLASS BACK/N6 0F SHEETS 0F SHEETS HONEYCOMB FIBRE GLASS M/LTON BRUCKER,
INVENTOR.
United States at 2,805,974 METHOD F MAKENG RADAR REFTECTGR Milton Brucker, Los Angeles, Calif., assignor, by mesne assignments, to Zenith Plastics Company, Gardena, Califi, a corporation of Delaware 5 Claims. (Cl. 154-411)) This invention relates to a method for constructing a radar reflector. More particularly, it relates to a method of making a radar reflector of new and improved light weight and rigidity containing a minimum of metal while obtaining all the advantages normally attributed to allmetal reflectors. It likewise relates to an improved method of making the desired reflector, largely of plastic and fibrous materials.
' This application is a division of my earlier application Serial Number 294,632 filed on June 20, 1952 now U. S. Patent No. 2,747,180.
Heretofore commercially acceptable radar reflectors, for use in particular by the Armed Forces of the United States for aircraft, seagoing, and land use, depended upon use of an all-metal concavity, or the like, all-metal shield, either cast integrally as a reflective unit, or made reticulate by metal bars, rods, mesh, and the like. Such prior art devices are relatively heavy in weight, costly in their manufacture and maintenance, and include the use of metal predominantly if not exclusively. Inasmuch as the larger radar reflectors are most effective in use, the weight-size relationship becomes critical, particularly for aircraft use. It is also important, to a somewhat lesser extent however, on ocean-going vessels, and even on land.
In view of the above considerations and others, it is among the objects of this invention to provide a method of making, from readily available plastic and fibrous materials, a satisfactory and commercially acceptable radar reflector utilizing a minimum of metal but without thereby diminishing either the utility or durability of a radar reflector of comparable size made in accordance with prior art teachings.
It is another object of this invention to provide, in a radar reflector of the desired character described, a weather-resistant, non-metallic surface, a relatively fine layer of reflective metal, and a relatively still and substantial highly reticulate backing of utmost lightness consistent with strength and durability, and in a manner corresponding to the first mentioned non-metallic surface which is closely adherent to and provides a strong backing and protection to the reflective metal layer.
Yet another object of the invention is the provision of a. method of making a new and improved plastic construction for radar reflectors incorporating metal as the electronically eflective ingredient, and the plastic as a durable, weather-resistant and non-corrosive structural foundation.
Yet another object of the invention is to provide a method of making a plastic radar reflector construction capable of satisfying the rigid standards of the Armed Forces of the United States, as well as commercial requirements, and Whose utility is susbtantially unaffected by increases in size, said increase being accompanied by disproportionate increases in weight, foundation, and reinforcement.
It is among the objects of this invention to provide a new and improved method of making a radar reflector as herein described and claimed.
2,805,974 Patented Sept. 10, 1957 Yet another object of the invention is the provision of a new and improved method for insuring suflicient I'lgld-' ity of the metal reflector portion of the device of the 1n-- stant invention. I
It is moreover an object to provide an improved method for insuring permanent adherence of the several metal and non-metal parts of the desired structure to one another.
It is a further object of the invention to provide new and improved means and molding method for obtaining a radar reflector of the instant invention.
In addition, it is among the objects of this specification and invention to set forth a suggested, preferred means and method for obtaining a new and improved radar reflector construction in accordance with the inventors conception; to improve prior art devices and methods heretofore intended to accomplish generally similar purposes.
These and other objects and purposes will be more fully understood by reference to the accompanying specification considered in the light of the drawings and the appended claims.
In the drawings:
Figure l is a perspective view, partially in section, of a mold and radar reflector constructed thereon in accordance with the teaching of this invention.
Figure 2 is a flow diagram of the method of this invention.
Figure 3 is a fragmentary sectional view of one edge of a finished reflector made by the method of this invention.
Referring more particularly to the drawings, there is illustrated by way of example but not of limitation a mold is of plastic or the like, having a base 11 by which the same is supported in any suitable fashion, as upon a floor, and provided with any reinforcing rim, as of wood or steel, 12. The upper surface 13 of the mold is convex to conform to the desired reflective shape of the intended reflector surface. The mold is further preferably provided with an annular flange portion 14 for a purpose to be described.
In the construction of the instant reflector, a layer of fiberglass cloth 15, thoroughly impregnated with a resin, is closely laid over the upper surface of the convex portion 13 of the mold, and also to the upper surface 16 of the flange 14 thereof. The resin is preferably also applied, prior to the application of the impregnated fiberglass sheet 15, to the mold surfaces 13 and 16, as by means of a brush, a spatula, by spraying, or by hand.
Said resin is most desirably an unsaturated polyester selected from any of those commercially available products more specifically, styrene copolymers of unsaturated alkyd resins, e. g., alkyd made from diethylene glycol with maleic anhydride and phthalate, soluble in styrene, or from diallyl phthalate.
The purpose of the first layer of cloth 15 is to provide a weather-proof coating for the reflective side of the reflector, to protect the metal coating 17 from oil and corrosion, and to provide a body which is conveniently and easily removed from the mold upon completion of the product. For such purpose a fiberglass woven mat of approximately ten thousandt'ns of an inch thickness is used.
The initial layer of fiberglass 15, together with the resin impregnated therein and thereunder, is next cured as under an ultraviolet lamp, which assists the activity of the lightactivated catalysts, if any, which may be incorporated in the resin, within the skill of those familiar with the art, or such curing may be accomplished in any conventional fashion, as in an oven for approximately an hour, at approximately 200 degrees Fahrenheit, or other satisfactory temperature. I 1
After the curing of the fiberglass impregnated resin, the exposed upper surface of the fiberglass mat is subjected to a sandblasting. Such sandblasting provides a satisfactory surface for the; next operation, which is the application, by means ofa, metal spray, of alayer of metal of substantially uniform thickness over the entire convex surface of the mold and cloth layer 15. Alayer of aluminum has been found satisfactory forthe instant purposes if deposited, for example, in a layer pf approxi mately ten thousandths of an inch. Other metals may also be employed, but if so, they should be selected from those which. do not require such a high temperature for spraying that the resultant heat of the sprayed metal willdeleteriously or otherwise afiectthe resin.
To the upper surface of the metal layer 17 there is applied, with or without sandblasting, and preferably also but not necessarily, a coating as by brush, spatula, by spray or by hand, a layer of said resin, over which is similarly laid a fiberglass mat 18, preferably of woven fiberglass. Said layer 18 has been found satisfactory if comprised of three layers of such fiberglass fabric of about thirty thousandths of an inch combined thickness. Also satisfactory is a single fiberglass mat of woven fiberglass fibers of approximately the same total thickness.
Over the last named layer 18 is placed a preferably honeycomb core 19. If it be assumed in the instant example that the diameter of the reflecter is to be approximately eight to nine feet, a honeycomb core of approximately one and three-quarter inches in thickness has been found suitable. The honeycomb itself comprises woven fiberglass impregnated with a polyester resin. The individual cells of the core, by way of example, may be hexagonal and extend continuously from the inside to the outside walls of the core. The walls of the core defining the honeycomb-like chambers are approximately three thousandths of an inch in thickness and are impregnated with said resin to give them a total thickness, including said resin, of about five thousandths of an inch.
After the honeycomb has been positioned over the layer 18, preferably though not necessarily as a continuous unit, a further backing 20 of woven fiberglass fabric impregnated with said resin is laid over the .core 19. Such a backing has been found satisfactory. in the form of approximately four layers or plies of woven fiberglass, each of which ply has an approximate thickness of ten thousandths of an inch, the whole backing 20 thereby having. an over-all thickness of approximately forty thousandths of an inch.
After the positioning of the layers 18, 19, and 20, over the sprayed metal layer 17, the upper surface of the mold is covered with a flexible bag 21 of any material such as polyvinyl acetate, or the like, non-compatible material which 'does not, like rubber, inhibit curing of the resin,
and which does not, after such curing, adhere to the resin.
Said bag 21 is laid also over the upper surface of the corresponding layers 16 through 29 disposed upon the flange 14, and if desired, also over'the outermost edge 22 of the flange 12, but prior to the positioning of the bag 21, a porous or otherwise open tube 23 is coiled about the mold. Such tube 23 may take the form merely of a coil spring or other coil of material comprising a helix. Moreover, at the outer edges of the flange, as at 24 and 25, a layer of sealing compound, such as zinc chromate, is employed, having the desired quality that it does not flow under the contemplated heat to which the mold is to be subjected.
The bag 21 is pressed into position over the zinc chromate seal, which seal, however, is not deposited inwardly, as at 26, between the tube 23 and the convex portion 13 of the mold.
A vacuum is next interconnected with the tube 23. The vacuum heretofore employed has been that required to subjectth'e dome 27, or convexity, to a pressure of approximately nine pounds per square inch; While the vacuum is applied, any air under the dome portion 27 is rubbed out as by brushing, rubbing, rolling or the like,
with pressure against the top of the dome, beginning in an oven, under ultra-violet light, or otherwise.
Thereupon the cured part is removed from the mold by physical stripping after the bag 21 has been removed. The edges designated collectively at 28 overlying the flange 14 are trimmed off, and the raw edges 29 thus exposed are capped as by two layers 3.0.31 of woven fiberglass mat, each having a thickness of approximately ten thousandths of an inch, impregnated with said resin, as under a heat lamp, to approximately 200 degrees Fahrenheit, for approximately an hour.
A reflector made as above described, by Way of ex:
ample, may have a diameter ,of approximately nine. feet.
The over-all thickness, which may be substantially the.
same from edge to edge, isaPPIOXimateIy 1.84 inches, not counting the added thickness of the cap 30-131.
The versatility of the instant. construction is such that a.
reflector may be made in any diameter, as for example, from two inches to fifty or even feet in diameter. The curve of the reflector surface is preferably parabolic. The weight of a corresponding steel frame of effective nine-foot diameter is approximately 350 pounds; whereas, the corresponding weight of an effective nine-foot reflector made in accordance with this invention is only. ninety pounds. Even the cost of the instant reflector is substantially less than that of its steel counterpart.
A reflector made in accordance with the teaching of this invention has, under test, withstood a mile-per-hour gale directed axially at same, or while rotating the same, with less than one-eighth of an inch deflection while mounted on a standard support. Y
It has excellent Weather-resistant qualities and may 'be used either exposed or under the protection of a radome or like shelter, in aircraft, aboard ship, or as part of a stationary or mobile land unit.
Although I have herein shown and described my in vention in what I have conceived to be the most practical and preferred embodiment, it is recognized that departures may be made therefrom within the scope of my invention, which is not to'be limited to the details dis: closed herein but is to be accorded the full scope of the claims so. as to embrace any and all equivalent structures and methods. e
' I claim:
1. The method of making a radar reflector comprising forming and retaining a layer of resinous material in a generally dish-shaped condition, curing said resin, sandblasting the outer' curved surface of said resin, spraying a metal uniformly over the sandblasted surface, permitting said metal to' harden on said surface, impregnating the" surface of said sprayed layer of metal with such thermosetting resin, impregnating a fiberglass cloth with said resin and applying the impregnated cloth to said impregnated sprayed metal surface, applying a cellular substantially rigid member on the outer surface of the impreg-.
nated fiberglass cloth layer, impregnating a second fiberglass cloth with said resin and applying said cloth over said cellular member, removing entrapped air and pressing.
all of said layers radially together and curing said resin in and between said layers, trimming the marginal edge:
of the resultant cured mass, impregnating a fiberglass material with a thermo-setting resin and applying said ma terial over said trimmed edge, and curing said last men-- tioned resin in place. 7 a
2. The method of making a radar reflector comprising forming and retaining a layer of woven fiberglass cloth in a generally dish-shaped condition, impregnating said cloth t a t me-s t e in e l psoid tesi is a i the outer curved surface of said resin-impregnatedcloth,
spraying a metal uniformly over the sandblasted surface, permitting said metal to harden on said surface, impregnating the surface of said sprayed layer of metal with such thermo-setting resin, impregnating a second fiberglass cloth with said resin and applying said impregnated second cloth to said impregnated sprayed metal surface, applying a cellular substantially rigid member on the outer surface of said second impregnated fiberglass cloth layer, impregnating a third fiberglass cloth with said resin and applying said cloth over said cellular member, removing entrapped air and pressing all of said layers radially together andcuring said resin in and between said layers, trimming the marginal edge of the resultant cured mass, impregnating a fiberglass material with a thcrmo-setting resin and applying said material over said trimmed edge, and curing said last mentioned resin in place.
3. The method of claim 2, wherein said thermo-setting resin is an unsaturated polyester.
4. The method of claim 2, including the additional steps of covering the foregoing layers with a flexible impervious layer of material non-compatible with said resin, and removing said air under vacuum around the circumferential periphery of said dish-shaped structure while pressing out any such entrapped air and residual resin in the direction of said circumferential periphery and said vacuum.
5. The method of making a radar reflector of the character described comprising forming a dome-shaped mold, positioning said mold with said dome shape uppermost upon a solid foundation, forming an annular flange around said dome at the base thereof, impregnating with a thermosetting resin and applying over said dome a layer of fiberglass cloth, curing said thermo-setting resin in and upon said cloth, sandblasting the upper cured surface of said resin, spraying a substantially uniform layer of aluminumlike metal over said sandblasted surface, impregnating with a thermo-setting resin and laying thereover a second fiberglass cloth, laying over said second fiberglass cloth a rigid material to a substantial thickness, impregnating with a thermo-setting resin and laying thereover a third fiberglass cloth, laying thereover an impervious flexible sheet, providing a vacuum under said last sheet substantially entirely around said dome at said flange, and wiping said dome downwardly toward said flange and vacuum while curing the resin, removing the cured reflector from the mold and trimming and finishing the edges thereof.
References Cited in the file of this patent UNITED STATES PATENTS 2,439,137 Keller Apr. 6, 1948 2,478,165 Collins Aug. 2, 1949 2,638,428 Gordon et al. May 12, 1953 2,706,832 Frost et al Apr. 26, 1955 FOREIGN PATENTS 365,755 Great Britain Jan. 28, 1932
Claims (1)
1. THE METHOD OF MAKING A RADAR REFLECTOR COMPRISING FORMING AND RETAINING A LAYER OF RESINOUS MATERIAL IN A GENERALLY DISH-SHAPED CONDIDTION, CURING SAID RESIN, SANDBLASTING THE OUTER CURVED SURFACE OF SAID RESIN, SPRAYING A METAL UNIFORMLY OVER THE SANDBLASTED SURFACE, PERMITTING SAID METAL TO HARDEN ON SAID SURFACE, IMPREGNATING THE SURFACE OF SAID SPRAYED LAYER OF METAL WITH SUCH THERMOSETTING RESIN, IMPREGNATING A FIBERGLASS CLOTH WITH SAID RESIN AND APPLYING THE IMPREGNATED CLOTH TO SAID IMPREGNATED SPRAYED METAL SURFACE, APPLYING A CELLULAR SUBSTANTIALLY RIGID MEMBER ON THE OUTER SURFACE OF THE IMPREGNATED FIBERGLASS CLOTH LAYER, IMPREGNATING A SECOND FIBERGLASS CLOTH WITH SAID RESIN AND APPLYING SAID CLOTH OVER SAID CELLULAR MEMBER, REMOVING ENTRAPPED AIR AND PRESSING ALL OF SAID LAYERS RADIALLY TOGETHER AND CURING SAID RESIN IN AND BETWEEN SAID LAYERS, TRIMMING THE MARGINAL EDGE OF THE RESULTANT CURED MASS, IMPREGNATING A FIBERGLASS MATERIAL WITH A THERMO-SETTING RESIN AND APPLYING SAID MATERIAL OVER SAID TRIMMED EDGE, AND CURING SAID LAST MENTIONED RESIN IN PLACE.
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US540796A US2805974A (en) | 1952-06-20 | 1955-10-17 | Method of making radar reflector |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US294632A US2747180A (en) | 1952-06-20 | 1952-06-20 | Radar reflector |
US540796A US2805974A (en) | 1952-06-20 | 1955-10-17 | Method of making radar reflector |
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Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2909791A (en) * | 1956-07-19 | 1959-10-27 | Jr Robert R Malary | Sandwich construction for seaplane floats |
US2913036A (en) * | 1956-08-10 | 1959-11-17 | Anthony Bros Fibre Glass Pool | Process and apparatus for molding large plastic structures |
US2950883A (en) * | 1955-06-14 | 1960-08-30 | Wesley K Landes | Skifor aircraft and the like |
US2958621A (en) * | 1956-11-20 | 1960-11-01 | Goodyear Aircraft Corp | Method of making a dome-like body of plastic reinforced fibers |
US2987983A (en) * | 1958-10-28 | 1961-06-13 | Isel I Solzman | Plastic casing for air exhauster |
US3043054A (en) * | 1959-03-23 | 1962-07-10 | Goodyear Aircraft Corp | Spherical self-supporting enclosures |
US3060453A (en) * | 1959-12-18 | 1962-10-30 | Swan George Dewey | Stall enclosure |
US3065940A (en) * | 1956-06-22 | 1962-11-27 | Emil L Eckstein | Aircraft outer surface covering |
US3074832A (en) * | 1957-12-04 | 1963-01-22 | Detag | Plastic window plate structure and method of making same |
US3085925A (en) * | 1957-02-20 | 1963-04-16 | Konenklijke Nl Vliegtuigenfabr | Method of forming an aircraft part having a pliable deicer boot thereon |
US3087581A (en) * | 1960-03-07 | 1963-04-30 | Pitman Mfg Company | Fiberglas structural member and method of making same |
US3091262A (en) * | 1957-08-19 | 1963-05-28 | Darworth Inc | Metal-fiber reinforced resin laminate |
US3136674A (en) * | 1959-12-09 | 1964-06-09 | Robert V Dunkle | Method of making electromagnetic wave reflector |
US3161556A (en) * | 1961-08-01 | 1964-12-15 | Bonafide Mills Inc | Method of making plastic terrazzo sheet material |
US3369843A (en) * | 1965-07-16 | 1968-02-20 | Philip E. Prew | Laminated wheel and method of manufacture |
US3932249A (en) * | 1973-04-13 | 1976-01-13 | Comalco (J. & S.) Pty. Limited | Mesh reinforced elastomeric polymers |
US3977773A (en) * | 1975-01-17 | 1976-08-31 | Rohr Industries, Inc. | Solar energy concentrator |
US4171563A (en) * | 1977-05-20 | 1979-10-23 | U.S. Philips Corporation | Method of manufacturing an antenna reflector |
US4188358A (en) * | 1976-03-29 | 1980-02-12 | U.S. Philips Corporation | Method of manufacturing a metallized plastic reflector |
US4216047A (en) * | 1978-09-15 | 1980-08-05 | Boeing Commercial Airplane Company | No-bleed curing of composites |
US4255364A (en) * | 1977-12-12 | 1981-03-10 | Talbert John W | Large mirror replication process |
US4563321A (en) * | 1977-10-13 | 1986-01-07 | Gessford James D | Method of producing a plastic unitary curved structure with two surfaces and a honeycomb shaped core |
US4780262A (en) * | 1986-01-15 | 1988-10-25 | The Boeing Company | Method for making composite structures |
US4836765A (en) * | 1987-12-03 | 1989-06-06 | United Technologies Corporation | Molding apparatus for composite materials |
US5437756A (en) * | 1990-07-16 | 1995-08-01 | United Technologies Corp. | Method of making a composite sphere for a motion base simulator with a low center of gravity |
US5440801A (en) * | 1994-03-03 | 1995-08-15 | Composite Optics, Inc. | Composite antenna |
WO2008061661A1 (en) * | 2006-11-21 | 2008-05-29 | Novation S.P.A. | Process for the moulding of multilayered fibre-reinforced polymer articles and articles so obtained |
CN103407170A (en) * | 2013-07-26 | 2013-11-27 | 北京卫星制造厂 | Manufacturing method for satellite borne antenna reflecting surface |
WO2017042442A1 (en) * | 2015-09-10 | 2017-03-16 | Airbus Safran Launchers Sas | Method for manufacturing an antenna reflector shell with a metallized ply, in particular for a spacecraft |
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Cited By (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2950883A (en) * | 1955-06-14 | 1960-08-30 | Wesley K Landes | Skifor aircraft and the like |
US3065940A (en) * | 1956-06-22 | 1962-11-27 | Emil L Eckstein | Aircraft outer surface covering |
US2909791A (en) * | 1956-07-19 | 1959-10-27 | Jr Robert R Malary | Sandwich construction for seaplane floats |
US2913036A (en) * | 1956-08-10 | 1959-11-17 | Anthony Bros Fibre Glass Pool | Process and apparatus for molding large plastic structures |
US2958621A (en) * | 1956-11-20 | 1960-11-01 | Goodyear Aircraft Corp | Method of making a dome-like body of plastic reinforced fibers |
US3085925A (en) * | 1957-02-20 | 1963-04-16 | Konenklijke Nl Vliegtuigenfabr | Method of forming an aircraft part having a pliable deicer boot thereon |
US3091262A (en) * | 1957-08-19 | 1963-05-28 | Darworth Inc | Metal-fiber reinforced resin laminate |
US3074832A (en) * | 1957-12-04 | 1963-01-22 | Detag | Plastic window plate structure and method of making same |
US2987983A (en) * | 1958-10-28 | 1961-06-13 | Isel I Solzman | Plastic casing for air exhauster |
US3043054A (en) * | 1959-03-23 | 1962-07-10 | Goodyear Aircraft Corp | Spherical self-supporting enclosures |
US3136674A (en) * | 1959-12-09 | 1964-06-09 | Robert V Dunkle | Method of making electromagnetic wave reflector |
US3060453A (en) * | 1959-12-18 | 1962-10-30 | Swan George Dewey | Stall enclosure |
US3087581A (en) * | 1960-03-07 | 1963-04-30 | Pitman Mfg Company | Fiberglas structural member and method of making same |
US3161556A (en) * | 1961-08-01 | 1964-12-15 | Bonafide Mills Inc | Method of making plastic terrazzo sheet material |
US3369843A (en) * | 1965-07-16 | 1968-02-20 | Philip E. Prew | Laminated wheel and method of manufacture |
US3932249A (en) * | 1973-04-13 | 1976-01-13 | Comalco (J. & S.) Pty. Limited | Mesh reinforced elastomeric polymers |
US3977773A (en) * | 1975-01-17 | 1976-08-31 | Rohr Industries, Inc. | Solar energy concentrator |
US4188358A (en) * | 1976-03-29 | 1980-02-12 | U.S. Philips Corporation | Method of manufacturing a metallized plastic reflector |
US4171563A (en) * | 1977-05-20 | 1979-10-23 | U.S. Philips Corporation | Method of manufacturing an antenna reflector |
US4563321A (en) * | 1977-10-13 | 1986-01-07 | Gessford James D | Method of producing a plastic unitary curved structure with two surfaces and a honeycomb shaped core |
US4255364A (en) * | 1977-12-12 | 1981-03-10 | Talbert John W | Large mirror replication process |
US4216047A (en) * | 1978-09-15 | 1980-08-05 | Boeing Commercial Airplane Company | No-bleed curing of composites |
US4780262A (en) * | 1986-01-15 | 1988-10-25 | The Boeing Company | Method for making composite structures |
US4836765A (en) * | 1987-12-03 | 1989-06-06 | United Technologies Corporation | Molding apparatus for composite materials |
US5437756A (en) * | 1990-07-16 | 1995-08-01 | United Technologies Corp. | Method of making a composite sphere for a motion base simulator with a low center of gravity |
US5440801A (en) * | 1994-03-03 | 1995-08-15 | Composite Optics, Inc. | Composite antenna |
US5771027A (en) * | 1994-03-03 | 1998-06-23 | Composite Optics, Inc. | Composite antenna |
WO2008061661A1 (en) * | 2006-11-21 | 2008-05-29 | Novation S.P.A. | Process for the moulding of multilayered fibre-reinforced polymer articles and articles so obtained |
CN103407170A (en) * | 2013-07-26 | 2013-11-27 | 北京卫星制造厂 | Manufacturing method for satellite borne antenna reflecting surface |
CN103407170B (en) * | 2013-07-26 | 2016-03-30 | 北京卫星制造厂 | A kind of preparation method of satellite antenna reflecting surface |
WO2017042442A1 (en) * | 2015-09-10 | 2017-03-16 | Airbus Safran Launchers Sas | Method for manufacturing an antenna reflector shell with a metallized ply, in particular for a spacecraft |
FR3041165A1 (en) * | 2015-09-10 | 2017-03-17 | Airbus Defence & Space Sas | METHOD FOR MANUFACTURING ANTENNA REFLECTOR SHELL WITH METALLIZED PLI, IN PARTICULAR A SPACE DEVICE |
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