US3103887A - Pre-stressed glass fiber attachment ring - Google Patents
Pre-stressed glass fiber attachment ring Download PDFInfo
- Publication number
- US3103887A US3103887A US13663A US1366360A US3103887A US 3103887 A US3103887 A US 3103887A US 13663 A US13663 A US 13663A US 1366360 A US1366360 A US 1366360A US 3103887 A US3103887 A US 3103887A
- Authority
- US
- United States
- Prior art keywords
- radome
- glass fiber
- ring
- band
- missile
- 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
Links
- 239000003365 glass fiber Substances 0.000 title description 18
- 239000000919 ceramic Substances 0.000 claims description 11
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 230000035882 stress Effects 0.000 description 13
- 239000000463 material Substances 0.000 description 5
- 239000000835 fiber Substances 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000004568 cement Substances 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000005065 mining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Definitions
- the present invention relates to an attaching and coupling means and more particularly to a method and means for securing a relatively thin shelled member to a second member.
- the attachment must not only withstand the structural loads over wide temperature ranges, but also must perform satisfactorily through high heating rates, since under these conditions, the thermal stresses resulting from difierential expansion and temperature gradients will add to the ordinary structural loads.
- the satisfactory attachment must also maintain the assembly in coupled relationship with a high degree of stiffness. In missiles having a high fineness ratio, that is, a high length to diameter ratio, it is extremely desirable to maintain overall stiffness in order that the natural frequency of the missile structure be high. Structural advantages as well as operational advantages accrue from a high natural frequency in a missile structure. Other obvious requirements of a satisfactory attachment are low Weight, small cross-section, fabrication cost and ease of assembly.
- the present invention will not only provide a satisfactory coupling from a structural standpoint with high strength, low Weight and cross-section, but will also provide advantageous features such as elimination of certain inherent electrical problems, avoidance of use of critical materials, and ease and low cost of fabrication. While the present invention is herein described in connection with a ceramic radome and a metal missile body, it will readily be seen that it is applicable as an attachment device for ceramicto-ceramic or meta-l-to-metal connections.
- the present invention comprises a ring of glass fibers or other high strength filament wrapped under tension and cured onto one of the members to be joined in such manner as to produce a residual stress in the ring.
- the resulting assembly of the ring and member is then secured to the other member by a plurality of mechanical fasteners. Presence of the residual stress in the ring provides a strong combination bonded-mechanical joint which will withstand high stresses of differential thermal expansions as well as of severe structural loads.
- the ceramic radome is encircled by the glass fiber ring to produce a combination bonded-mechanical joint, shear fasteners being provided to secure the ring to the missile body.
- FIG. 1 is an elevation showing the missile radome coupled to a missile body by the present invention
- FIG. 2 is an enlarged fragmentary section showing the glass fiber ring wrapped onto the ceramic radome.
- FIG. 3 is an enlarged fragmentary section showing the attaching details.
- FIG. 1 shows a missile '10 having a ceramic radome 12 coupled to a missile body 14 by an attachment 16 constituting the present invention.
- the randome '12 is provided on the outer periphery thereof with a groove 18 near the aft end of the randome, the forward portion of the groove being somewhat deeper than the rearward portion.
- a circular band 20 Positioned at the aft end of the radome 12 is a circular band 20 having an inwardly depending flange 22 which abuts the radome and is cemented thereto by cement 23.
- Girdling the radome 12 and band 20 is a glass fiber ring 24 that is wrapped under tension and cured thereon so as to provide a residual compressive stress in the ceramic radome.
- FIG. 3 it can be seen that a plurality of apertures 26 are formed around the periphery of the band 20 and extend through the ring 24, the apertures being countersunk on the inner face of the ban-d. Pressed into the apertures 26 are inserts 28 which accommodate screws 30 for engagement with a forwardly extending flange 32 on the missile body 14. 'Interposed between the end of the flange 32 and the flange 22 is a seal 34.
- the glass fiber ring 24 is first bonded to the ceramic radome 12 and then mechanically fastened to the missile body 14 to securely attach the radome to the missile body. Because the ring 24 is formed with glass fibers wrapped under tension, a residual hoop tension stress is produced therein which is maintained after curing. This tension in the glass fiber ring coupled with the fact that the groove 18 is formed with a reverse taper provides a combination bonded-mechanical joint and solves the problem of differential expansions since any thermal stress induce-d will be opposed by the residual stress in the ring.
- the band 20 which is preferably made of steel, tends to maintain a better sealing surface and also tends to hold the internal tolerance on surface mating to the missile body. More important, however, is the fact that the band 20 also provides a high modulus and strength to resist compression fastener loads, and to retain tension pre-stress in the aft portion of the glass fiber ring 24 to resist compress-ion fastener loads.
- the tension wrapping of the radome 1 2 is best done by mounting it and the band 20 in juxtaposition on a mandrel, a cement :23 being applied to the abutting surfaces of the end of the radome and the flange 22 of the band 20.
- the surface of the radome and band to receive the glass fiber wrapping is wetted with an adhesive such as Epon VIII.
- Glass fibers in the form of tape such as type XP ISO or XP'126 produced by the Minnesota Mining and amass? Manufacturing Co., is then wrapped onto the radorne and band under tension of the order of 125-300 pounds depending on the amount of pre-stressing desired.
- the last layer of tangential tape may be sealed just before releasing the tension by applying heat from a soldering iron.
- the radome, band and glass fiber ring are cured in an oven for about six or seven hours at approximately 300 F. Machining of the excess glass fiber material is best accomplished after the curing step, and as previously mentioned, residual stresses remain in the ring and radome after curing and machining.
- an attachment for coupling said radorne and body comprising, a peripheral groove in the outer wall of said radome at the aft end thereof, said groove being deeper at its forward end than at its aft end, an annular metallic band in juxtaposition with the rear of said radome and having an inwardly depending flange secured to the rear face of said rado-me, said metallic band having an internal diameter slightly greater than- 2.
- said flange is cemented to the rear face of said radome.
Description
. 1963 A. B. NEPPLE 3,103,887
PRE-STRESSED GLASS FIBER ATTACHMENT RING Filed March 8, 1960 ARTHUR B. NEPPLE INVENT OR.
Q. EDM QKT ATTORNEYS Patented Sept. 17, 1963 3,1tl3,887 PRE-STRESSED GLASS FIBER ATTACHMENT RING Arthur B. Nepple, Rockville, Md, assignor to the United States of America as represented by the Secretary of the Navy Filed Mar. 8, 1964), Ser. No. 13,663 2 Claims. (Cl. 10256) The present invention relates to an attaching and coupling means and more particularly to a method and means for securing a relatively thin shelled member to a second member.
Attaching problems arise whenever relatively thin walled members are to be joined to another member, especially when the first member is of brittle material and the structural loads encountered are of considerable magnitude. Such conditions are present in certain missile designs where ceramic material is used in airframe primary structures because of the favorable characteristics of such materials in a high temperature environment. It is apparent that this use of ceramic material will create a special requirement for satisfactory ceramicto-metal and ceramic-to-ceramie attachments. Because of the relatively low tensile strength of ceramics as compared to steel, and because of its complete lack of duetili-ty, it is not feasible to utilize conventional attaching methods. The attachment must not only withstand the structural loads over wide temperature ranges, but also must perform satisfactorily through high heating rates, since under these conditions, the thermal stresses resulting from difierential expansion and temperature gradients will add to the ordinary structural loads. The satisfactory attachment must also maintain the assembly in coupled relationship with a high degree of stiffness. In missiles having a high fineness ratio, that is, a high length to diameter ratio, it is extremely desirable to maintain overall stiffness in order that the natural frequency of the missile structure be high. Structural advantages as well as operational advantages accrue from a high natural frequency in a missile structure. Other obvious requirements of a satisfactory attachment are low Weight, small cross-section, fabrication cost and ease of assembly.
It is therefore the principle object of the present invention to provide a suitable attachment device for coupling a thin-shelled brittle member such as a missile radome to a second member such as a missile body. The present invention will not only provide a satisfactory coupling from a structural standpoint with high strength, low Weight and cross-section, but will also provide advantageous features such as elimination of certain inherent electrical problems, avoidance of use of critical materials, and ease and low cost of fabrication. While the present invention is herein described in connection with a ceramic radome and a metal missile body, it will readily be seen that it is applicable as an attachment device for ceramicto-ceramic or meta-l-to-metal connections.
Briefly, the present invention comprises a ring of glass fibers or other high strength filament wrapped under tension and cured onto one of the members to be joined in such manner as to produce a residual stress in the ring. The resulting assembly of the ring and member is then secured to the other member by a plurality of mechanical fasteners. Presence of the residual stress in the ring provides a strong combination bonded-mechanical joint which will withstand high stresses of differential thermal expansions as well as of severe structural loads. In a ceramic radome and metallic missile body application, the ceramic radome is encircled by the glass fiber ring to produce a combination bonded-mechanical joint, shear fasteners being provided to secure the ring to the missile body.
Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings in which:
FIG. 1 is an elevation showing the missile radome coupled to a missile body by the present invention;
FIG. 2 is an enlarged fragmentary section showing the glass fiber ring wrapped onto the ceramic radome; and
FIG. 3 is an enlarged fragmentary section showing the attaching details.
Referring now to the drawing in detail, FIG. 1 shows a missile '10 having a ceramic radome 12 coupled to a missile body 14 by an attachment 16 constituting the present invention.
In FIG. 2 it can be seen that the randome '12 is provided on the outer periphery thereof with a groove 18 near the aft end of the randome, the forward portion of the groove being somewhat deeper than the rearward portion. Positioned at the aft end of the radome 12 is a circular band 20 having an inwardly depending flange 22 which abuts the radome and is cemented thereto by cement 23. Girdling the radome 12 and band 20 is a glass fiber ring 24 that is wrapped under tension and cured thereon so as to provide a residual compressive stress in the ceramic radome.
In FIG. 3 it can be seen that a plurality of apertures 26 are formed around the periphery of the band 20 and extend through the ring 24, the apertures being countersunk on the inner face of the ban-d. Pressed into the apertures 26 are inserts 28 which accommodate screws 30 for engagement with a forwardly extending flange 32 on the missile body 14. 'Interposed between the end of the flange 32 and the flange 22 is a seal 34.
It is seen then that the glass fiber ring 24 is first bonded to the ceramic radome 12 and then mechanically fastened to the missile body 14 to securely attach the radome to the missile body. Because the ring 24 is formed with glass fibers wrapped under tension, a residual hoop tension stress is produced therein which is maintained after curing. This tension in the glass fiber ring coupled with the fact that the groove 18 is formed with a reverse taper provides a combination bonded-mechanical joint and solves the problem of differential expansions since any thermal stress induce-d will be opposed by the residual stress in the ring. While this pre-stress in tension in the ring, with accompanying compressive pre-stress in the radome, prevents the ring from loosening from the radome due to any temperature rise of the joint under high speed flight conditions, excessive pre-stress is undesirable since it results in excessive stresses in the radome. Also, excessive pressures within the glass fiber ring could tend to force resin out.
The incorporation of the band 20, which is preferably made of steel, tends to maintain a better sealing surface and also tends to hold the internal tolerance on surface mating to the missile body. More important, however, is the fact that the band 20 also provides a high modulus and strength to resist compression fastener loads, and to retain tension pre-stress in the aft portion of the glass fiber ring 24 to resist compress-ion fastener loads.
The tension wrapping of the radome 1 2 is best done by mounting it and the band 20 in juxtaposition on a mandrel, a cement :23 being applied to the abutting surfaces of the end of the radome and the flange 22 of the band 20. The surface of the radome and band to receive the glass fiber wrapping is wetted with an adhesive such as Epon VIII. Glass fibers in the form of tape such as type XP ISO or XP'126 produced by the Minnesota Mining and amass? Manufacturing Co., is then wrapped onto the radorne and band under tension of the order of 125-300 pounds depending on the amount of pre-stressing desired. After one layer of the tape is wound tangentially onto the radome and band, the mandrel is stopped and, with the tension maintained on the tape, a layer of glass fibers with the fibers running axially is placed over the first layer. Adherence of the axial fiber layer to the first layer is obtained by heating and softening the resin with a warm air dryer. Alternate layers of tangentially wound tape and axial fibers are then installed onto the radome and band until the desired thickness is obtained. Four or five of these alternate layers have been found to produce excellent results; however, it has been discovered that superior results have been obtained by overwrapping, that is, by wrapping a considerable excess of glass fiber material onto the Iadome and band, and then machining to the desired diameter. By this method, greater hoop loading stresses in the ring have been. attained.
The last layer of tangential tape may be sealed just before releasing the tension by applying heat from a soldering iron. After the wrapping is completed, the radome, band and glass fiber ring are cured in an oven for about six or seven hours at approximately 300 F. Machining of the excess glass fiber material is best accomplished after the curing step, and as previously mentioned, residual stresses remain in the ring and radome after curing and machining.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
What is claimed is:
1. In an aerial missile having a ceramic radome and a metallic body, an attachment for coupling said radorne and body, comprising, a peripheral groove in the outer wall of said radome at the aft end thereof, said groove being deeper at its forward end than at its aft end, an annular metallic band in juxtaposition with the rear of said radome and having an inwardly depending flange secured to the rear face of said rado-me, said metallic band having an internal diameter slightly greater than- 2. The invention as recited in claim 1 wherein said flange is cemented to the rear face of said radome.
References Cited in the file of this patent UNITED STATES PATENTS 1,794,905 Kass Mar. 3, 1931 2,336,143 Werme Dec. 7, 1943 2,782,716 Johnston Feb. 26, 1957 2,792,618 Walker May 21, 1957 2,337,456 Parilla June 3, 1958 2,872,865 Skaar Feb. 10, 1959 2,918,006 Zborowski Dec. 22, 1959 2,925,776 Ferris Feb. 23, 1960 2,931,273 Weatherhead Apr. 5, 1960 FOREIGN PATENTS 279,063 Italy Oct. 29, 1930
Claims (1)
1. IN AN AERIAL MISSILE HAVING A CERAMIC RADOME AND A METALLIC BODY, AN ATTACHMENT FOR COUPLING SAID RADOME AND BODY, COMPRISING, A PERIPHERAL GROOVE IN THE OUTER WALL OF SAID RADOME AT THE AFT END THEREOF, SAID GROOVE BEING DEEPER AT ITS FORWARD END THAN AT ITS AFT END, AN ANNULAR METALLIC BAND IN JUXTAPOSITION WITH THE REAR OF SAID RADOME AND HAVING AN INWARDLY DEPENDING FLANGE SECURED TO THE REAR FACE OF SAID RADOME, SAID METALLIC BAND HAVING AN INTERNAL DIAMETER SLIGHTLY GREATER THAN
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13663A US3103887A (en) | 1960-03-08 | 1960-03-08 | Pre-stressed glass fiber attachment ring |
US184622A US3116547A (en) | 1960-03-08 | 1962-03-02 | Method for coupling a pair of cylindrical members in end-to-end abutment |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13663A US3103887A (en) | 1960-03-08 | 1960-03-08 | Pre-stressed glass fiber attachment ring |
Publications (1)
Publication Number | Publication Date |
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US3103887A true US3103887A (en) | 1963-09-17 |
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ID=21761073
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US13663A Expired - Lifetime US3103887A (en) | 1960-03-08 | 1960-03-08 | Pre-stressed glass fiber attachment ring |
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Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3183024A (en) * | 1962-03-13 | 1965-05-11 | Jack A Myers | Radial wedge joint |
US3310256A (en) * | 1965-07-27 | 1967-03-21 | James E Webb | Aerodynamic protection for space flight vehicles |
DE1254998B (en) * | 1964-04-20 | 1967-11-23 | Dornier System Gmbh | Altitude research rocket |
US3633948A (en) * | 1970-01-08 | 1972-01-11 | Ronald E Dickey | Abrasion-resistant pipe coupling |
US3885818A (en) * | 1974-04-02 | 1975-05-27 | Mueller Co | Insulated coupling joint |
US4446794A (en) * | 1979-04-02 | 1984-05-08 | Aktiebolaget Bofors | Practice shell particularly useful for training purposes |
US5686692A (en) * | 1996-09-30 | 1997-11-11 | The United States Of America As Represented By The Secretary Of The Navy | Single fuse follow-through grenade |
US6410867B1 (en) | 2000-07-11 | 2002-06-25 | Abb Inc. | Bolted conical loading joint system |
US6495785B1 (en) | 2000-06-29 | 2002-12-17 | Abb Power T&D Company Inc. | Non-glue mounting of non-metallic tubes |
US20100045029A1 (en) * | 2008-08-22 | 2010-02-25 | Younes Youssef | Axially-tensioned pipe joint |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1794905A (en) * | 1925-10-01 | 1931-03-03 | Samuel M Kass | Pipe joint |
US2336143A (en) * | 1941-01-04 | 1943-12-07 | Remington Arms Co Inc | Method of making projectiles |
US2782716A (en) * | 1953-11-30 | 1957-02-26 | North American Aviation Inc | Destructible cover for fragile dome |
US2792618A (en) * | 1953-11-23 | 1957-05-21 | Woodrow A Walker | Method of construction of dual jacket partition bullets |
US2837456A (en) * | 1952-02-29 | 1958-06-03 | Kellogg M W Co | Filament wound container |
US2872865A (en) * | 1955-09-29 | 1959-02-10 | Karsten S Skaar | High strength fiber glass-metal construction and process for its manufacture |
US2918006A (en) * | 1950-11-10 | 1959-12-22 | Helmut P G A R Von Zborowski | Destruction engines carrying a hollow charge |
US2925776A (en) * | 1944-05-15 | 1960-02-23 | Robert G Ferris | Combination amplifier and oscillator unit |
US2931273A (en) * | 1957-06-28 | 1960-04-05 | Weatherhead Co | Rocket launcher |
-
1960
- 1960-03-08 US US13663A patent/US3103887A/en not_active Expired - Lifetime
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1794905A (en) * | 1925-10-01 | 1931-03-03 | Samuel M Kass | Pipe joint |
US2336143A (en) * | 1941-01-04 | 1943-12-07 | Remington Arms Co Inc | Method of making projectiles |
US2925776A (en) * | 1944-05-15 | 1960-02-23 | Robert G Ferris | Combination amplifier and oscillator unit |
US2918006A (en) * | 1950-11-10 | 1959-12-22 | Helmut P G A R Von Zborowski | Destruction engines carrying a hollow charge |
US2837456A (en) * | 1952-02-29 | 1958-06-03 | Kellogg M W Co | Filament wound container |
US2792618A (en) * | 1953-11-23 | 1957-05-21 | Woodrow A Walker | Method of construction of dual jacket partition bullets |
US2782716A (en) * | 1953-11-30 | 1957-02-26 | North American Aviation Inc | Destructible cover for fragile dome |
US2872865A (en) * | 1955-09-29 | 1959-02-10 | Karsten S Skaar | High strength fiber glass-metal construction and process for its manufacture |
US2931273A (en) * | 1957-06-28 | 1960-04-05 | Weatherhead Co | Rocket launcher |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3183024A (en) * | 1962-03-13 | 1965-05-11 | Jack A Myers | Radial wedge joint |
DE1254998B (en) * | 1964-04-20 | 1967-11-23 | Dornier System Gmbh | Altitude research rocket |
US3310256A (en) * | 1965-07-27 | 1967-03-21 | James E Webb | Aerodynamic protection for space flight vehicles |
US3633948A (en) * | 1970-01-08 | 1972-01-11 | Ronald E Dickey | Abrasion-resistant pipe coupling |
US3885818A (en) * | 1974-04-02 | 1975-05-27 | Mueller Co | Insulated coupling joint |
US4446794A (en) * | 1979-04-02 | 1984-05-08 | Aktiebolaget Bofors | Practice shell particularly useful for training purposes |
US5686692A (en) * | 1996-09-30 | 1997-11-11 | The United States Of America As Represented By The Secretary Of The Navy | Single fuse follow-through grenade |
US6495785B1 (en) | 2000-06-29 | 2002-12-17 | Abb Power T&D Company Inc. | Non-glue mounting of non-metallic tubes |
US6410867B1 (en) | 2000-07-11 | 2002-06-25 | Abb Inc. | Bolted conical loading joint system |
US20100045029A1 (en) * | 2008-08-22 | 2010-02-25 | Younes Youssef | Axially-tensioned pipe joint |
US8007014B2 (en) * | 2008-08-22 | 2011-08-30 | Younes Youssef | Axially-tensioned pipe joint |
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