DE102017216085A1 - Method for producing a strut and strut made thereby - Google Patents
Method for producing a strut and strut made thereby Download PDFInfo
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- DE102017216085A1 DE102017216085A1 DE102017216085.3A DE102017216085A DE102017216085A1 DE 102017216085 A1 DE102017216085 A1 DE 102017216085A1 DE 102017216085 A DE102017216085 A DE 102017216085A DE 102017216085 A1 DE102017216085 A1 DE 102017216085A1
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- bore
- brace
- slot
- extending
- central
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Classifications
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- 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
- B29D23/00—Producing tubular articles
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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
- B29C70/32—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 on a rotating mould, former or core
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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
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C7/00—Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads
- F16C7/02—Constructions of connecting-rods with constant length
- F16C7/026—Constructions of connecting-rods with constant length made of fibre reinforced resin
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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
- B29C2793/00—Shaping techniques involving a cutting or machining operation
- B29C2793/0036—Slitting
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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
- B29C2793/00—Shaping techniques involving a cutting or machining operation
- B29C2793/009—Shaping techniques involving a cutting or machining operation after shaping
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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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
- B29C53/583—Winding and joining, e.g. winding spirally helically for making tubular articles with particular features
- B29C53/585—Winding and joining, e.g. winding spirally helically for making tubular articles with particular features the cross-section varying along their axis, e.g. tapered, with ribs, or threads, with socket-ends
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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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
- B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
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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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
- B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
- B29C53/602—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels for tubular articles having closed or nearly closed ends, e.g. vessels, tanks, containers
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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
- B29C57/00—Shaping of tube ends, e.g. flanging, belling or closing; Apparatus therefor, e.g. collapsible mandrels
- B29C57/02—Belling or enlarging, e.g. combined with forming a groove
- B29C57/04—Belling or enlarging, e.g. combined with forming a groove using mechanical means
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- 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
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2220/00—Shaping
- F16C2220/28—Shaping by winding impregnated fibres
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2326/00—Articles relating to transporting
- F16C2326/47—Cosmonautic vehicles, i.e. bearings adapted for use in outer-space
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Ein Verfahren zum Herstellen einer Verstrebung mit einer hohlen Mittelbohrung umfasst die Schritte des Bereitstellen eines Dorns und einer Menge eines Faden- oder Fasermaterials; Legen des Faden- oder Fasermaterials um den Dorn, um eine Verstrebung auszubilden mit einem zylindrischen Mittelabschnitt, zwei einander gegenüberliegenden Verbindungsendabschnitten, einer Mittelbohrung, die sich durch die Verstrebung erstreckt, wobei die Mittelbohrung zwei Abschnitte mit reduziertem Durchmesser aufweist, die sich durch jeden Endabschnitt erstrecken, und einer Achse, die sich im Wesentlichen mittig durch die Bohrung erstreckt; Ausbilden eines Schlitzes oder von Schlitzen, der sich von einem äußeren Ende des einen der Verbindungsabschnitte nach innen erstreckt und innerhalb des einen Verbindungsabschnitts oder des Mittelabschnitts endet; Umbiegen von zumindest einem Teil des einen Verbindungsabschnitts entlang des Schlitzes, um so den Bohrungsabschnitt mit reduziertem Durchmesser an einem Ende zu vergrößern; und Verschieben des Dorns entlang der Mittelachse und durch den vergrößerten Bohrungsendabschnitt, bis der Dorn aus der Verstrebungsbohrung entfernt ist.A method of making a brace with a hollow center bore comprises the steps of providing a mandrel and a quantity of a filament or fibrous material; Laying the filamentary material around the mandrel to form a brace having a cylindrical central portion, two opposed connecting end portions, a central bore extending through the brace, the central bore having two reduced diameter portions extending through each end portion and an axis extending substantially centrally through the bore; Forming a slit or slits extending inwardly from an outer end of the one of the connecting portions and terminating within the one connecting portion or the central portion; Bending at least a portion of the one connecting portion along the slot so as to enlarge the reduced diameter bore portion at one end; and displacing the mandrel along the central axis and through the enlarged bore end portion until the mandrel is removed from the brace bore.
Description
HINTERGRUND DER ERFINDUNGBACKGROUND OF THE INVENTION
Die vorliegende Erfindung betrifft Verstrebungen und insbesondere eine Verstrebung, die in einer Luft- und Raumfahrtstruktur verwendet wird.The present invention relates to struts, and more particularly to a strut used in an aerospace structure.
Luft- und Raumfahrtverstrebungen sind bekannt und weisen im Allgemeinen einen zylindrischen Körper mit einander gegenüberliegenden Enden, die mit einer Flugzeugzelle verbunden sind, auf. Diese Verstrebungen nehmen üblicherweise Belastungen, vorzugsweise in Spannung und Kompression, auf. Einige Luft- und Raumfahrtverstrebungen sind aus Komposit-Materialien, wie beispielsweise Fasern und Harz, gebildet.Aerospace struts are known and generally have a cylindrical body with opposite ends connected to an airframe. These braces usually absorb loads, preferably in tension and compression. Some aerospace struts are made of composite materials such as fibers and resin.
ZUSAMMENFASSUNG DER ERFINDUNGSUMMARY OF THE INVENTION
In einem Aspekt ist die vorliegende Erfindung ein Verfahren zum Herstellen einer Verstrebung mit einer hohlen Zentralbohrung, wobei das Verfahren die Schritte aufweist: Bereitstellen eines Dorns und einer Vielzahl eines Faden- oder Fasermaterials; Legen des Faden- oder Fasermaterials um den Dorn, um eine Verstrebung mit einem im Wesentlichen zylindrischen Mittelabschnitt, zwei einander gegenüberliegenden Verbindungsendabschnitten, eine Mittelbohrung, die sich durch die Verstrebung erstreckt, wobei die Mittelbohrung zwei Abschnitte mit reduziertem Durchmesser aufweist, die sich durch den jeweiligen Endabschnitt erstrecken, und eine Achse, die sich mittig durch die Bohrung erstreckt, auszubilden; Ausbilden von zumindest einem Schlitz, der sich von einem äußeren Ende einer der Verbindungsabschnitte nach innen erstreckt und innerhalb der einen Verbindungsabschnitte oder dem Mittelabschnitt endet; Biegen von zumindest einem Teilabschnitt des einen Verbindungsabschnitts entlang des Schlitzes, um so den Abschnitt der Bohrung mit reduziertem Durchmesser an zumindest einem Ende zu vergrößern; und Verschieben des Dorns im Allgemeinen entlang der Mittelachse und durch den vergrößerten Bohrungsendabschnitt bis der Dorn aus der Verstrebungsbohrung entfernt ist.In one aspect, the present invention is a method of making a brace having a hollow central bore, the method comprising the steps of: providing a mandrel and a plurality of filamentary or fibrous material; Placing the filamentary material around the mandrel about a strut having a substantially cylindrical central portion, two opposed connecting end portions, a central bore extending through the strut, the central bore having two reduced diameter portions extending through the respective one Endabschnitt extend, and an axis that extends centrally through the bore form; Forming at least one slot extending inwardly from an outer end of one of the connecting portions and terminating within the one connecting portion or the middle portion; Bending at least a portion of the one connecting portion along the slot so as to increase the portion of the reduced diameter bore at at least one end; and displacing the mandrel generally along the central axis and through the enlarged bore end portion until the mandrel is removed from the brace bore.
In einem anderen Aspekt ist die vorliegende Erfindung eine Verstrebung mit einem länglichen Körper, der aus gelegten Fäden/Fasern und Harz gebildet ist, wobei der Körper einen im Allgemeinen zylindrischen Mittelabschnitt, zwei einander gegenüberliegende, Verbindungsendabschnitte, eine Mittelbohrung, die sich durch die Verstrebung erstreckt, aufweist. Die Mittelbohrung hat zwei Abschnitte mit reduziertem Durchmesser, die sich durch den jeweiligen Endabschnitt erstrecken und eine Achse, die sich mittig durch die Bohrung erstreckt. Die Fäden oder Fasern des Mittelabschnitts sind im Wesentlichen durchgängig und frei von verschweißten Teilen.In another aspect, the present invention is a strut having an elongated body formed of laid filaments / fibers and resin, the body having a generally cylindrical central portion, two opposing connecting end portions, a central bore extending through the strut , having. The center bore has two reduced diameter portions extending through the respective end portion and an axis extending centrally through the bore. The threads or fibers of the central portion are substantially continuous and free of welded parts.
KURZE BESCHREIBUNG VON EINIGEN ANSICHTEN DER ZEICHNUNGENBRIEF DESCRIPTION OF SOME VIEWS OF THE DRAWINGS
Die vorstehende Zusammenfassung, genauso wie die detaillierte Beschreibung der bevorzugten Ausführungsbeispiele der vorliegenden Erfindung werden besser verstanden, wenn sie in Verbindung mit den angehängten Zeichnungen gelesen wird. Zum Zweck der Illustration der Erfindung, werden in den Zeichnungen, die schematisch sind, Ausführungsbeispiele gezeigt, die momentan bevorzugt sind. Es ist zu verstehen, dass dennoch die Erfindung nicht auf die genauen Anordnungen und Ausgestaltungen, die gezeigt sind, limitiert ist. In den Zeichnungen:The foregoing summary, as well as the detailed description of the preferred embodiments of the present invention, will be better understood when read in conjunction with the appended drawings. For the purpose of illustrating the invention, there will be shown in the drawings, which are schematic, embodiments which are presently preferred. It is understood, however, that the invention is nevertheless not limited to the precise arrangements and configurations shown. In the drawings:
DETAILLIERTE BESCHREIBUNG DER ERFINDUNGDETAILED DESCRIPTION OF THE INVENTION
Unter Bezugnahme nun auf die Zeichnungen im Detail, bei denen ähnliche Bezugszeichen verwendet werden, um ähnliche Elemente zu bezeichnen, wird in den
Bezugnehmend auf die
Die Schlitze
Bezugnehmend insbesondere auf
Bezugnehmend auf
Bezugnehmend auf
Bezugnehmend auf die
Es wird bei den Fachleuten gewertschätzt werden, dass Änderungen an den Ausführungsbeispielen, die oben beschrieben sind, gemacht werden können, ohne von dem breiten erfindungsgemäßen Konzept abzuweichen. Es ist deshalb zu verstehen, dass die Erfindung nicht auf die speziellen Ausführungsbeispiele, die offenbart sind, beschränkt ist, sondern dazu gedacht ist, Modifikationen innerhalb der Idee und des Rahmens der vorliegenden Erfindung abzudecken, wie sie im Allgemeinen hierin und in den angehängten Ansprüchen definiert ist.It will be appreciated by those skilled in the art that changes may be made to the embodiments described above without departing from the broad inventive concept. It is therefore to be understood that the invention is not limited to the particular embodiments disclosed, but is intended to cover modifications within the spirit and scope of the present invention as defined in general herein and in the appended claims is.
Claims (12)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US201662400272P | 2016-09-27 | 2016-09-27 | |
US62/400,272 | 2016-09-27 |
Publications (1)
Publication Number | Publication Date |
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DE102017216085A1 true DE102017216085A1 (en) | 2018-03-29 |
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ID=61564407
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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DE102017216085.3A Pending DE102017216085A1 (en) | 2016-09-27 | 2017-09-12 | Method for producing a strut and strut made thereby |
Country Status (3)
Country | Link |
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CN (1) | CN107866986B (en) |
DE (1) | DE102017216085A1 (en) |
FR (1) | FR3056439B1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3578337A1 (en) * | 2018-06-08 | 2019-12-11 | Goodrich Corporation | Composite tube |
US10927883B2 (en) | 2017-07-11 | 2021-02-23 | Goodrich Corporation | Composite joint assembly |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110126300A (en) * | 2019-05-05 | 2019-08-16 | 宜兴市新立织造有限公司 | A kind of composite material undercarriage and preparation method thereof using 3 D weaving |
CN110966284A (en) * | 2019-12-18 | 2020-04-07 | 肇庆市海特复合材料技术研究院 | Composite material connecting joint and preparation method thereof |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
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US20050056117A1 (en) * | 2003-07-22 | 2005-03-17 | Kaiser Compositek, Inc. | Composite strut and method of making same |
ITPD20040175A1 (en) * | 2004-07-02 | 2004-10-02 | Giuseppe Bottacin | PROCEDURE FOR THE STRUCTURAL JOINING OF CABLE MODULES OF GENERICALLY ELONGATED FORM, FOR THE PURPOSE OF PRODUCING COLUMNS OR CAVE RODS AND PRODUCT OBTAINED |
FR2944469A1 (en) * | 2009-04-16 | 2010-10-22 | Messier Dowty Sa | METHOD FOR MANUFACTURING A ROD IN COMPOSITE MATERIAL HAVING ENHANCED ENDS |
US9486965B2 (en) * | 2011-11-03 | 2016-11-08 | The Boeing Company | Composite columnar structure having co-bonded reinforcement and fabrication method |
BE1021537B1 (en) * | 2012-10-11 | 2015-12-09 | Bd Invent S.A. | BIELLE MONOBLOC |
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2017
- 2017-09-12 DE DE102017216085.3A patent/DE102017216085A1/en active Pending
- 2017-09-20 FR FR1758705A patent/FR3056439B1/en active Active
- 2017-09-26 CN CN201710878558.3A patent/CN107866986B/en active Active
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10927883B2 (en) | 2017-07-11 | 2021-02-23 | Goodrich Corporation | Composite joint assembly |
EP3578337A1 (en) * | 2018-06-08 | 2019-12-11 | Goodrich Corporation | Composite tube |
US10823213B2 (en) | 2018-06-08 | 2020-11-03 | Goodrich Corporation | Composite joint assembly |
Also Published As
Publication number | Publication date |
---|---|
CN107866986B (en) | 2022-03-15 |
FR3056439A1 (en) | 2018-03-30 |
CN107866986A (en) | 2018-04-03 |
FR3056439B1 (en) | 2021-07-02 |
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