US20180370613A1 - Composite structure with integrated hinge - Google Patents
Composite structure with integrated hinge Download PDFInfo
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- US20180370613A1 US20180370613A1 US15/629,580 US201715629580A US2018370613A1 US 20180370613 A1 US20180370613 A1 US 20180370613A1 US 201715629580 A US201715629580 A US 201715629580A US 2018370613 A1 US2018370613 A1 US 2018370613A1
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- 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
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Definitions
- Composite materials such as carbon fiber reinforced polymer materials, typically are used in applications in which properties of such materials may be advantageous.
- such materials are strong but lightweight, resulting in their widespread use in fields such as aviation or other lightweight air, ground, or waterborne vehicles.
- composite materials are rigid, which can be an advantage in certain respects but may be a limitation in others.
- the rigidity of composite materials may make them unsuitable for use in applications that may require a more flexible material and/or one that may be more durable over many cycles of being bent or flexed.
- FIG. 1 is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- FIG. 2A is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- FIG. 2B is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- FIG. 2C is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- FIG. 3 is a flow chart illustrating an embodiment of a process to fabricate a composite structure with an integrated hinge.
- FIG. 4 is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- the invention can be implemented in numerous ways, including as a process; an apparatus; a system; a composition of matter; a computer program product embodied on a computer readable storage medium; and/or a processor, such as a processor configured to execute instructions stored on and/or provided by a memory coupled to the processor.
- these implementations, or any other form that the invention may take, may be referred to as techniques.
- the order of the steps of disclosed processes may be altered within the scope of the invention.
- a component such as a processor or a memory described as being configured to perform a task may be implemented as a general component that is temporarily configured to perform the task at a given time or a specific component that is manufactured to perform the task.
- the term ‘processor’ refers to one or more devices, circuits, and/or processing cores configured to process data, such as computer program instructions.
- a composite structure with an integrated hinge comprising one or more layers of high strength synthetic fiber fabric, such as Kevlar® or another aramid material or material with similar properties, is disclosed.
- one or more layers of high strength synthetic fiber fabric, such as Kevlar® or another aramid material or material with similar properties are interleaved with other composite layers in an overlapping manner that results in a composite structure in which a portion of the high strength synthetic fiber fabric is present in a region that joins a first relatively rigid composite component/structure to a second relatively rigid composite component in a flexibly bendable manner.
- a composite structure with an integrated hinge as disclosed herein includes an aircraft component, such as a wing, tail, or other aerodynamic structure, in which an integrated hinge as disclosed herein joins an access flap to the aircraft component, enabling access to be gained to structures located under the flap, e.g., by lifting the flap and thereby bending the hinge.
- an aircraft component such as a wing, tail, or other aerodynamic structure
- an integrated hinge as disclosed herein joins an access flap to the aircraft component, enabling access to be gained to structures located under the flap, e.g., by lifting the flap and thereby bending the hinge.
- FIG. 1 is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- airfoil 102 e.g., an aircraft wing or tail structure, comprises a composite shell formed in the shape of airfoil 102 , e.g., using a mold or other tool.
- layers of carbon fiber reinforced fabric that has been pre-impregnated with a resin, such as epoxy, commonly referred to as “pre-preg”, may be laid out (by hand, robot or other automated machine, etc.) on a mold or other tool in the shape of the desired composite structure, or a portion thereof, and the resulting layering material cured to form a rigid, durable composite structure.
- airfoil 102 has an aerodynamic control structure 104 at a trailing edge of airfoil 102 .
- aerodynamic control structure 104 include without limitation an aileron, elevator, elevon, spoiler, flap, or other structure.
- aerodynamic control structure 104 is positioned (e.g., moved up, down, and/or back to a neutral position) via a mechanical linkage 106 .
- the mechanical linkage 106 is driven, in this example, by structures to which access (e.g., for repair) is provided via a hinged flap 108 .
- hinged flap 108 provides access to a void 110 in which a servo motor and/or associated power supply and/or control circuits and/or wires or other connectors are located.
- access to void 110 may be gained by lifting up a free end of hinged flap 108 , i.e., an end opposite a hinged end by which flap 108 is attached integrally with the composite structure of airfoil 102 .
- hinged flap 108 is attached integrally with the composite structure of airfoil 102 by a hinge structure comprising one or more layers of Kevlar® or other aramid or other polymer fabric material having high strength (e.g., tensile strength) and greater flexibility as compared to the composite structure of airfoil 102 itself.
- hinged flap 108 may comprise a flap made of the same or similar composition as the composite structure of airfoil 102 , and a hinge material comprising one or more layer interleaved with adjacent layers of the composite material comprising airfoil 102 .
- the resulting structure(s) in some embodiments may be compressed (e.g., by vacuum, a press, or other means) and cured to form a combined structure comprising the composite structure of airfoil 102 (e.g., multi-layer carbon fiber reinforced polymer composite), a hinge portion (e.g., one or more layers of Kevlar®), and a flap portion comprising a segment of rigid composite material coupled to the composite structure of airfoil 102 by the hinge portion.
- the composite structure of airfoil 102 e.g., multi-layer carbon fiber reinforced polymer composite
- a hinge portion e.g., one or more layers of Kevlar®
- a flap portion comprising a segment of rigid composite material coupled to the composite structure of airfoil 102 by the hinge portion.
- FIG. 1 shows a hinged access flap on the upper surface of airfoil 102
- a hinged structure is instead and/or in addition included on the bottom surface.
- FIG. 2A is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- a composite structure 200 is shown to be formed by interleaving with carbon reinforced polymer fabric (e.g., pre-preg) layers 202 , 204 , and 206 , on one side, and with carbon reinforced polymer fabric (e.g., pre-preg) layers 212 , 214 , and 216 , on the other side, layers of durable, flexible hinge material 220 , 222 .
- hinge material layers 220 , 222 comprise Kevlar® or material having properties (e.g., strength, flexibility) similar to Kevlar®.
- FIG. 2B is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- the materials comprising composite structure 200 of FIG. 2A are shown in a compressed and cured state in which adjacent layers and/or portions thereof have been bonded to one another.
- bonded and cured composite layers 202 , 204 , and 206 are shown to form a composite structure, such as may be used in some embodiments to provide a structure such as airfoil 102 of FIG. 1 .
- First ends of hinge materials 220 and 222 are shown to be interleaved between and cured with, and therefore bonded to, adjacent layers 202 , 204 , and 206 .
- Opposite ends of hinge materials 220 and 222 are shown to be interleaved between and cured with, and therefore bonded to, composite material layers 212 , 214 , and 216 .
- the rightmost end of the composite structure comprising layers 212 , 214 , and 216 is free, as in the free (trailing) end of hinged flap 108 of FIG. 1 .
- FIG. 2C is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- the free end of the (hinged flap) composite structure comprising layers 212 , 214 , and 216 has been lifted upwards (as shown) by bending/flexing the hinge material 220 , 222 .
- the hinge material 220 , 222 would tend to return to its original, unbent state, such that release of the composite structure comprising layers 212 , 214 , and 216 would result in the hinge material 220 , 222 unbending and the composite structure comprising layers 212 , 214 , and 216 returning to the position shown in FIG. 2B .
- the hinge material 220 , 222 comprises two layers of prepreg Kevlar, e.g., 0 . 004 in thick layers, both oriented in the 0°/90° direction.
- hinge material 220 and hinge material 222 overlap by a minimum of 1 ⁇ 2 inch (total) with the ends not superimposed on top of one another, e.g., in some embodiments they are staggered by 1 ⁇ 4 inch or so on each side as shown.
- FIG. 3 is a flow chart illustrating an embodiment of a process to fabricate a composite structure with an integrated hinge.
- the process of FIG. 3 may be used to form a composite structure with an integrated hinge, such as one or more of airfoil 102 and hinged flap 108 of FIG. 1 and/or the composite structure 200 of FIGS. 2A-2C .
- prepreg fabric layers are laid up, e.g., in one or more molds, forms, or other tools, to (begin to) define a primary structure (e.g., airfoil 102 of FIG. 1 ) and an access flap (e.g., rigid composite flap 108 of FIG. 1 ) ( 302 ).
- prepreg layers may be laid up on opposite sides of a single mold or in separate molds in adjacent positions, e.g., on a work bench or other surface.
- the composite layers of the primary structure, on the one hand, and the access flap (or other secondary structure) on the other hand may be spaced apart by a distance associated with an exposed portion of a hinge to be formed between the primary and secondary composite structures.
- the exposed portion of the hinge may mechanically couple the primary structure to the secondary structure (e.g., access flap), enabling the second structure to be manipulated in the finished product by bending the exposed portion of the hinge.
- any “first” and “second” composite structures may be connected by an integrated hinge as disclosed herein.
- Kevlar® or other flexible hinged materials are interleaved with adjacent layers of prepreg (or other rigid composite precursor material) ( 304 ).
- segments of Kevlar® may be laid across opposite edges of the lower layer stack of the primary and secondary composite structures, and alternating layers in between, followed by one or more upper layers of prepreg.
- the laminate stacks, including the interleaved hinge materials, are cured ( 306 ).
- pressure may be applied to compress the stacked layers of material, and the combined mass heated to cure the resin in the prepreg, resulting in a composite structure comprising an integrated flexible hinged, the hinge comprising hinge material interleaved with and bonded at each end with alternating layers of composite material.
- FIG. 4 is a diagram illustrating an embodiment of a composite structure with an integrated hinge.
- airfoil 102 of FIG. 1 is shown in perspective view 400 to comprise a wing or other aerodynamic structure having a control surface 104 positioned along a portion of the trailing edge of the airfoil 102 .
- Hinged flap 108 is shown to overlap a forward edge of the control surface 104 at a free end of hinged flap 108 and to be flexibly coupled to and integrated with airfoil 102 by a hinge material 220 , such as Kevlar®.
- the hinged flap 108 may be lifted at its free end, which results in the hinge material 220 bending and access being gained to a void or other region below hinged flap 108 , such as the linkage 106 and/or servo motor 112 of FIG. 1 .
- a composite structure with an integrated hinge may be used to provide a hinged access flap or other structure having a durable, flexible hinged attachment to and integration with a primary composite structure.
- integrating the hinge material into the composite layer stack, as disclosed herein may enable the hinge to be integrated with the composite structure in a secure manner without requiring additional adhesives or mounting hardware.
- the resulting structure may have minimal drag and lower complexity and/or failure modes as compared to other solutions to provide an access flap or other hinged connection between composite parts.
Abstract
Description
- Composite materials, such as carbon fiber reinforced polymer materials, typically are used in applications in which properties of such materials may be advantageous. For example, such materials are strong but lightweight, resulting in their widespread use in fields such as aviation or other lightweight air, ground, or waterborne vehicles.
- Typically, composite materials are rigid, which can be an advantage in certain respects but may be a limitation in others. For example, in aviation and other applications, the rigidity of composite materials may make them unsuitable for use in applications that may require a more flexible material and/or one that may be more durable over many cycles of being bent or flexed.
- Various embodiments of the invention are disclosed in the following detailed description and the accompanying drawings.
-
FIG. 1 is a diagram illustrating an embodiment of a composite structure with an integrated hinge. -
FIG. 2A is a diagram illustrating an embodiment of a composite structure with an integrated hinge. -
FIG. 2B is a diagram illustrating an embodiment of a composite structure with an integrated hinge. -
FIG. 2C is a diagram illustrating an embodiment of a composite structure with an integrated hinge. -
FIG. 3 is a flow chart illustrating an embodiment of a process to fabricate a composite structure with an integrated hinge. -
FIG. 4 is a diagram illustrating an embodiment of a composite structure with an integrated hinge. - The invention can be implemented in numerous ways, including as a process; an apparatus; a system; a composition of matter; a computer program product embodied on a computer readable storage medium; and/or a processor, such as a processor configured to execute instructions stored on and/or provided by a memory coupled to the processor. In this specification, these implementations, or any other form that the invention may take, may be referred to as techniques. In general, the order of the steps of disclosed processes may be altered within the scope of the invention. Unless stated otherwise, a component such as a processor or a memory described as being configured to perform a task may be implemented as a general component that is temporarily configured to perform the task at a given time or a specific component that is manufactured to perform the task. As used herein, the term ‘processor’ refers to one or more devices, circuits, and/or processing cores configured to process data, such as computer program instructions.
- A detailed description of one or more embodiments of the invention is provided below along with accompanying figures that illustrate the principles of the invention. The invention is described in connection with such embodiments, but the invention is not limited to any embodiment. The scope of the invention is limited only by the claims and the invention encompasses numerous alternatives, modifications and equivalents. Numerous specific details are set forth in the following description in order to provide a thorough understanding of the invention. These details are provided for the purpose of example and the invention may be practiced according to the claims without some or all of these specific details. For the purpose of clarity, technical material that is known in the technical fields related to the invention has not been described in detail so that the invention is not unnecessarily obscured.
- A composite structure with an integrated hinge comprising one or more layers of high strength synthetic fiber fabric, such as Kevlar® or another aramid material or material with similar properties, is disclosed. In various embodiments, one or more layers of high strength synthetic fiber fabric, such as Kevlar® or another aramid material or material with similar properties, are interleaved with other composite layers in an overlapping manner that results in a composite structure in which a portion of the high strength synthetic fiber fabric is present in a region that joins a first relatively rigid composite component/structure to a second relatively rigid composite component in a flexibly bendable manner. For example, in one application, a composite structure with an integrated hinge as disclosed herein includes an aircraft component, such as a wing, tail, or other aerodynamic structure, in which an integrated hinge as disclosed herein joins an access flap to the aircraft component, enabling access to be gained to structures located under the flap, e.g., by lifting the flap and thereby bending the hinge.
-
FIG. 1 is a diagram illustrating an embodiment of a composite structure with an integrated hinge. In the example shown,airfoil 102, e.g., an aircraft wing or tail structure, comprises a composite shell formed in the shape ofairfoil 102, e.g., using a mold or other tool. In some embodiments, layers of carbon fiber reinforced fabric that has been pre-impregnated with a resin, such as epoxy, commonly referred to as “pre-preg”, may be laid out (by hand, robot or other automated machine, etc.) on a mold or other tool in the shape of the desired composite structure, or a portion thereof, and the resulting layering material cured to form a rigid, durable composite structure. In the example shown,airfoil 102 has anaerodynamic control structure 104 at a trailing edge ofairfoil 102. Examples of anaerodynamic control structure 104 include without limitation an aileron, elevator, elevon, spoiler, flap, or other structure. - In the example shown,
aerodynamic control structure 104 is positioned (e.g., moved up, down, and/or back to a neutral position) via amechanical linkage 106. Themechanical linkage 106 is driven, in this example, by structures to which access (e.g., for repair) is provided via ahinged flap 108. Specifically, hingedflap 108 provides access to avoid 110 in which a servo motor and/or associated power supply and/or control circuits and/or wires or other connectors are located. As shown in the lowermost drawing ofFIG. 1 , access tovoid 110 may be gained by lifting up a free end of hingedflap 108, i.e., an end opposite a hinged end by whichflap 108 is attached integrally with the composite structure ofairfoil 102. - In various embodiments, hinged
flap 108 is attached integrally with the composite structure ofairfoil 102 by a hinge structure comprising one or more layers of Kevlar® or other aramid or other polymer fabric material having high strength (e.g., tensile strength) and greater flexibility as compared to the composite structure ofairfoil 102 itself. For example, in some embodiments, hingedflap 108 may comprise a flap made of the same or similar composition as the composite structure ofairfoil 102, and a hinge material comprising one or more layer interleaved with adjacent layers of the compositematerial comprising airfoil 102. The resulting structure(s) in some embodiments may be compressed (e.g., by vacuum, a press, or other means) and cured to form a combined structure comprising the composite structure of airfoil 102 (e.g., multi-layer carbon fiber reinforced polymer composite), a hinge portion (e.g., one or more layers of Kevlar®), and a flap portion comprising a segment of rigid composite material coupled to the composite structure ofairfoil 102 by the hinge portion. - While
FIG. 1 shows a hinged access flap on the upper surface ofairfoil 102, in some embodiments a hinged structure is instead and/or in addition included on the bottom surface. -
FIG. 2A is a diagram illustrating an embodiment of a composite structure with an integrated hinge. In the example shown, acomposite structure 200 is shown to be formed by interleaving with carbon reinforced polymer fabric (e.g., pre-preg)layers layers flexible hinge material material layers -
FIG. 2B is a diagram illustrating an embodiment of a composite structure with an integrated hinge. In the example shown, the materials comprisingcomposite structure 200 ofFIG. 2A are shown in a compressed and cured state in which adjacent layers and/or portions thereof have been bonded to one another. In the example shown, bonded and curedcomposite layers airfoil 102 ofFIG. 1 . First ends ofhinge materials adjacent layers hinge materials composite material layers - In various embodiments, the rightmost end of the composite
structure comprising layers hinged flap 108 ofFIG. 1 . -
FIG. 2C is a diagram illustrating an embodiment of a composite structure with an integrated hinge. In the position shown inFIG. 2C , the free end of the (hinged flap) compositestructure comprising layers hinge material hinge material structure comprising layers hinge material structure comprising layers FIG. 2B . - In some embodiments, the
hinge material material 220 and hingematerial 222 overlap by a minimum of ½ inch (total) with the ends not superimposed on top of one another, e.g., in some embodiments they are staggered by ¼ inch or so on each side as shown. -
FIG. 3 is a flow chart illustrating an embodiment of a process to fabricate a composite structure with an integrated hinge. In various embodiments, the process ofFIG. 3 may be used to form a composite structure with an integrated hinge, such as one or more ofairfoil 102 and hingedflap 108 ofFIG. 1 and/or thecomposite structure 200 ofFIGS. 2A-2C . In the example shown, prepreg fabric layers are laid up, e.g., in one or more molds, forms, or other tools, to (begin to) define a primary structure (e.g.,airfoil 102 ofFIG. 1 ) and an access flap (e.g., rigidcomposite flap 108 ofFIG. 1 ) (302). For example, prepreg layers may be laid up on opposite sides of a single mold or in separate molds in adjacent positions, e.g., on a work bench or other surface. The composite layers of the primary structure, on the one hand, and the access flap (or other secondary structure) on the other hand may be spaced apart by a distance associated with an exposed portion of a hinge to be formed between the primary and secondary composite structures. The exposed portion of the hinge may mechanically couple the primary structure to the secondary structure (e.g., access flap), enabling the second structure to be manipulated in the finished product by bending the exposed portion of the hinge. - Note that while the term “primary” and “secondary” are sometimes used herein to refer to composite structured joined by an integrated hinge as disclosed herein, in various embodiments any “first” and “second” composite structures may be connected by an integrated hinge as disclosed herein.
- In nearly adjacent regions of the primary structure, on the one hand, and the access flap or other secondary structure, on the other, layers of Kevlar® or other flexible hinged materials are interleaved with adjacent layers of prepreg (or other rigid composite precursor material) (304). For example, segments of Kevlar® may be laid across opposite edges of the lower layer stack of the primary and secondary composite structures, and alternating layers in between, followed by one or more upper layers of prepreg.
- The laminate stacks, including the interleaved hinge materials, are cured (306). For example, pressure may be applied to compress the stacked layers of material, and the combined mass heated to cure the resin in the prepreg, resulting in a composite structure comprising an integrated flexible hinged, the hinge comprising hinge material interleaved with and bonded at each end with alternating layers of composite material.
-
FIG. 4 is a diagram illustrating an embodiment of a composite structure with an integrated hinge. In the example shown,airfoil 102 ofFIG. 1 is shown inperspective view 400 to comprise a wing or other aerodynamic structure having acontrol surface 104 positioned along a portion of the trailing edge of theairfoil 102. Hingedflap 108 is shown to overlap a forward edge of thecontrol surface 104 at a free end of hingedflap 108 and to be flexibly coupled to and integrated withairfoil 102 by ahinge material 220, such as Kevlar®. In various embodiments, the hingedflap 108 may be lifted at its free end, which results in thehinge material 220 bending and access being gained to a void or other region below hingedflap 108, such as thelinkage 106 and/orservo motor 112 ofFIG. 1 . - In various embodiments, a composite structure with an integrated hinge, as disclosed herein, may be used to provide a hinged access flap or other structure having a durable, flexible hinged attachment to and integration with a primary composite structure. In various embodiments, integrating the hinge material into the composite layer stack, as disclosed herein, may enable the hinge to be integrated with the composite structure in a secure manner without requiring additional adhesives or mounting hardware. The resulting structure may have minimal drag and lower complexity and/or failure modes as compared to other solutions to provide an access flap or other hinged connection between composite parts.
- Although the foregoing embodiments have been described in some detail for purposes of clarity of understanding, the invention is not limited to the details provided. There are many alternative ways of implementing the invention. The disclosed embodiments are illustrative and not restrictive.
Claims (18)
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US16/210,274 US10647408B2 (en) | 2017-06-21 | 2018-12-05 | Composite structure with integrated hinge |
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US15/629,580 US10179642B1 (en) | 2017-06-21 | 2017-06-21 | Composite structure with integrated hinge |
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Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
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GB2584996A (en) * | 2019-06-18 | 2020-12-30 | Gkn Aerospace Services Ltd | Adaptive structure |
CN112977802A (en) * | 2021-02-26 | 2021-06-18 | 珠海天晴航空航天科技有限公司 | Integrated control surface connecting structure, manufacturing method and unmanned aerial vehicle |
US11059565B2 (en) | 2018-11-21 | 2021-07-13 | The Boeing Company | Airflow-dependent deployable fences for aircraft wings |
US11059564B2 (en) | 2018-11-21 | 2021-07-13 | The Boeing Company | Automated deployable fences for aircraft wings |
US11066149B2 (en) | 2018-11-21 | 2021-07-20 | The Boeing Company | Airflow-dependent deployable fences for aircraft wings |
US11130561B2 (en) * | 2018-11-21 | 2021-09-28 | The Boeing Company | Airflow-dependent deployable fences for aircraft wings |
US11449108B2 (en) | 2020-03-05 | 2022-09-20 | Microsoft Technology Licensing, Llc | Flexible hinge device |
Families Citing this family (1)
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JP6270299B1 (en) * | 2017-07-03 | 2018-01-31 | 株式会社国際気象コンサルタント | Hinge and hinge roll |
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US3445052A (en) | 1966-08-22 | 1969-05-20 | Phillips Petroleum Co | Hinged laminate |
US5350614A (en) * | 1991-07-25 | 1994-09-27 | United Technologies Corporation | All composite article of manufacture including first and second composite members joined by a composite hinge |
JP3451041B2 (en) * | 1999-09-17 | 2003-09-29 | 川崎重工業株式会社 | Flap hinge mechanism, method of manufacturing the same, and flap hinge device |
DE10018893A1 (en) | 2000-04-14 | 2001-10-25 | Acts Gmbh & Co Kg | Instrument panel for a motor vehicle and method for producing a plastic carrier for an instrument panel |
EP1738895B1 (en) | 2005-06-29 | 2012-07-18 | SGL Carbon SE | Joint |
IT1402386B1 (en) | 2010-09-17 | 2013-09-04 | Automobili Lamborghini Spa | HINGE FOR COMPOSITE MATERIALS AND PROCESS FOR ITS MANUFACTURING |
US10544610B2 (en) | 2013-08-06 | 2020-01-28 | Lockheed Martin Corporation | Composite live hinge |
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2017
- 2017-06-21 US US15/629,580 patent/US10179642B1/en active Active
- 2017-06-22 WO PCT/US2017/038818 patent/WO2018236383A1/en active Application Filing
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- 2018-12-05 US US16/210,274 patent/US10647408B2/en active Active
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11059565B2 (en) | 2018-11-21 | 2021-07-13 | The Boeing Company | Airflow-dependent deployable fences for aircraft wings |
US11059564B2 (en) | 2018-11-21 | 2021-07-13 | The Boeing Company | Automated deployable fences for aircraft wings |
US11066149B2 (en) | 2018-11-21 | 2021-07-20 | The Boeing Company | Airflow-dependent deployable fences for aircraft wings |
US11130561B2 (en) * | 2018-11-21 | 2021-09-28 | The Boeing Company | Airflow-dependent deployable fences for aircraft wings |
GB2584996A (en) * | 2019-06-18 | 2020-12-30 | Gkn Aerospace Services Ltd | Adaptive structure |
GB2584996B (en) * | 2019-06-18 | 2023-08-02 | Gkn Aerospace Services Ltd | Adaptive structure |
US11449108B2 (en) | 2020-03-05 | 2022-09-20 | Microsoft Technology Licensing, Llc | Flexible hinge device |
CN112977802A (en) * | 2021-02-26 | 2021-06-18 | 珠海天晴航空航天科技有限公司 | Integrated control surface connecting structure, manufacturing method and unmanned aerial vehicle |
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US10179642B1 (en) | 2019-01-15 |
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US10647408B2 (en) | 2020-05-12 |
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