公开(公告)号：US20180141246A1

公开(公告)日：2018-05-24

申请号：US15872706

申请日：2018-01-16

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Suvankar Mishra ,  John R. McCullough ,  Mark Chris ,  Stanley B. Woychesin

IPC: B29C44/04 ,  B32B27/12 ,  B29C44/12 ,  B29C70/86 ,  B32B3/04 ,  B32B3/12 ,  B32B3/26 ,  B32B5/18 ,  B32B27/06 ,  B32B7/12 ,  B32B7/02 ,  B32B5/26 ,  B32B5/24 ,  B32B27/08

CPC classification number: B29C44/0415 ,  B29C44/128 ,  B29C70/865 ,  B32B3/04 ,  B32B3/12 ,  B32B3/263 ,  B32B5/18 ,  B32B5/245 ,  B32B5/26 ,  B32B7/02 ,  B32B7/12 ,  B32B27/065 ,  B32B27/08 ,  B32B27/12 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/542 ,  B32B2605/18 ,  Y02T50/43 ,  Y10T428/24149 ,  Y10T428/249953

Abstract: A composite structure includes a first face sheet, a second face sheet, and a foam member located between the first face sheet and the second face sheet. The foam member has a molded contour, the mold contour being configured to provide tooling surface for at least one of the first face sheet and the second face sheet prior to curing of the composite structure. A method of making the foam member includes creating a mold tool having an interior surface which resembles the desired outer contour of the foam member. A mixture is poured into a pour opening in the mold tool. The mixture is allowed to polymerize into a foam as the foam expands and distributes within the mold tool. Vent openings in the mold tool are selectively tailored to control the density of the foam member. The foam member is cured in the mold tool.

公开(公告)号：US20160089844A1

公开(公告)日：2016-03-31

申请号：US14496271

申请日：2014-09-25

Applicant: Bell Helicopter Textron Inc.

Inventor： Suvankar Mishra ,  Jesse Wrabel ,  John R. McCullough ,  Randall Willnow ,  Carl May

IPC: B29C73/10 ,  B29C73/02

CPC classification number: B29C73/10 ,  B29C44/1214 ,  B29C44/1276 ,  B29C44/128 ,  B29C44/18 ,  B29C66/02241 ,  B29C73/02 ,  B29C73/04 ,  B29C73/06 ,  B29C2073/264 ,  B29L2031/082 ,  B29L2031/3076 ,  B29L2031/3085 ,  B29L2031/3088 ,  B29L2031/608 ,  B64F5/40

Abstract: A method of repairing a core stiffened structure can include removing a damaged portion of the core stiffened structure; creating a cutout in a portion of a repair core member; fitting the repair core member onto an existing core member such that the cutout mates with a portion of the existing core member; bonding the repair core member to the existing core member; and placing a skin patch over the repair core member.

Abstract translation: 修复芯加固结构的方法可以包括去除芯加固结构的损坏部分; 在修复核心部件的一部分中形成切口; 将修复芯构件装配到现有的芯构件上，使得切口与现有芯构件的一部分配合; 将修复芯构件粘合到现有的芯构件上; 并将皮肤贴片放置在修复芯部件上。

公开(公告)号：US11027465B2

公开(公告)日：2021-06-08

申请号：US16141127

申请日：2018-09-25

Applicant: Bell Helicopter Textron Inc.

Inventor： James A. Cordell ,  Suvankar Mishra ,  Andrew Paul Haldeman ,  Jesse J. Wrabel ,  Dalton T. Hampton

IPC: B29C44/18 ,  B64C11/26 ,  B29C44/34 ,  B29C44/60 ,  B29C44/42 ,  B29L31/08 ,  B64C27/473

Abstract: A method is provided in one example embodiment and may include positioning at least one nozzle within a hollow portion of a rotor blade at a distance associated with a span of the rotor blade and providing, via the at least one nozzle, a liquid foam mixture in the hollow portion, wherein the liquid foam expands and becomes a solid foam material that fills the hollow portion of the rotor blade. Another method is provided in another example embodiment and may include providing a plurality of openings for a rotor blade that are positioned proximate to a hollow portion of the rotor blade and providing a liquid foam mixture in the hollow portion of the rotor blade through at least one opening of the rotor blade, wherein the liquid foam mixture expands and becomes a solid foam material that fills the hollow portion of the rotor blade.

公开(公告)号：US10899084B2

公开(公告)日：2021-01-26

申请号：US16036228

申请日：2018-07-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Suvankar Mishra ,  Jesse J. Wrabel ,  Vance N. Cribb, III

IPC: B29C65/00 ,  B32B37/10 ,  B32B37/06 ,  B32B38/10 ,  B32B43/00 ,  B32B37/00

Abstract: A method is provided in one example embodiment and may include forming a ply stack comprising a plurality of uncured composite plies, wherein one or more uncured composite ply of the plurality of uncured composite plies comprises a plurality of perforations that extend, at least partially, through a thickness of the one or more uncured composite ply; and compacting the ply stack to form a composite structure. The plurality of perforations may provide paths for volatiles to be removed through the thickness of the one or more uncured composite ply of the ply stack during the compacting. Volatiles may also be removed through edges of the ply stack during the compacting. In some instances, all uncured composite plies of the ply stack may include a plurality of perforations that extend, at least partially, through the thickness of each uncured composite ply.

公开(公告)号：US20160303818A1

公开(公告)日：2016-10-20

申请号：US15195501

申请日：2016-06-28

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ramesh Thiagarajan ,  Suvankar Mishra ,  Mark Chris ,  William Evans, III ,  Mike Mikel

IPC: B32B3/08 ,  B29C44/08 ,  B32B5/18 ,  B29C44/58 ,  B29C44/60 ,  B64C5/10 ,  B29C44/04 ,  B29C44/10

CPC classification number: B32B3/08 ,  B29C44/025 ,  B29C44/0415 ,  B29C44/086 ,  B29C44/10 ,  B29C44/588 ,  B29C44/60 ,  B29K2075/00 ,  B29K2105/04 ,  B29L2031/3076 ,  B32B1/00 ,  B32B5/18 ,  B32B5/245 ,  B32B5/26 ,  B32B5/28 ,  B32B7/06 ,  B32B7/12 ,  B32B2250/03 ,  B32B2250/40 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2266/0278 ,  B32B2305/022 ,  B32B2305/076 ,  B32B2305/10 ,  B32B2603/00 ,  B32B2605/18 ,  B64C1/068 ,  B64C3/20 ,  B64C3/24 ,  B64C5/10 ,  B64C2001/0072 ,  B64C2027/4736 ,  Y02T50/43 ,  Y10T156/10 ,  Y10T428/233 ,  Y10T428/249953 ,  Y10T428/249982

Abstract: A structure includes a skin and a foam member. The foam member has a molded contour, the mold contour being configured to provide tooled surface for the skin. When the skin is a composite skin, the foam member provides support for the skin so that the skin can be cured under heat and pressure. A method of making the foam member for a foam stiffened structure includes creating a mold having an interior cavity which resembles a desired shape the foam member. A subsequent step involves introducing a foam mixture into the mold. Next, the foam mixture is allowed to polymerize so as to expand and distribute within the cavity of the mold. The method further includes selectively controlling a density of the foam member in the mold. The foam member is at least partially cured. The foam member is assembled with a skin to produce the foam stiffened structure.

Abstract translation: 结构包括皮肤和泡沫构件。 泡沫构件具有模制轮廓，模具轮廓被配置成为皮肤提供工具表面。 当皮肤是复合皮肤时，泡沫构件为皮肤提供支撑，使得皮肤可以在热和压力下固化。 制造用于泡沫硬化结构的泡沫构件的方法包括产生具有类似于所需形状的泡沫构件的内部空腔的模具。 随后的步骤包括将泡沫混合物引入模具中。 接下来，允许泡沫混合物聚合，以便在模具的空腔内膨胀和分布。 该方法还包括选择性地控制模具中泡沫构件的密度。 泡沫构件至少部分固化。 泡沫构件与皮肤组装以产生泡沫硬化结构。

公开(公告)号：US20140120298A1

公开(公告)日：2014-05-01

申请号：US13664010

申请日：2012-10-30

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ramesh Thiagarajan ,  Theodore W. Ingram, III ,  John R. McCullough ,  Suvankar Mishra ,  Carl May

IPC: B32B3/06 ,  B32B3/26 ,  B32B3/12

CPC classification number: B32B3/12 ,  B29C73/06 ,  B29C73/10 ,  B29C2073/264 ,  B29L2031/082 ,  B29L2031/608 ,  Y10T428/24008 ,  Y10T428/24157 ,  Y10T428/249953

Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

公开(公告)号：US20140119930A1

公开(公告)日：2014-05-01

申请号：US13663954

申请日：2012-10-30

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ramesh Thiagarajan ,  Robert Mark Chris ,  John R. McCullough ,  Suvankar Mishra

IPC: B32B38/00 ,  B64C27/46 ,  B32B3/12 ,  B32B3/26

CPC classification number: B29C44/1228 ,  B29L2031/082 ,  B29L2031/608 ,  B32B3/12 ,  B32B5/20 ,  B32B7/02 ,  B32B7/12 ,  B32B2307/304 ,  B32B2307/306 ,  B32B2603/00 ,  B64F5/40 ,  Y10T428/192

Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

公开(公告)号：US11298899B2

公开(公告)日：2022-04-12

申请号：US16450739

申请日：2019-06-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Suvankar Mishra ,  Vance Newton Cribb, III

IPC: B29C73/02 ,  B64F5/40 ,  B29C73/24 ,  B64C11/26 ,  B29L31/08 ,  B29C44/18 ,  B29C65/54

Abstract: A method of repairing a composite structure includes providing an assembled composite structure comprising a substantially rigid outer component, wherein the composite structure comprises a void space at least partially bounded by the outer component. The method further includes forming an injection hole through the outer component to provide a path between the void space and space external to the composite structure. The method further includes injecting foam into the void space through the injection hole while the foam is in a substantially unexpanded state and expanding the foam within the void space.

公开(公告)号：US20200016880A1

公开(公告)日：2020-01-16

申请号：US16036228

申请日：2018-07-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Suvankar Mishra ,  Jesse J. Wrabel ,  Vance N. Cribb, III

IPC: B32B37/10 ,  B32B38/10 ,  B32B43/00 ,  B32B37/06 ,  B32B37/00

Abstract: A method is provided in one example embodiment and may include forming a ply stack comprising a plurality of uncured composite plies, wherein one or more uncured composite ply of the plurality of uncured composite plies comprises a plurality of perforations that extend, at least partially, through a thickness of the one or more uncured composite ply; and compacting the ply stack to form a composite structure. The plurality of perforations may provide paths for volatiles to be removed through the thickness of the one or more uncured composite ply of the ply stack during the compacting. Volatiles may also be removed through edges of the ply stack during the compacting. In some instances, all uncured composite plies of the ply stack may include a plurality of perforations that extend, at least partially, through the thickness of each uncured composite ply.

公开(公告)号：US20180244397A1

公开(公告)日：2018-08-30

申请号：US15444085

申请日：2017-02-27

Applicant: Bell Helicopter Textron Inc.

Inventor： Timothy Brian Carr ,  Suvankar Mishra ,  Michael Stephen Deslatte ,  Michael Douglas Ishmael ,  Ronald James Turner

IPC: B64D37/00 ,  B64D37/02 ,  B05D1/02

CPC classification number: B64D37/005 ,  B05D1/02 ,  B64D37/02 ,  B64D37/06

Abstract: An aircraft fuel system includes one or more fuel cells adapted to contain fuel, a fuel cell receiving assembly having an inner surface adapted to receive the one or more fuel cells and a fuel cell cushion disposed between the inner surface of the fuel cell receiving assembly and the one or more fuel cells. The fuel cell cushion is machined from a foam substrate to form a shaped foam substrate that is substantially covered with a cushion coating. The cushion coating is sprayable onto the shaped foam substrate such that the fuel cell cushion is substantially nonabsorbent of fuel. The fuel cell cushion is interposable between the inner surface of the fuel cell receiving assembly and the one or more fuel cells to cushion the one or more fuel cells from damage.