Patents by Inventor Jiangtian Cheng

Jiangtian Cheng has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 12220890
    Abstract: A method of fabricating a solid laminate stringer on a composite panel, including unspooling one or more composite layers onto the composite panel; compacting the one or more composite layers unspooled onto the composite panel; cutting the one or more composite layers unspooled onto the composite panel; and curing the one or more composite layers unspooled onto the composite panel, wherein the one or more composite layers are unspooled continuously along a length corresponding to a length of the solid laminate stringer.
    Type: Grant
    Filed: February 18, 2020
    Date of Patent: February 11, 2025
    Assignee: THE BOEING COMPANY
    Inventor: Jiangtian Cheng
  • Publication number: 20240373668
    Abstract: A multifunctional composite panel and a system for fabricating the multifunctional composite panel are disclosed. The multifunctional composite panel may include a plurality of structural layers and a plurality of photovoltaic layers disposed adjacent the plurality of structural layers. The structural layers may include a plurality of alternating layers where each of the alternating layers includes a first layer and a second layer. The first layer may include one or more polymers and the second layer may include one or more inorganic materials. The system for fabricating the multifunctional composite panel may include a based configured to support the multifunctional composite panel and a plurality of application heads disposed proximal the based and configured to form layers of the multifunctional composite panel.
    Type: Application
    Filed: July 19, 2024
    Publication date: November 7, 2024
    Applicant: The Boeing Company
    Inventors: Jiangtian Cheng, Paul S. Nordman, Hojun Yoon, Xiaobo Zhang
  • Patent number: 12089435
    Abstract: A multifunctional composite panel and a system for fabricating the multifunctional composite panel are disclosed. The multifunctional composite panel may include a plurality of structural layers and a plurality of photovoltaic layers disposed adjacent the plurality of structural layers. The structural layers may include a plurality of alternating layers where each of the alternating layers includes a first layer and a second layer. The first layer may include one or more polymers and the second layer may include one or more inorganic materials. The system for fabricating the multifunctional composite panel may include a based configured to support the multifunctional composite panel and a plurality of application heads disposed proximal the based and configured to form layers of the multifunctional composite panel.
    Type: Grant
    Filed: January 11, 2021
    Date of Patent: September 10, 2024
    Assignee: THE BOEING COMPANY
    Inventors: Jiangtian Cheng, Paul S. Nordman, Hojun Yoon, Xiaobo Zhang
  • Patent number: 11572148
    Abstract: Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.
    Type: Grant
    Filed: June 4, 2018
    Date of Patent: February 7, 2023
    Assignee: THE BOEING COMPANY
    Inventor: Jiangtian Cheng
  • Publication number: 20220388625
    Abstract: A method for producing a window assembly includes producing a structural panel. Producing the structural panel includes depositing one or more structural reinforcement layers. Each of the one or more structural reinforcement layers includes a plurality of nanolaminated layers. The nanolaminated layers include Al2O3, SiO2, graphene, or a combination thereof. Producing the structural panel also includes depositing a structural transparent polymer layer on the one or more structural reinforcement layers. The structural transparent polymer layer includes a transparent thermoplastic material.
    Type: Application
    Filed: August 17, 2022
    Publication date: December 8, 2022
    Applicant: The Boeing Company
    Inventors: Jiangtian Cheng, Paul S. Nordman
  • Patent number: 11453474
    Abstract: One piece, multifunctional window assemblies for use in vehicles, equipment, or structures and methods for making them is provided. The disclosed window assembly can include a protection panel and a structural panel each formed of a plurality of nanolaminated layers. The nanolaminated window assembly is self-supporting and does not need a frame. For particular applications, such as in an aircraft, the one piece, multifunctional, nanolaminated window can be directly attached to the fuselage to provide load bearing capability, a larger window area, impact protection, ice buildup prevention, and/or electromagnetic effect protection.
    Type: Grant
    Filed: May 2, 2019
    Date of Patent: September 27, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Jiangtian Cheng, Paul S. Nordman
  • Patent number: 11325339
    Abstract: In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The tips of the plurality of drop-off plies are arranged in a monotonically-inward pattern.
    Type: Grant
    Filed: January 14, 2021
    Date of Patent: May 10, 2022
    Assignee: The Boeing Company
    Inventor: Jiangtian Cheng
  • Patent number: 11325689
    Abstract: In an example, a composite stringer assembly includes a composite stringer, a radius filler, and an overwrap layer. The composite stringer includes: (i) a skin flange configured to be coupled to a support structure, (ii) a web, (iii) a lower corner portion of the composite stringer extending from the skin flange to the web, and (iv) an inner surface of the composite stringer extending along the skin flange, the lower corner portion, and the web. The radius filler includes a first surface coupled to the inner surface at the lower corner portion, a second surface configured to couple to the support structure, and a third surface extending between the first surface and the second surface. The overwrap layer is coupled to the inner surface at the web, the third surface of the radius filler, and the support structure.
    Type: Grant
    Filed: May 9, 2019
    Date of Patent: May 10, 2022
    Assignee: The Boeing Company
    Inventor: Jiangtian Cheng
  • Patent number: 11325688
    Abstract: In an example, a composite stringer is described. The composite stringer includes a skin flange having a first gage, a top flange having a second gage, and a web having a third gage and extending between the skin flange and the top flange. The skin flange is configured to be coupled to a support structure. The support structure includes at least one of a skin of a vehicle or a base charge. The second gage of the top flange is greater than the first gage of the skin flange and the third gage of the web. The skin flange, the top flange, and the web include a plurality of plies of composite material.
    Type: Grant
    Filed: May 9, 2019
    Date of Patent: May 10, 2022
    Assignee: The Boeing Company
    Inventor: Jiangtian Cheng
  • Patent number: 11318705
    Abstract: A composite panel includes a plurality of segments, wherein each segment includes a plurality of reinforcement plies such as carbon fiber plies. Collimated fiber bands (e.g., carbon fibers) within each reinforcement ply are oriented in a single direction, which can be, for example, 0°, 45°, 90°, and ?45°. Each segment can include a stack of reinforcement plies, wherein the collimated fiber bands of each reinforcement ply are oriented in one of these directions. The orientations of the collimated fiber bands that form the reinforcement plies in a stack determine a stiffness of the stack and the segment that includes the stack. The stiffness of each segment is controlled to reduce a stiffness mismatch between adjacent segments that form the composite panel, thereby reducing separation of the segments during use.
    Type: Grant
    Filed: August 26, 2019
    Date of Patent: May 3, 2022
    Assignee: THE BOEING COMPANY
    Inventor: Jiangtian Cheng
  • Patent number: 11242127
    Abstract: In an example, a composite stringer is described. The composite stringer includes a composite stringer and a base flange. The composite stringer includes a top flange, a first skin flange and a second skin flange configured to be coupled to a support structure, a first web extending between the first skin flange and a first side of the top flange, and a second web extending between the second skin flange and a second side of the top flange. The support structure includes at least one of a skin of a vehicle or a base charge. The base flange includes a bottom surface extending between the first skin flange and the second skin flange. The bottom surface of the base flange is configured to be coupled to the support structure. The base flange also includes a top surface extending between the first web and the second web.
    Type: Grant
    Filed: April 22, 2020
    Date of Patent: February 8, 2022
    Assignee: The Boeing Company
    Inventor: Jiangtian Cheng
  • Publication number: 20210331780
    Abstract: In an example, a composite stringer is described. The composite stringer includes a composite stringer and a base flange. The composite stringer includes a top flange, a first skin flange and a second skin flange configured to be coupled to a support structure, a first web extending between the first skin flange and a first side of the top flange, and a second web extending between the second skin flange and a second side of the top flange. The support structure includes at least one of a skin of a vehicle or a base charge. The base flange includes a bottom surface extending between the first skin flange and the second skin flange. The bottom surface of the base flange is configured to be coupled to the support structure. The base flange also includes a top surface extending between the first web and the second web.
    Type: Application
    Filed: April 22, 2020
    Publication date: October 28, 2021
    Inventor: Jiangtian Cheng
  • Publication number: 20210252817
    Abstract: A method of fabricating a solid laminate stringer on a composite panel, including unspooling one or more composite layers onto the composite panel; compacting the one or more composite layers unspooled onto the composite panel; cutting the one or more composite layers unspooled onto the composite panel; and curing the one or more composite layers unspooled onto the composite panel, wherein the one or more composite layers are unspooled continuously along a length corresponding to a length of the solid laminate stringer.
    Type: Application
    Filed: February 18, 2020
    Publication date: August 19, 2021
    Applicant: The Boeing Company
    Inventor: Jiangtian Cheng
  • Patent number: 11085111
    Abstract: A method for fabricating a structural part is disclosed. The method can include forming a plurality of layers on a base of a system having one or more application heads. Forming the plurality of layers can include forming alternating layers of a first material and a second material. Forming the alternating layers can include forming a first layer from the first material, and forming a second layer adjacent the first layer from the second material. The plurality of layers can form the structural part, and one or more dimensions of the structural part can be greater than or equal to about 0.05 cm.
    Type: Grant
    Filed: October 11, 2018
    Date of Patent: August 10, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Paul S. Nordman, Jiangtian Cheng
  • Patent number: 11052617
    Abstract: A method of fabricating a plank stringer for use in an aircraft includes grouping a plurality of stacked plies of reinforcing material into a plurality of charges, where each charge in the plurality of charges includes a substack of plies. The method also includes grouping the plurality of charges into two or more groups such that, for each charge in a given group, a respective substack of plies includes a sequence of orientation angles with respect to a longitudinal axis of the plank stringer corresponding to the given group. The method also includes laying up each group of charges as a continuous blanket of plies, where each continuous blanket of plies includes the respective substack of plies for each charge in the respective group. The method also includes cutting each continuous blanket of plies into the respective group of charges and stacking the plurality of charges to form the plank stringer.
    Type: Grant
    Filed: November 1, 2018
    Date of Patent: July 6, 2021
    Assignee: The Boeing Company
    Inventors: Scott M. Spencer, Jessica R. Hughes, Jae Dong Hwang, Joseph L. Sweetin, Kanna M. Pham, Jaime C. Garcia, Gregory P. Freed, Frederick T. Calkins, Cynthia G. Feng, Jiangtian Cheng
  • Publication number: 20210162697
    Abstract: In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The tips of the plurality of drop-off plies are arranged in a monotonically-inward pattern.
    Type: Application
    Filed: January 14, 2021
    Publication date: June 3, 2021
    Inventor: Jiangtian Cheng
  • Publication number: 20210135163
    Abstract: A multifunctional composite panel and a system for fabricating the multifunctional composite panel are disclosed. The multifunctional composite panel may include a plurality of structural layers and a plurality of photovoltaic layers disposed adjacent the plurality of structural layers. The structural layers may include a plurality of alternating layers where each of the alternating layers includes a first layer and a second layer. The first layer may include one or more polymers and the second layer may include one or more inorganic materials. The system for fabricating the multifunctional composite panel may include a based configured to support the multifunctional composite panel and a plurality of application heads disposed proximal the based and configured to form layers of the multifunctional composite panel.
    Type: Application
    Filed: January 11, 2021
    Publication date: May 6, 2021
    Applicant: The Boeing Company
    Inventors: Jiangtian Cheng, Paul S. Nordman, Hojun Yoon, Xiaobo Zhang
  • Patent number: 10988229
    Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.
    Type: Grant
    Filed: April 23, 2020
    Date of Patent: April 27, 2021
    Assignee: The Boeing Company
    Inventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
  • Publication number: 20210060894
    Abstract: A composite panel includes a plurality of segments, wherein each segment includes a plurality of reinforcement plies such as carbon fiber plies. Collimated fiber bands (e.g., carbon fibers) within each reinforcement ply are oriented in a single direction, which can be, for example, 0°, 45°, 90°, and ?45°. Each segment can include a stack of reinforcement plies, wherein the collimated fiber bands of each reinforcement ply are oriented in one of these directions. The orientations of the collimated fiber bands that form the reinforcement plies in a stack determine a stiffness of the stack and the segment that includes the stack. The stiffness of each segment is controlled to reduce a stiffness mismatch between adjacent segments that form the composite panel, thereby reducing separation of the segments during use.
    Type: Application
    Filed: August 26, 2019
    Publication date: March 4, 2021
    Applicant: The Boeing Company
    Inventor: Jiangtian Cheng
  • Patent number: 10919256
    Abstract: In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The tips of the plurality of drop-off plies are arranged in a monotonically-inward pattern.
    Type: Grant
    Filed: May 9, 2019
    Date of Patent: February 16, 2021
    Assignee: The Boeing Company
    Inventor: Jiangtian Cheng