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).

  • Publication number: 20200247523
    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: Application
    Filed: April 23, 2020
    Publication date: August 6, 2020
    Inventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
  • Patent number: 10723436
    Abstract: Methods and apparatus to increase strength and toughness of aircraft structural components are disclosed. An example apparatus includes a composite structure of an aircraft, a stringer coupled to the composite structure of the aircraft, where the stringer and the composite structure form a stringer radius gap. A gap filler is disposed in the stringer radius gap, which includes chopped fibers randomly distributed throughout an entire volume of the gap filler.
    Type: Grant
    Filed: August 14, 2017
    Date of Patent: July 28, 2020
    Assignee: The Boeing Company
    Inventors: Jiangtian Cheng, Forouzan Behzadpour
  • Patent number: 10689085
    Abstract: Stringer stiffened composite panels having improved pull-off strength are disclosed. An example stringer includes a first surface, a second surface, an edge, and a chamfer. The second surface is located opposite the first surface and is to be coupled to a composite structure of an aircraft. The edge extends from the second surface toward the first surface. The chamfer extends from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
    Type: Grant
    Filed: March 6, 2018
    Date of Patent: June 23, 2020
    Assignee: The Boeing Company
    Inventors: Forouzan Behzadpour, Jiangtian Cheng
  • Patent number: 10669005
    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 also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: June 2, 2020
    Assignee: The Boeing Company
    Inventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
  • Publication number: 20200139646
    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: Application
    Filed: November 1, 2018
    Publication date: May 7, 2020
    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: 20200119307
    Abstract: A method for fabricating a multifunctional composite panel is disclosed. The method can include forming a plurality of structural layers, and forming a plurality of photovoltaic layers adjacent the plurality of structural layers. Forming the plurality of structural layers can include forming alternating layers of a conductive organic material and an inorganic material. Forming the alternating layers can include forming a first layer from the conductive organic material, and forming a second layer adjacent the first layer from the inorganic material. The multifunctional composite panel can have a thickness of from about 1 mm to about 30 mm.
    Type: Application
    Filed: October 11, 2018
    Publication date: April 16, 2020
    Inventors: Jiangtian Cheng, Paul S. Nordman, Hojun Yoon, Xiaobo Zhang
  • Publication number: 20200115793
    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: Application
    Filed: October 11, 2018
    Publication date: April 16, 2020
    Inventors: Paul S. Nordman, Jiangtian Cheng
  • Publication number: 20190367145
    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: Application
    Filed: June 4, 2018
    Publication date: December 5, 2019
    Inventor: Jiangtian Cheng
  • Publication number: 20190263496
    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 also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.
    Type: Application
    Filed: February 27, 2018
    Publication date: August 29, 2019
    Inventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
  • Publication number: 20190047677
    Abstract: Methods and apparatus to increase strength and toughness of aircraft structural components are disclosed. An example apparatus includes a composite structure of an aircraft, a stringer coupled to the composite structure of the aircraft, where the stringer and the composite structure form a stringer radius gap. A gap filler is disposed in the stringer radius gap, which includes chopped fibers randomly distributed throughout an entire volume of the gap filler.
    Type: Application
    Filed: August 14, 2017
    Publication date: February 14, 2019
    Inventors: Jiangtian Cheng, Forouzan Behzadpour
  • Publication number: 20190047676
    Abstract: Stringer stiffened composite panels having improved pull-off strength are disclosed. An example stringer includes a first surface, a second surface, an edge, and a chamfer. The second surface is located opposite the first surface and is to be coupled to a composite structure of an aircraft. The edge extends from the second surface toward the first surface. The chamfer extends from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
    Type: Application
    Filed: March 6, 2018
    Publication date: February 14, 2019
    Inventors: Forouzan Behzadpour, Jiangtian Cheng
  • Patent number: 9856008
    Abstract: A composite structure is provided. The composite structure includes a first stiffener, a second stiffener, and an intermediate structure positioned between the first and second stiffeners such that the first stiffener is coupled to a first side of the intermediate structure, and such that the second stiffener is coupled to a second opposing side of the intermediate structure. A first radius gap is defined at least partially between the first stiffener and the intermediate structure, and a second radius gap is defined at least partially between the second stiffener and the intermediate structure.
    Type: Grant
    Filed: May 19, 2014
    Date of Patent: January 2, 2018
    Assignee: The Boeing Company
    Inventors: Jiangtian Cheng, Derek Paul Vetter, Patrick Alan Woodard, Forouzan Behzadpour
  • Publication number: 20160144943
    Abstract: A composite structure is provided. The composite structure includes a first stiffener, a second stiffener, and an intermediate structure positioned between the first and second stiffeners such that the first stiffener is coupled to a first side of the intermediate structure, and such that the second stiffener is coupled to a second opposing side of the intermediate structure. A first radius gap is defined at least partially between the first stiffener and the intermediate structure, and a second radius gap is defined at least partially between the second stiffener and the intermediate structure.
    Type: Application
    Filed: May 19, 2014
    Publication date: May 26, 2016
    Applicant: The Boeing Company
    Inventors: Jiangtian Cheng, Derek Paul Vetter, Patrick Alan Woodard, Forouzan Behzadpour
  • Publication number: 20030134705
    Abstract: The invention comprises a multi-ribbed belt wherein a rib tip has a concave arcuate surface disposed between substantially flat surfaces, which are in turn disposed between rib side surfaces. The substantially flat surfaces are adjacent to curved surfaces which connect to rib side surfaces. The inventive rib profile and rib compound construction significantly reduce rib tip cracking, which significantly reduces belt flex fatigue under high applied frictional torque. Further, the inventive rib profile and rib compound construction significantly reduces high localized tensile stress/strain at the rib tip and highly localized shear stress at the rib flank, thereby significantly reducing rib tip cracking and rib tear off. The inventive belt also comprises a significantly reduced contact normal force, thereby increasing an operating life of the belt.
    Type: Application
    Filed: January 13, 2003
    Publication date: July 17, 2003
    Inventor: Jiangtian Cheng