公开(公告)号：US20220187249A1

公开(公告)日：2022-06-16

申请号：US17538008

申请日：2021-11-30

Applicant: The Boeing Company

Inventor： William Paul Motzer ,  Eddie Thelonious Boyd ,  Sadie Lee Fieni ,  David A. Lilienthal

IPC: G01N29/04 ,  G01N21/3563 ,  G01N29/44

Abstract: Non-destructive test systems and associated methods. A non-destructive test system includes an infrared thermography assembly and an ultrasonic test assembly for testing a test piece. The infrared thermography assembly may include one or more thermography sensor modules and a thermography test controller. The ultrasonic test assembly may include one or more ultrasonic sensor subassemblies with respective excitation modules and respective detector modules and an ultrasonic test controller. Each excitation module may be configured to produce a respective ultrasonic beam within the test piece, and each detector module may be configured to detect a respective reflected vibration of the test piece. In some examples, a method of performing a non-destructive test on a test piece includes testing an infrared test region of the test piece with an infrared thermography assembly and testing an ultrasonic test region of the test piece with an ultrasonic test assembly.

公开(公告)号：US20190381700A1

公开(公告)日：2019-12-19

申请号：US16010905

申请日：2018-06-18

Applicant: The Boeing Company

Inventor： Kristofer L. Peterson ,  Eileen E. Miller ,  Mark Allen Ulvin ,  Ronald Leroy McGhee ,  David A. Lilienthal

IPC: B29C35/02 ,  B32B3/08 ,  B32B7/08 ,  B32B27/08 ,  B29C70/54 ,  B32B7/12

Abstract: A method for fabricating a composite structure is provided. A first number of layers of composite material is laid up to form a first set of stiffeners. A second number of layers of composite material is laid up to form a panel. The first set of stiffeners is associated with a first side of the panel. A pre-cured composite strip is positioned on a second side of the panel, opposite the first side. A third number of layers of composite material is laid up on the second side of the panel to form a second set of stiffeners running perpendicular to the first set of stiffeners. The pre-cured composite lies at an intersection between one of the first set of stiffeners and one of the second set of stiffeners. All the layers of composite material are co-cured to form the composite structure.

公开(公告)号：US11639914B2

公开(公告)日：2023-05-02

申请号：US17538008

申请日：2021-11-30

Applicant: The Boeing Company

Inventor： William Paul Motzer ,  Eddie Thelonious Boyd ,  Sadie Lee Fieni ,  David A. Lilienthal

IPC: G01N29/44 ,  G01N29/04 ,  G01N21/3563

Abstract: Non-destructive test systems and associated methods. A non-destructive test system includes an infrared thermography assembly and an ultrasonic test assembly for testing a test piece. The infrared thermography assembly may include one or more thermography sensor modules and a thermography test controller. The ultrasonic test assembly may include one or more ultrasonic sensor subassemblies with respective excitation modules and respective detector modules and an ultrasonic test controller. Each excitation module may be configured to produce a respective ultrasonic beam within the test piece, and each detector module may be configured to detect a respective reflected vibration of the test piece. In some examples, a method of performing a non-destructive test on a test piece includes testing an infrared test region of the test piece with an infrared thermography assembly and testing an ultrasonic test region of the test piece with an ultrasonic test assembly.

公开(公告)号：US10780611B2

公开(公告)日：2020-09-22

申请号：US16010905

申请日：2018-06-18

Applicant: The Boeing Company

Inventor： Kristofer L. Peterson ,  Eileen E. Miller ,  Mark Allen Ulvin ,  Ronald Leroy McGhee ,  David A. Lilienthal

IPC: B29C35/02 ,  B29C70/54 ,  B32B3/08 ,  B32B7/08 ,  B32B7/12 ,  B32B27/08 ,  B29C70/30 ,  B29L31/30

Abstract: A method for fabricating a composite structure is provided. A first number of layers of composite material is laid up to form a first set of stiffeners. A second number of layers of composite material is laid up to form a panel. The first set of stiffeners is associated with a first side of the panel. A pre-cured composite strip is positioned on a second side of the panel, opposite the first side. A third number of layers of composite material is laid up on the second side of the panel to form a second set of stiffeners running perpendicular to the first set of stiffeners. The pre-cured composite lies at an intersection between one of the first set of stiffeners and one of the second set of stiffeners. All the layers of composite material are co-cured to form the composite structure.