公开(公告)号：US09709443B2

公开(公告)日：2017-07-18

申请号：US14961494

申请日：2015-12-07

Applicant: THE BOEING COMPANY

Inventor： Tyler M. Holmes ,  Gary E. Georgeson ,  Jeffrey G. Thompson

IPC: G02F1/01 ,  G01J5/10 ,  G01J5/00

CPC classification number: G01J5/10 ,  G01J2005/0077 ,  G01J2005/0081 ,  G01N25/72 ,  G06T7/0004 ,  G06T2207/10048 ,  G06T2207/30108

Abstract: Method and apparatus for detecting defects in a laminate of uncured, compacted composite sheets. After a number of plies of composite sheets are arranged and compacted, a burst of heat energy is applied to a top surface of the laminate and a digital thermographic camera captures images of the top surface. A computer processor measures heat characteristics of the top surface to identify regions of the top surface with different heat characteristics. Such different areas are identified as regions that include a defect. The defect regions can be repaired by applying additional compaction and/or by removing at least a portion of some layers, removing any foreign object debris, replacing the layers, and compacting the replaced layers. After any defects are addressed, the laminate is cured.

公开(公告)号：US09645012B2

公开(公告)日：2017-05-09

申请号：US14827788

申请日：2015-08-17

Applicant: The Boeing Company

Inventor： Bobby J. Marsh ,  Gary E. Georgeson ,  Jeffrey R. Thompson

IPC: G01J5/10 ,  G06T7/00 ,  G01S17/06 ,  G01D5/347 ,  G06T7/40 ,  H04N5/225 ,  H04N5/33 ,  H04N5/247 ,  G06K9/00 ,  G01J5/00

CPC classification number: G01J5/10 ,  G01D5/347 ,  G01J5/026 ,  G01J5/0846 ,  G01J5/089 ,  G01J2005/0077 ,  G01J2005/0081 ,  G01N25/72 ,  G01S17/023 ,  G01S17/06 ,  G01S17/66 ,  G06K9/00671 ,  G06T7/0004 ,  G06T7/0006 ,  G06T7/40 ,  G06T7/73 ,  G06T2200/32 ,  G06T2207/10048 ,  G06T2207/20221 ,  G06T2207/30108 ,  G06T2207/30164 ,  H04N5/2256 ,  H04N5/247 ,  H04N5/33 ,  H04N5/332

Abstract: Systems and methods for infrared thermographic inspection of large-scale composite structures such as sections of an aircraft fuselage. Optical metrology is used to precisely locate the infrared images relative to a three-dimensional coordinate system of the composite structure. The optical metrology may comprise laser tracking or photogrammetry or both. In some embodiments, the optical metrology comprises laser tracking merged with photogrammetry. Once the infrared images have been precisely located relative to the coordinate system of the composite structure, structural data about the composite structure (e.g., thickness data) can be retrieved from a database containing a three-dimensional model of the composite structure. In the case of thermographic porosity measurements, the infrared imaging data can be correlated with thickness data to determine the porosity of the composite structure in the inspection area.

公开(公告)号：US09575033B1

公开(公告)日：2017-02-21

申请号：US14049974

申请日：2013-10-09

Applicant: The Boeing Company

Inventor： Gary E. Georgeson ,  William Joseph Tapia ,  Michael D. Fogarty ,  Hong Hue Tat ,  Richard H. Bossi ,  Robert L. Carlsen

IPC: G01N29/04 ,  G01N17/00 ,  G01N29/07

CPC classification number: G01N29/07 ,  G01N29/11 ,  G01N2291/011 ,  G01N2291/015 ,  G01N2291/0231 ,  G01N2291/044 ,  G01N2291/102 ,  G01N2291/106

Abstract: A method and apparatus for evaluating an object having a wrinkle. Energy is sent into the object at a plurality of locations using an array of transmitting elements. Reflected energy is received at an array of receiving elements in response to a portion of the energy being reflected off a plurality of layers in the object. A three-dimensional model of the wrinkle in the object is created based on the reflected energy received at the array of receiving elements.

Abstract translation: 一种用于评估具有皱纹的物体的方法和装置。 使用发射元件的阵列在多个位置将能量发送到物体。 响应于能量的一部分被反射离开物体中的多个层，在接收元件的阵列处接收反射能量。 基于在接收元件阵列处接收到的反射能量，创建对象中皱纹的三维模型。

公开(公告)号：US20170030864A1

公开(公告)日：2017-02-02

申请号：US14811735

申请日：2015-07-28

Applicant: The Boeing Company

Inventor： Gary E. Georgeson ,  Tyler M. Holmes ,  Jeffrey R. Kollgaard

IPC: G01N29/04 ,  G01N29/44

CPC classification number: G01N29/041 ,  G01N29/07 ,  G01N29/11 ,  G01N29/2468 ,  G01N29/28 ,  G01N29/30 ,  G01N29/4445 ,  G01N2291/0231 ,  G01N2291/0234 ,  G01N2291/106 ,  G01N2291/2694

Abstract: Example systems and methods for non-destructive evaluation of depressions on a surface of an object are provided. One example system includes a measurement apparatus having a two-dimensional ultrasonic transducer array, a delay line material, a sealing member position such that the sealing member forms a cavity between the delay line material and a surface of the object, and a liquid inlet for injecting a liquid into the cavity. The example system also includes a processor configured to determine, using ultrasonic signals received from the two-dimensional ultrasonic transducer array, at least one property of a depression such as a dent on the surface of an object. The example system may also be configured to provide an output that is indicative of whether the at least one property of the depression satisfies a predetermined criterion. Another example system includes a compressible elastomeric delay line material that conforms to a surface of an object.

Abstract translation: 提供了用于对物体表面上的凹陷进行非破坏性评估的示例系统和方法。 一个示例性系统包括具有二维超声波换能器阵列，延迟线材料，密封构件位置，使得密封构件在延迟线材料和物体表面之间形成空腔的测量装置，以及用于 将液体注入空腔。 示例性系统还包括处理器，其被配置为使用从二维超声换能器阵列接收的超声波信号来确定物体表面上的诸如凹陷之类的凹陷的至少一种性质。 示例性系统还可以被配置为提供指示抑郁症的至少一个属性是否满足预定标准的输出。 另一示例性系统包括符合物体表面的可压缩弹性体延迟线材料。

公开(公告)号：US20170016861A1

公开(公告)日：2017-01-19

申请号：US14707403

申请日：2015-05-08

Applicant: The Boeing Company

Inventor： Hong H. Tat ,  Gary E. Georgeson ,  Richard H. Bossi

IPC: G01N29/11 ,  G01N15/08

CPC classification number: G01N29/11 ,  G01N15/08 ,  G01N15/088 ,  G01N29/4427 ,  G01N29/4472 ,  G01N2291/015 ,  G01N2291/0231

Abstract: A system and method is disclosed for generating ultrasound results having a simulated level of porosity for a composite. Data for a set of composite coupons having different levels of porosity is obtained. An attenuation distribution function is fit to a back wall signal generated from the data for each coupon and a library of echo patterns based on such data is created. An interpolated attenuation distribution function is calculated based on an interpolation of two stored attenuation distribution functions having the closest porosity values to the selected level. A main attenuation distribution function value is assigned to one portion of a selected region in a zero porosity coupon and attenuation distribution functions values within a predetermined percentage of the main attenuation distribution function are assigned to other portions of the region. Waveforms associated with the portions are modified based on such values and selected echo patterns from the library.

Abstract translation: 公开了一种用于产生具有复合材料的模拟孔隙度水平的超声波结果的系统和方法。 获得具有不同孔隙度水平的一组复合试样的数据。 衰减分布函数适合于从每个优惠券的数据生成的后壁信号，并且创建基于这样的数据的回波图案库。 基于具有最接近孔隙度值的两个存储的衰减分布函数的插值到所选择的电平来计算内插衰减分布函数。 将主衰减分布函数值分配给零孔隙率优惠券中的所选区域的一部分，并且将主衰减分布函数的预定百分比内的衰减分布函数值分配给该区域的其它部分。 基于这些值和从库中选择的回波模式来修改与这些部分相关联的波形。

公开(公告)号：US09464754B1

公开(公告)日：2016-10-11

申请号：US15181516

申请日：2016-06-14

Applicant: The Boeing Company

Inventor： James J. Troy ,  Scott W. Lea ,  Gary E. Georgeson ,  Karl Edward Nelson ,  Daniel James Wright

IPC: G06F19/00 ,  F16M11/18 ,  F16M11/42 ,  G05D1/02 ,  G01N29/22 ,  G01N29/265 ,  G01N29/28

CPC classification number: F16M11/18 ,  B66C13/48 ,  B66C23/72 ,  F16M11/24 ,  F16M11/42 ,  G01N29/225 ,  G01N29/265 ,  G01N29/28 ,  G05D1/0276 ,  G05D2201/0207 ,  Y10S901/01

Abstract: A system comprising a multi-functional boom subsystem integrated with a holonomic-motion boom base platform. The boom base platform may comprise: Mecanum wheels with independently controlled motors; a pair of sub-platforms coupled by a roll-axis pivot to maintain four-wheel contact with the ground surface; and twist reduction mechanisms to minimize any yaw-axis twisting torque exerted on the roll-axis pivot. A computer with motion control software may be embedded on the boom base platform. The motion control function can be integrated with a real-time tracking system. The motion control computer may have multiple platform motion control modes: (1) a path following mode in which the boom base platform matches the motion path of the surface crawler (i.e., integration with crawler control); (2) a reactive mode in which the boom base platform moves based on the pan and tilt angles of the boom arm; and (3) a collision avoidance mode using sensors distributed around the perimeter of the boom base platform to detect obstacles.

公开(公告)号：US09443300B2

公开(公告)日：2016-09-13

申请号：US14486461

申请日：2014-09-15

Applicant: THE BOEING COMPANY

Inventor： Gary E. Georgeson ,  Anish Poudel ,  Tsuchin Chu ,  James A. Grossnickle

IPC: G06T7/00

CPC classification number: G06T7/001 ,  G06K9/036 ,  G06K9/6201 ,  G06T7/0008 ,  G06T2207/30108

Abstract: A method for analyzing a bondline in a structure is provided. The method includes obtaining, from a first side of the structure, by at least one computing device, at least one first internal image of the structure that includes at least a first pattern associated with the bondline, wherein the structure is in a pre-loaded state and obtaining, from the first side of the structure, by the at least one computing device, at least one second internal image of the structure that includes at least the first pattern, wherein the structure is in a loaded state. Additionally, the method includes comparing, by the at least one computing device, the at least one first internal image with the at least one second internal image, and determining, by the at least one computing device, at least one stress and/or strain-related property of the bondline based on the comparison. The method additionally includes predicting an estimated life of the bondline, whereby the estimated life provides a valuable tool for optimization of maintenance effort and enabling cost-optimal maintenance decisions.

Abstract translation: 提供了一种用于分析结构中的粘结线的方法。 所述方法包括从所述结构的第一侧通过至少一个计算设备获得所述结构的至少一个第一内部图像，所述至少一个第一内部图像至少包括与所述粘合线相关联的第一图案，其中所述结构处于预加载 并且从所述结构的第一侧由所述至少一个计算设备获得至少包括所述第一图案的所述结构的至少一个第二内部图像，其中所述结构处于加载状态。 另外，该方法包括通过至少一个计算设备将至少一个第一内部图像与至少一个第二内部图像进行比较，以及由至少一个计算设备确定至少一个应力和/或应变 基于比较的绑定线的相关属性。 该方法还包括预测粘合线的估计寿命，由此估计寿命为优化维护工作提供了有价值的工具，并且能够实现成本最优化的维护决策。

公开(公告)号：US20160239013A1

公开(公告)日：2016-08-18

申请号：US14620588

申请日：2015-02-12

Applicant: THE BOEING COMPANY

Inventor： James J. Troy ,  Barry A. Fetzer ,  Scott W. Lea ,  Gary E. Georgeson

IPC: G05B19/402 ,  B25J9/16 ,  G05B15/02

CPC classification number: G05B19/402 ,  B25J9/1607 ,  B25J9/1664 ,  B25J9/1692 ,  B25J9/1697 ,  G05B15/02 ,  G05B2219/31076 ,  Y10S901/09

Abstract: Systems and methods for calibrating the location of an end effector-carrying apparatus relative to successive workpieces before the start of a production manufacturing operation. The location calibration is performed using a positioning system. These disclosed methodologies allow an operator to program (or teach) the robot motion path once and reuse that path for subsequent structures by using relative location feedback from a measurement system to adjust the position and orientation offset of the robot relative to the workpiece. When each subsequent workpiece comes into the robotic workcell, its location (i.e., position and orientation) relative to the robot may be different than the first workpiece that was used when developing the initial program. The disclosed systems and methods can also be used to compensate for structural differences between workpieces intended to have identical structures.

Abstract translation: 用于在生产制造操作开始之前校准末端执行器承载装置相对于连续工件的位置的系统和方法。 位置校准使用定位系统进行。 这些公开的方法允许操作者编程（或教导）机器人运动路径一次，并通过使用来自测量系统的相对位置反馈重新使用该路径用于后续结构，以调整机器人相对于工件的位置和取向偏移。 当每个随后的工件进入机器人工作单元时，其相对于机器人的位置（即位置和方位）可以不同于在开发初始程序时使用的第一个工件。 所公开的系统和方法也可用于补偿旨在具有相同结构的工件之间的结构差异。

公开(公告)号：US20160176177A1

公开(公告)日：2016-06-23

申请号：US15059321

申请日：2016-03-03

Applicant: The Boeing Company

Inventor： Gary E. Georgeson ,  Kenneth H. Griess

IPC: B32B37/12 ,  B32B37/10

CPC classification number: B29C73/14 ,  B29K2105/08 ,  B29K2105/256 ,  B29L2031/3082 ,  B32B3/266 ,  B32B7/12 ,  B32B27/08 ,  B32B37/10 ,  B32B37/1018 ,  B32B37/12 ,  B32B2305/72 ,  B32B2556/00 ,  B32B2605/18 ,  Y10T428/24314

Abstract: A method for patching a hole in a composite parent structure. The method comprises: inserting an insert in the hole; placing a composite patch having a multiplicity of curved flexible members on one side of the composite parent structure in a position where a central portion of the composite patch overlies the insert and the flexible members confront opposing portions of the composite parent structure providing adhesive between the composite patch, the insert, and the composite parent structure; pressing the composite patch against the composite parent structure with sufficient pressure to force the flexible members to conform to the shape of the composite parent structure; and while the flexible members are in a stressed state, curing the adhesive in a manner that causes the flexible members to bond to the parent structure.

Abstract translation: 一种用于在复合母体结构中修补孔的方法。 该方法包括：将插入件插入孔中; 将具有多个弯曲柔性构件的复合贴片放置在复合母体结构的一侧上，其中复合贴片的中心部分覆盖插入件，并且柔性构件面对复合母体结构的相对部分，在复合母体结构之间提供粘合剂 补丁，插入和复合父结构; 以足够的压力将复合贴片压靠在复合母体结构上，以迫使柔性构件符合复合母体结构的形状; 并且当柔性构件处于应力状态时，以使柔性构件结合到母体结构的方式固化粘合剂。

公开(公告)号：US09372177B2

公开(公告)日：2016-06-21

申请号：US13840980

申请日：2013-03-15

Applicant: The Boeing Company

Inventor： Gary E. Georgeson ,  Megan N. Watson ,  Morteza Safai

IPC: G01N21/88 ,  G01N31/22 ,  C09D5/26 ,  G01K11/20 ,  G01N21/91 ,  G01N21/84

CPC classification number: G01N31/229 ,  C09D5/26 ,  G01K11/20 ,  G01N21/91 ,  G01N2021/8472

Abstract: A method of detecting high-temperature exposure of a composite may include applying a composition comprising an adduct suitable for detecting heat and/or mechanical stress in a composite, wherein the adduct reverts to first and second adduct components after exposure of the composition to a temperature of from about 190° C. to about 260° C. to a surface of the composite; exposing the surface to which the composition has been applied to ultraviolet light; and measuring fluorescence of the composition.

Abstract translation: 检测复合材料的高温暴露的方法可以包括施加包含适合于在复合材料中检测热和/或机械应力的加合物的组合物，其中在将组合物暴露于温度之后，加合物回复到第一和第二加合物组分 约190℃至约260℃的温度; 将已经施加组合物的表面暴露于紫外光下; 并测量组合物的荧光。