Method for analyzing fastening structure and system related thereto

Abstract

To solve a problem in which it is physically impossible during a test to accurately measure all of necessary attributes in real time at reasonable costs, in a reasonable schedule and with reasonable accuracy.SOLUTION: A method for analyzing a fastening structure includes: accessing an electric design model of the fastening structure; embedding at least one sensor element model in the electric design model; applying at least one simulation load to the electric design model; using the at least one sensor element model to monitor a measurement parameter to detect a load condition in a corresponding selection location on the basis of the at least one simulation load; and comparing the detected load condition with a predetermined measurement threshold for the monitored measurement parameter. A fastening structure management system includes a computing system, and a storage device operative to communicate with the computing system.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001]

[0001] The present disclosure relates generally to analysis of fastened structures, and more particularly to analysis of electronic design models using simulated loads and embedded sensor models to measure loading conditions in conjunction with physical testing and / or validation of the design. The analysis may be applied to all levels of design, testing, and certification of product building blocks, and all aspects of the product life. Thus, the analysis may be repeated at lower level assemblies, higher level assemblies, and ultimately at the product end item. The analysis has applications not only to aircraft design, but also to other types of vehicle and transportation structures. Applications to the design of various other types of fastened structures are also envisioned. [Background technology]

[0002]

[0002] In the design of fastened structures (such as aircraft), multiple challenges arise associated with the determination of local loads and load distribution. For example, various performance characteristics (displacement, rotation, stiffness, clamp-up, damage state, etc.) in fastened assemblies undergoing thermo-mechanical testing face many challenges. Performance characteristics are typically evaluated by physical testing in closed environment chambers, but such tests inherently obscure / do not allow visual physical measurement of desired behavior. The main problem is the physical inability to accurately and currently measure all required attributes during testing at reasonable cost, schedule, and accuracy.

[0003]

[0003] Accordingly, those skilled in the art continue to engage in research and development efforts to improve techniques for testing fastener structure designs, and in particular, to develop in-situ techniques for analytically assessing the internal loading conditions of joined components (particularly the fasteners in the joint) and / or at any point between the fasteners. Summary of the Invention

[0004]

[0004] Examples of methods for analyzing fastener structures, fastener structure management systems, and analytical computing systems for analyzing fastener structures are disclosed. The following is a non-limiting list of examples of inventive subject matter according to the present disclosure, which may or may not be claimed.

[0005]

[0005] In one example, a disclosed method for analyzing a fastener structure includes: (1) accessing an electronic design model of the fastener structure, the fastener structure including at least two structural elements assembled with a plurality of fastener elements, the electronic design model including structural element parameters for each structural element and fastener parameters for each fastener element, the structural element parameters and fastener parameters representing properties and behaviors of the corresponding structural element and the corresponding fastener element in an environment to which the assembled fastener structure is expected to be exposed; and (2) embedding at least one sensor element model within the electronic design model, each sensor element model representing properties and behaviors of the at least two structural elements assembled with a plurality of fastener elements. (3) embedding at least one sensor element model in a selected location associated with a selected joint between two or more of the structural elements of the structural components, the at least one sensor element model being configured to monitor a measurement parameter at the selected location in response to application of one or more simulated loads to the electronic design model; (4) monitoring the measurement parameter using the at least one sensor element model to detect a load condition at the corresponding selected location based on the at least one simulated load; and (5) comparing the detected load condition to a predetermined measurement threshold of the monitored measurement parameter.

[0006] In one example, a fastener structure management system includes a computing system and a storage device operative to communicate with the computing system. The computing system is configured to execute a design analysis application program. The computing system executes the design analysis application program and performs the following steps: (1) accessing an electronic design model of the fastened structure from the design computing system, the fastened structure including at least two structural elements assembled by a plurality of fastener elements, the electronic design model including structural element parameters for each structural element and fastener parameters for each fastener element, the structural element parameters and fastener parameters representing properties and behaviors of the corresponding structural elements and the corresponding fastener elements in an environment to which the assembled fastened structure is expected to be exposed; and (2) embedding at least one sensor element model within the electronic design model, the sensor element parameters for each sensor element. (3) embedding at least one sensor element model at a selected location associated with a selected joint between two or more of the at least two structural elements, the at least one sensor element model being configured to monitor a measurement parameter at the selected location in response to application of one or more simulated loads to the electronic design model; (4) monitoring the measurement parameter using the at least one sensor element model to detect a load condition at the corresponding selected location based on the at least one simulated load; and (5) comparing the detected load condition to a predetermined measurement threshold of the monitored measurement parameter. is configured to execute.

[0007] In one example, a disclosed analysis computing system for analyzing a fastened structure includes at least one processor and associated memory, at least one electronic storage device, and a network interface. The at least one electronic storage device stores a design analysis application program. The network interface is operative to communicate with the at least one processor and configured to interface with a communication network. The analysis computing system performs the design analysis application program in conjunction with the at least one processor executing the design analysis application program by: (1) accessing from the design computing system via the network interface and the communication network an electronic design model of the fastened structure, the fastened structure including at least two structural elements assembled by a plurality of fastener elements, the electronic design model including structural element parameters for each structural element and fastener parameters for each fastener element, the structural element parameters and fastener parameters representing properties and behaviors of the corresponding structural elements and the corresponding fastener elements in an environment to which the assembled fastened structure is expected to be exposed; and (2) acquiring at least one sensor within the electronic design model. (3) embedding at least one sensor element model at a selected location associated with a selected junction between two or more of the at least two structural elements, the at least one sensor element model being configured to monitor a measurement parameter at the selected location in response to application of one or more simulated loads to the electronic design model; (4) applying the at least one simulated load to the electronic design model; (5) detecting a load condition at the corresponding selected location based on the at least one simulated load using the at least one sensor element model; and (6) comparing the detected load condition to a predetermined measurement threshold of the monitored measurement parameter. is configured to execute.

[0008]

[0008] Other examples of the disclosed methods for analyzing fastening structures, fastening structure management systems, and analytical computing systems for analyzing fastening structures will become apparent from the following detailed description, the accompanying drawings, and the appended claims. [Brief description of the drawings]

[0009] [Figure 1] FIG. 1 is a flow diagram of an example of a method for analyzing a fastening structure. [Diagram 2] FIG. 2 is a flow diagram of another example of a method for analyzing a fastening structure, combined with FIG. [Diagram 3] FIG. 2 is a flow diagram of yet another example of a method for analyzing a fastening structure, in combination with FIG. 1; [Figure 4] FIG. 2 is a functional block diagram of an example electronic design model. [Diagram 5] FIG. 2 is a functional block diagram of an example of a fastening structure. [Figure 6] FIG. 2 is a functional block diagram of an example of a fastening structure management system. [Figure 7] FIG. 1 is a functional block diagram of an example of an analytical computing system for analyzing a fastening structure. [Figure 8] FIG. 1 is a block diagram of an aircraft manufacturing and maintenance methodology. [Figure 9] FIG. 1 is a schematic diagram of an aircraft. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010]

[0018] With general reference to Figures 1-6 by way of example, the present disclosure is directed to methods 100, 200, 300 for analyzing a fastening structure 500. In Figures 1-3, optional features are shown as dashed blocks in the flow diagrams. Figure 2, in combination with Figure 1, discloses an example of a method 200. Figure 3, in combination with Figure 1, discloses some examples of a method 300. Figure 4 discloses an example of an electronic design model 400. Figure 5 discloses an example of a fastening structure 500.

[0011]

[0019] 1 and 4-6, in one or more examples, a method 100 (see FIG. 1) for analyzing a fastening structure 500 begins at 102 where an electronic design model 400 of the fastening structure 500 is accessed. The fastening structure 500 includes at least two structural elements 502 assembled by a plurality of fastening elements 504. The electronic design model 400 includes structural element parameters 610 for each structural element 502 and fastener parameters 612 for each fastening element 504. The structural element parameters 610 and fastener parameters 612 represent the properties and behavior of the corresponding structural elements 502 and corresponding fastener elements 504 in an environment to which the assembled fastening structure 500 is expected to be exposed. At 104, at least one sensor element model 402 is embedded within the electronic design model 400. Each sensor element model 402 is embedded at a selected location associated with a selected junction between two or more of the at least two structural elements 502. The at least one sensor element model 402 is configured to monitor a measurement parameter 614 at the selected location in response to application of one or more simulated loads 616 to the electronic design model 400. At 106, the at least one simulated load 616 is applied to the electronic design model 400. At 108, the measurement parameter 614 is monitored using the at least one sensor element model 402, and a load condition 618 at the corresponding selected location is detected based on the at least one simulated load 616. At 110, the detected load condition 618 is compared to a predetermined measurement threshold 620 of the monitored measurement parameter 614.

[0012]

[0020] In another example of the method 100, the fastening structure 500 includes three or more structural elements 502 assembled by a plurality of fastener elements 504. In yet another example of the method 100, the fastening structure 500 forms a product structure, a vehicle structure, an automotive structure, an aerial vehicle structure, an aircraft structure, a missile structure, a rocket structure, a launch structure, a satellite structure, a bridge structure, a tunnel structure, or any other suitable structure having multiple parts fastened together.

[0013]

[0021] In yet another example of the method 100, the plurality of fastener elements 504 includes a set of fastener elements 504. In this example, the at least two structural elements 502 include at least one composite structural element and at least one non-composite structural element. The at least one non-composite structural element is joined to one or more of the at least one composite structural element by the set of fastener elements 504. In a further example, the plurality of fastener elements 504 and the set of fastener elements 504 include metal fasteners, metal screws, metal machine screws, metal bolts, metal pins, metal rivets, metal nuts, metal retention mechanisms, or any other suitable fastener components, in any suitable combination. In yet another example, the at least one composite structural element includes a thermoplastic composite, a thermoset composite, a reinforced composite, a fiber reinforced composite, a carbon fiber reinforced composite, a reinforced polymer, a fiber reinforced polymer, a carbon fiber reinforced polymer, or any other suitable composite material, in any suitable combination. In yet another example, the at least one non-composite structural element comprises titanium, a titanium based metal, a titanium alloy, Ti-6Al-4V, Ti 6-4, aluminum, an aluminum based metal, an aluminum alloy, vanadium, a vanadium based metal, a vanadium alloy, paper, foam, resin, metal, additive, or any other suitable non-composite solid material in any suitable combination.

[0014]

[0022] In yet another example of the method 100, the plurality of fastener elements 504 are represented in the electronic design model 400 as a plurality of fastener element models 404. In other words, the fastener element models are modeled structural elements represented in software (such as ABAQUS® or LS-DYNA). ABAQUS® is a registered trademark of Dassault Systemes Simulia Corporation of Johnston, Rhode Island. LS-DYNA is commercially available from Ansys, Inc. of Canonsburg, Pennsylvania. In a further example, each fastener element model 404 is represented in the electronic design model 400 as any suitable combination of truss elements, beam elements, shell elements, or any other suitable finite elements.

[0015]

[0023] In another example of method 100, at least two fastener elements 502 are represented in electronic design model 400 as at least two structural element models 406. In other words, the structural element models are modeled structural elements represented in software (such as ABAQUS® or LS-DYNA). In a further example, each structural element model 406 is represented in electronic design model 400 as any suitable combination of beam elements, shell elements, solid elements, or any other suitable shaped elements. For example, electronic design model 400 may be viewed as a mesh of structural element models 406.

[0016]

[0024] In yet another example of method 100, each sensor element model 402 is represented in electronic design model 400 as any suitable combination of truss elements, beam elements, shell elements, or any other suitable fixed elements. In other words, the sensor element models are modeled structural elements that are represented in software (such as ABAQUS® or LS-DYNA).

[0017]

[0025] In yet another example of method 100, the selected location includes a selected surface location of the at least two structural elements 502, a selected interior location of the at least two structural elements 502, a selected gap location between the at least two structural elements 502, a selected overlap location of two or more of the at least two structural elements 502, or any other suitable location associated with the at least two structural elements 502.

[0018]

[0026] In yet another example of the method 100, the at least one simulated load 616 includes a simulated thermal load, a simulated hygric load, a simulated mechanical load, a simulated structural load, a simulated axial load, or any other suitable simulated load in any suitable combination. The simulated loads may be applied as a constant, cyclical, static, ambient, with a high rate of change, dynamically, shock, undulating, or any other suitable application technique.

[0019]

[0027] In another example of the method 100, the detected loading conditions 618 include a displacement condition, a rotation condition, a stiffness condition, a clamp-up condition, a deformation condition, a damage condition, or any other suitable detected loading condition in any suitable combination. Many of the detected loading conditions 618 result from the fastener structure including different types of structural elements having different thermal expansion characteristics. For example, the fastener structure may include various types of composite structural elements (e.g., thermoplastic composites) and non-composite structural elements (e.g., titanium).

[0020]

[0028] In yet another example of the method 100, the at least one sensor element model 402 includes a zero stiffness model that has no effect on the detected loading condition 618. In yet another example of the method 100, the at least one sensor element model 402 includes a one-dimensional element model, a two-dimensional element model, or any other suitable finite element model, in any suitable combination. In yet another example of the method 100, the at least one sensor element model 402 represents any suitable combination of strain measuring devices, extensometers, strain gauges, strain transducers, load sensors, load cells, force sensors, piezoresistive force sensors, torque sensors, torque transducers, torque cells, stiffness sensors, tactile sensors, or any other suitable sensors.

[0021]

[0029] In another example of the method 100, the at least one sensor element model 402 includes at least one fastener element model 404 associated with at least one fastener element 504 of the plurality of fastener elements 504. In a further example, the fastener element model 404 includes a one-dimensional element model, or any other suitable finite element model, in any suitable combination. In yet another example, the fastener element model 404 includes a model calibrated with fastener parameters 612 representing properties and behavior of actual fasteners in an environment to which the assembled fastened structure 500 is expected to be exposed, to respond to at least one simulated load 616 in a manner that affects the detected load condition 618. In yet another example, the fastener element model 404 includes a zero stiffness model that does not affect the detected load condition 618.

[0022]

[0030] In yet another example, the method 100 also includes validating 112 the electronic design model 400 of the fastening structure 500 if the detected loading condition 618 is within a predetermined tolerance of the predetermined measurement threshold 620 .

[0023]

[0031] 1, 2, and 4-6, in one or more examples, a method 200 (see FIG. 2) for analyzing a fastened structure includes the method 100 (see FIG. 1) described above. In one example, the method 200 continues from 110 of the method 100 to 202, where if the detected loading condition 622 is not within a predetermined tolerance of the predetermined measurement threshold 620, the electronic design model 400 of the fastened structure 500 is altered to generate a modified design model of the modified structure. At 204, the method 200 for analyzing the fastened structure 500 is repeated based on the modified design model of the modified structure by returning to 102 of the method 100. In a further example, the electronic design model 400 is modified by modifying one or more structural elements 502 of the at least two structural elements 502, modifying one or more fastener elements 504 of the plurality of fastener elements 504, adding one or more fastener elements 504 to the plurality of fastener elements 504, removing one or more fastener elements 504 from the plurality of fastener elements 504, or making any other suitable modification to the electronic design model, in any suitable combination.

[0024]

[0032] 1 and 3-6, in one or more examples, a method 300 (see FIG. 3) for analyzing a fastener structure includes the method 100 (see FIG. 1) described above. In this example, the at least one sensor element model 402 includes a plurality of sensor element models 402. In one example, the method 300 continues from 110 of the method 100 to 302, where a distributed load condition 622 of the fastener structure 500 is determined based on the loading condition 618 detected by the plurality of sensor element models 402. At 304, the distributed load condition 622 is compared to a predetermined distribution threshold 624 of the distributed load condition 622.

[0025]

[0033] In another example of the method 300, the distributed load conditions 622 include distributed displacement conditions, distributed rotation conditions, distributed stiffness conditions, distributed clamp-up conditions, distributed deformation conditions, distributed damage state conditions, or any other suitable distributed load conditions in any suitable combination. Many of the detected load conditions 618 result from the fastened structure including different types of structural elements having different thermal expansion characteristics. For example, the fastened structure may include various types of composite structural elements (e.g., thermoplastic composites) and non-composite structural elements (e.g., titanium).

[0026]

[0034] In yet another example, the method 300 also includes validating 306 the electronic design model 400 of the fastening structure 500 if the distributed load condition 622 is within a predetermined tolerance of a predetermined distribution threshold 624 .

[0027]

[0035] In yet another example, the method 300 also includes modifying 308 the electronic design model 400 of the fastened structure 500 to generate a modified design model of the modified structure if the distributed load condition 622 is not within a predetermined tolerance of the predetermined distribution threshold 624. At 310, the method 300 for analyzing the fastened structure 500 is repeated based on the modified design model of the modified structure by returning to 102 of the method 100. In yet a further example, the electronic design model 400 is modified by modifying one or more structural elements 502 of the at least two structural elements 502, modifying one or more fastener elements 504 of the plurality of fastener elements 504, adding one or more fastener elements 504 to the plurality of fastener elements 504, removing one or more fastener elements 504 from the plurality of fastener elements 504, or making any other suitable modification to the electronic design model, in any suitable combination.

[0028]

[0036] 4-6, by way of example, the present disclosure is directed to a fastener structure management system 600. FIG 4 discloses an example of an electronic design model 400. FIG 5 discloses an example of a fastener structure 500. FIG 6 illustrates a fastener structure management system 600 having a computing system 602 and a storage device 606 that stores a design analysis application program 604 accessible to the computing system 602.

[0029]

[0037] 4-6 , in one or more examples, the fastening structure management system 600 includes a computing system 602 and a storage device 606. The computing system 602 is configured to execute a design analysis application program 604. The storage device 606 is operative to communicate with the computing system 602. The computing system 602 is configured to execute the design analysis application program 604 and to access the electronic design model 400 of the fastening structure 500 from a design computing system 608. The fastening structure 500 includes at least two structural elements 502 assembled by a plurality of fastener elements 504. The electronic design model 400 includes structural element parameters 610 for each structural element 502 and fastener parameters 612 for each fastener element 504. The structural element parameters 610 and fastener parameters 612 represent the properties and behavior of the corresponding structural elements 502 and the corresponding fastener elements 504 in an environment to which the assembled fastening structure 500 is expected to be exposed. The computing system 602 is further configured to execute a design analysis application program 604 and to embed at least one sensor element model 402 in the electronic design model 400. Each sensor element model 402 is embedded at a selected location associated with a selected junction between two or more of the at least two structural elements 502. The at least one sensor element model 402 is configured to monitor a measurement parameter 614 at the selected location in response to application of one or more simulated loads 616 to the electronic design model 400.

[0030]

[0038] Additionally, the computing system 602 is configured to execute the design analysis application program 604 and to apply at least one simulated load 616 to the electronic design model 400. The computing system 602 is further configured to execute the design analysis application program 604 and to monitor the measurement parameters 614 using the at least one sensor element model 402 and detect a load condition 618 at a corresponding selected location based on the at least one simulated load 616. Additionally, the computing system 602 is further configured to execute the design analysis application program 604 and to compare the detected load condition 618 to a predetermined measurement threshold 620 of the monitored measurement parameters 614.

[0031]

[0039] In another example of the fastening structure management system 600, the fastening structure 500 includes three or more structural elements 502 assembled by a plurality of fastener elements 504. In yet another example of the fastening structure management system 600, the fastening structure 500 forms a product structure, a vehicle structure, an automotive structure, an aerial vehicle structure, an aircraft structure, a missile structure, a rocket structure, a launch structure, a satellite structure, a bridge structure, a tunnel structure, or any other suitable structure having a plurality of parts fastened together.

[0032]

[0040] In yet another example of the fastening structure management system 600, the plurality of fastener elements 504 includes a set of fastener elements 504. In this example, the at least two structural elements 502 include at least one composite structural element and at least one non-composite structural element. The at least one non-composite structural element is joined to one or more of the at least one composite structural element by the set of fastener elements 504. In a further example, the plurality of fastener elements 504 and the set of fastener elements 504 include metal fasteners, metal screws, metal machine screws, metal bolts, metal pins, metal rivets, metal nuts, metal retention mechanisms, or any other suitable fastener components, in any suitable combination. In yet another example, the at least one composite structural element includes a thermoplastic composite, a thermoset composite, a reinforced composite, a fiber reinforced composite, a carbon fiber reinforced composite, a reinforced polymer, a fiber reinforced polymer, a carbon fiber reinforced polymer, or any other suitable composite material, in any suitable combination. In yet another example, the at least one non-composite structural element comprises titanium, a titanium based metal, a titanium alloy, Ti-6Al-4V, Ti 6-4, aluminum, an aluminum based metal, an aluminum alloy, vanadium, a vanadium based metal, a vanadium alloy, paper, foam, resin, metal, additive, or any other suitable non-composite solid material in any suitable combination.

[0033]

[0041] In yet another example of the fastener structure management system 600, the fastener elements 504 are represented in the electronic design model 400 as a plurality of fastener element models 404. In other words, the fastener element models are modeled structural elements represented in software (such as ABAQUS® or LS-DYNA). In a further example, each fastener element model 404 is represented in the electronic design model 400 as any suitable combination of truss elements, beam elements, shell elements, or any other suitable fixed elements.

[0034]

[0042] In another example of fastening structure management system 600, at least two structural elements 502 are represented in electronic design model 400 as at least two structural element models 406. In other words, the structural element models are modeled structural elements represented in software (such as ABAQUS® or LS-DYNA). In a further example, each structural element model 406 is represented in electronic design model 400 as any suitable combination of beam elements, shell elements, solid elements, or any other suitable shaped elements. For example, electronic design model 400 may be viewed as a mesh of structural element models 406.

[0035]

[0043] In yet another example of the fastener structure management system 600, each sensor element model 402 is represented in the electronic design model 400 as any suitable combination of truss elements, beam elements, shell elements, or any other suitable fixed elements. In other words, the sensor element models are modeled structural elements that are represented in software (such as ABAQUS® or LS-DYNA).

[0036]

[0044] In yet another example of the fastening structure management system 600, the selected location includes a selected surface location of the at least two structural elements 502, a selected interior location of the at least two structural elements 502, a selected gap location between the at least two structural elements 502, a selected overlap location of two or more of the at least two structural elements 502, or any other suitable location associated with the at least two structural elements 502.

[0037]

[0045] In yet another example of the fastener structure management system 600, the at least one simulated load 616 includes a simulated thermal load, a simulated humidity load, a simulated mechanical load, a simulated structural load, a simulated axial load, or any other suitable simulated load in any suitable combination. The simulated loads may be applied as a constant, cyclical, static, peripheral, with a high rate of change, dynamically, impact, wavy, or any other suitable application technique.

[0038]

[0046] In another example of the fastener structure management system 600, the detected load conditions 618 include a displacement condition, a rotation condition, a stiffness condition, a clamp-up condition, a deformation condition, a damage condition, or any other suitable detected load condition in any suitable combination. Many of the detected load conditions 618 result from the fastener structure including different types of structural elements having different thermal expansion characteristics. For example, the fastener structure may include various types of composite structural elements (e.g., thermoplastic composites) and non-composite structural elements (e.g., titanium).

[0039]

[0047] In yet another example of the fastener structure management system 600, the at least one sensor element model 402 includes a zero stiffness model that has no effect on the detected loading condition 618. In yet another example of the fastener structure management system 600, the at least one sensor element model 402 includes a one-dimensional element model, a two-dimensional element model, or any other suitable finite element model, in any suitable combination. In yet another example of the fastener structure management system 600, the at least one sensor element model 402 represents any suitable combination of strain measuring devices, extensometers, strain gauges, strain transducers, load sensors, load cells, force sensors, piezoresistive force sensors, torque sensors, torque transducers, torque cells, stiffness sensors, tactile sensors, or any other suitable sensors.

[0040]

[0048] In another example of the fastener structure management system 600, the at least one sensor element model 402 includes at least one fastener element model 404 associated with at least one fastener element 504 of the plurality of fastener elements 504. In a further example, the fastener element model 404 includes a one-dimensional element model, or any other suitable finite element model, in any suitable combination. In yet another example, the fastener element model 404 includes a model calibrated with fastener parameters 612 representing properties and behavior of actual fasteners in an environment to which the assembled fastened structure 500 is expected to be exposed, to respond to at least one simulated load 616 in a manner that affects the detected load condition 618. In yet another example, the fastener element model 404 includes a zero stiffness model that does not affect the detected load condition 618.

[0041]

[0049] In yet another example of a fastening structure management system 600, a computing system 602 is configured to execute a design analysis application program 604 and certify the electronic design model 400 of the fastening structure 500 if the detected loading condition 618 is within a predetermined tolerance of a predetermined measurement threshold 620.

[0042]

[0050] In yet another example of the fastening structure management system 600, the at least one sensor element model 402 includes a plurality of sensor element models 402. In a further example, the computing system 602 is configured to execute the design analysis application program 604 and determine a distributed load condition 622 of the fastening structure 500 based on the load condition 618 detected by the plurality of sensor element models 402. The computing system 602 is further configured to compare the distributed load condition 622 to a predetermined distribution threshold 624 of the distributed load condition 622. In yet a further example, the distributed load condition 622 includes a distributed displacement condition, a distributed rotation condition, a distributed stiffness condition, a distributed clamp-up condition, a distributed deformation condition, a distributed damage state condition, or any other suitable distributed load condition in any suitable combination. Many of the distributed load conditions 622 result from the fastening structure including different types of structural elements having different thermal expansion characteristics. For example, the fastening structure may include various types of composite structural elements (e.g., thermoplastic composites) and non-composite structural elements (e.g., titanium). In yet another example, the computing system 602 is configured to execute the design analysis application program 604 and validate the electronic design model 400 of the fastening structure 500 if the distributed load condition 622 is within a predetermined tolerance of a predetermined distribution threshold 624.

[0043]

[0051] In one or more additional examples of the fastener structure management system 600, the computing system 602 may further include at least one processor 626 and associated memory 628, a user input device 630, a user display device 632, and a network interface 634 operative to communicate with the design computing system 608 via a communications network 636. The computing system 602 may be operative to communicate with local user computing devices 638 and / or remote user computing devices 640. The storage device 606 may include memory areas allocated to store at least one application program 642, a model 644, and data 646.

[0044]

[0052] 4-7, by way of example, the present disclosure is directed to an analytical computing system 700. FIG. 4 discloses an example of an electronic design model 400. FIG. 5 discloses an example of a fastened structure 500. FIG. 6 illustrates a fastened structure management system 600 having certain components that may be implemented in the analytical computing system 700. FIG. 7 illustrates an analytical computing system 700 having at least one processor 702 and at least one electronic storage device 706 having stored thereon a design analysis application program 604 accessible to the at least one processor 702.

[0045]

[0053] 4-7, in one or more examples, the analysis computing system 700 includes at least one processor 702 and associated memory 704, at least one electronic storage device 706, and a network interface 708. The at least one electronic storage device 706 stores the design analysis application program 604. The network interface 708 is operative to communicate with the at least one processor 702 and configured to interface with a communications network 710. The analysis computing system 700 is configured to access an electronic design model 400 of a fastening structure 500 from the design computing system 608 via the network interface 708 and the communications network 710 in conjunction with the at least one processor 702 executing the design analysis application program 604. The fastening structure 500 includes at least two structural elements 502 assembled by a plurality of fastener elements 504. The electronic design model 400 includes structural element parameters 610 for each structural element 502 and fastener parameters 612 for each fastener element 504. The structural element parameters 610 and fastener parameters 612 represent properties and behaviors of the corresponding structural element 502 and the corresponding fastener element 504 in an environment to which the assembled fastened structure 500 is expected to be exposed. The analytical computing system 700 is further configured to embed at least one sensor element model 402 in the electronic design model 400 in conjunction with the at least one processor 702 executing the design analysis application program 604. Each sensor element model 402 is embedded at a selected location associated with a selected joint between two or more of the at least two structural elements 502. The at least one sensor element model 402 is configured to monitor a measurement parameter 614 at the selected location in response to application of one or more simulated loads 616 to the electronic design model 400.

[0046]

[0054] Additionally, the analysis computing system 700 is configured to apply at least one simulated load 616 to the electronic design model 400 in conjunction with the at least one processor 702 executing the design analysis application program 604. The analysis computing system 700 is further configured to monitor the measurement parameters 614 using the at least one sensor element model 402 in conjunction with the at least one processor 702 executing the design analysis application program 604, and detect a load condition 618 at a corresponding selected location based on the at least one simulated load 616. Additionally, the analysis computing system 700 is configured to compare the detected load condition 618 to a predetermined measurement threshold 620 of the monitored measurement parameter 614 in conjunction with the at least one processor 702 executing the design analysis application program 604.

[0047]

[0055] In another example of the analytical computing system 700, the at least one electronic storage device 706 is configured to store at least one sensor element model 402, measurement parameters 614 associated with the at least one sensor element model 402, and predetermined measurement thresholds 620 associated with the measurement parameters 614.

[0048]

[0056] In yet another example of the analytical computing system 700, the fastened structure 500 includes three or more structural elements 502 assembled by a plurality of fastener elements 504. In yet another example of the analytical computing system 700, the fastened structure 500 forms a product structure, a vehicle structure, an automotive structure, an aerial vehicle structure, an aircraft structure, a missile structure, a rocket structure, a launch structure, a satellite structure, a bridge structure, a tunnel structure, or any other suitable structure having a plurality of parts fastened together.

[0049]

[0057] In yet another example of the analytical computing system 700, the plurality of fastener elements 504 includes a set of fastener elements 504. The at least two structural elements 502 include at least one composite structural element and at least one non-composite structural element. The at least one non-composite structural element is joined to one or more of the at least one composite structural element by the set of fastener elements 504. In a further example, the plurality of fastener elements 504 and the set of fastener elements 504 include metal fasteners, metal screws, metal machine screws, metal bolts, metal pins, metal rivets, metal nuts, metal retention mechanisms, or any other suitable fastener components, in any suitable combination. In yet another example, the at least one composite structural element includes a thermoplastic composite, a thermoset composite, a reinforced composite, a fiber reinforced composite, a carbon fiber reinforced composite, a reinforced polymer, a fiber reinforced polymer, a carbon fiber reinforced polymer, or any other suitable composite material, in any suitable combination. In still yet another example, the at least one non-composite structural element comprises titanium, a titanium based metal, a titanium alloy, Ti-6Al-4V, Ti 6-4, aluminum, an aluminum based metal, an aluminum alloy, vanadium, a vanadium based metal, a vanadium alloy, paper, foam, resin, metal, additive, or any other suitable non-composite solid material in any suitable combination.

[0050]

[0058] In another example of analytical computing system 700, the fastener elements 504 are represented in electronic design model 400 as a plurality of fastener element models 404. In other words, the fastener element models are modeled structural elements represented in software (such as ABAQUS® or LS-DYNA). In a further example, each fastener element model 404 is represented in electronic design model 400 as any suitable combination of truss elements, beam elements, shell elements, or any other suitable shaped elements.

[0051]

[0059] In yet another example of analytical computing system 700, at least two structural elements 502 are represented in electronic design model 400 as at least two structural element models 406. In other words, the structural element models are modeled structural elements represented in software (such as ABAQUS® or LS-DYNA). In a further example, each structural element model 406 is represented in electronic design model 400 as any suitable combination of beam elements, shell elements, solid elements, or any other suitable shaped elements. For example, electronic design model 400 may be viewed as a mesh of structural element models 406.

[0052]

[0060] In yet another example of analytical computing system 700, each sensor element model 402 is represented in electronic design model 400 as any suitable combination of truss elements, beam elements, shell elements, or any other suitable fixed elements. In other words, the sensor element models are modeled structural elements that are represented in software (such as ABAQUS® or LS-DYNA).

[0053]

[0061] In still further examples of the analytical computing system 700, the selected locations include selected surface locations of the at least two structural elements 502, selected interior locations of the at least two structural elements 502, selected gap locations between the at least two structural elements 502, selected overlap locations of two or more of the at least two structural elements 502, or any other suitable locations associated with the at least two structural elements 502.

[0054]

[0062] In another example of the analytical computing system 700, the at least one simulated load 616 includes a simulated thermal load, a simulated humidity load, a simulated mechanical load, a simulated structural load, a simulated axial load, or any other suitable simulated load in any suitable combination. The simulated loads may be applied as a constant, cyclical, static, peripheral, with a high rate of change, dynamically, impact, undulating, or any other suitable application technique.

[0055]

[0063] In yet another example of the analytical computing system 700, the detected loading conditions 618 include displacement conditions, rotation conditions, stiffness conditions, clamp-up conditions, deformation conditions, damage state conditions, or any other suitable detected loading conditions in any suitable combination. Many of the detected loading conditions 618 result from the fastener structure including different types of structural elements having different thermal expansion characteristics. For example, the fastener structure may include various types of composite structural elements (e.g., thermoplastic composites) and non-composite structural elements (e.g., titanium).

[0056]

[0064] In yet another example of the analysis computing system 700, the at least one sensor element model 402 includes a zero stiffness model that has no effect on the detected loading condition 618. In still yet another example of the analysis computing system 700, the at least one sensor element model 402 includes a one-dimensional element model, a two-dimensional element model, or any other suitable finite element model, in any suitable combination. In another example of the analysis computing system 700, the at least one sensor element model 402 represents any suitable combination of strain measuring devices, extensometers, strain gauges, strain transducers, load sensors, load cells, force sensors, piezoresistive force sensors, torque sensors, torque transducers, torque cells, stiffness sensors, tactile sensors, or any other suitable sensors.

[0057]

[0065] In yet another example of the analytical computing system 700, the at least one sensor element model 402 includes at least one fastener element model 404 associated with at least one fastener element 504 of the plurality of fastener elements 504. In a further example, the fastener element model 404 includes a one-dimensional element model, or any other suitable finite element model, in any suitable combination. In yet another example, the fastener element model 404 includes a model calibrated with fastener parameters 612 representing properties and behavior of actual fasteners in an environment to which the assembled fastened structure 500 is expected to be exposed, to respond to at least one simulated load 616 in a manner that affects the detected loading condition 618. In yet another example, the fastener element model 404 includes a zero stiffness model that does not affect the detected loading condition 618.

[0058]

[0066] In yet another example of the analytical computing system 700, the analytical computing system 700 is configured, in conjunction with at least one processor 702 executing the design analysis application program 604, to certify the electronic design model 400 of the fastening structure 500 if the detected loading condition 618 is within a predetermined tolerance of the predetermined measurement threshold 620.

[0059]

[0067] In yet another example of the analysis computing system 700, the at least one sensor element model 402 includes a plurality of sensor element models 402. In a further example, the analysis computing system 700 is configured to determine a distributed load condition 622 of the fastened structure 500 based on the load condition 618 detected by the plurality of sensor element models 402 in conjunction with the at least one processor 702 executing the design analysis application program 604. Additionally, the analysis computing system 700 is configured to compare the distributed load condition 622 to a predetermined distribution threshold 624 of the distributed load condition 622 in conjunction with the at least one processor 702 executing the design analysis application program 604. In yet a further example, the distributed load condition 622 includes a distributed displacement condition, a distributed rotation condition, a distributed stiffness condition, a distributed clamp-up condition, a distributed deformation condition, a distributed damage state condition, or any other suitable distributed load condition in any suitable combination. Many of the distributed load conditions 622 result from the fastened structure including different structural elements having different thermal expansion characteristics. For example, the fastened structure may include various types of composite structural elements (e.g., thermoplastic composites) and non-composite structural elements (e.g., titanium). In yet another example, the analytical computing system 700, in conjunction with the at least one processor 702 executing the design analysis application program 604, is configured to validate the electronic design model 400 of the fastened structure 500 if the distributed load condition 622 is within a predetermined tolerance of the predetermined distribution threshold 624.

[0060]

[0068] In one or more further examples, the analytical computing system 700 may also include a user input device 712 and a user display device 714. The analytical computing system 700 may be operative to communicate with local user computing devices 716 and / or remote user computing devices 718. The at least one electronic storage device 706 may include memory areas allocated to store at least one application program 642, a model 644, and data 646.

[0061]

[0069] The examples of the methods 100, 200, 300, electronic design model 400, fastener structure management system 600, and analytical computing system 700 for analyzing fastener structures 500 may be related to or used in the context of aircraft design and manufacturing. Although an aircraft example is described, the examples and principles disclosed herein may also be applied to other products in the aerospace industry and other industries, such as automotive, space, building, and other design and manufacturing industries. Thus, the examples and principles disclosed herein may also be applied to methods for analyzing fastener structures in the design and manufacturing of various types of vehicles and in the design and construction of various types of transportation structures, in addition to aircraft.

[0062]

[0070] The above detailed description refers to the attached drawings, which show illustrative examples of the present disclosure. Other examples with different structures and steps do not depart from the scope of the present disclosure. Similar reference numbers may represent the same features, elements, or components in different drawings. Throughout this disclosure, any of a plurality of items may be referred to individually as that item, and a plurality of items may be referred to collectively as that item or with a plurality of similar reference numbers. Furthermore, as used herein, it should be understood that a feature, element, component, or step following the word "a" or "an" does not exclude a plurality of features, elements, components, or steps unless such exclusion is expressly stated.

[0063]

[0071] The above provides illustrative and non-exhaustive examples of the subject matter according to the present disclosure. Such examples may, but are not necessarily, claimed. Reference herein to an "example" means that one or more features, structures, elements, components, properties, and / or process steps described in connection with the example are included in at least one aspect, embodiment, and / or implementation of the subject matter according to the present disclosure. Thus, throughout this disclosure, the phrases "one example," "another example," "one or more examples," and similar phrases may, but do not necessarily, refer to the same example. Furthermore, subject matter characterizing any one of the examples may, but does not necessarily, include subject matter characterizing any other example. Furthermore, subject matter characterizing any one of the examples may, but does not necessarily, be combined with subject matter characterizing any other example.

[0064]

[0072] As used herein, a system, apparatus, device, structure, article, element, component, or hardware that is "configured to" perform a particular function does not have the potential to perform that particular function only after further modification, but is in fact capable of performing such particular function without any modification. In other words, a system, apparatus, structure, article, element, component, or hardware that is "configured to" perform a particular function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing that particular function. As used herein, "configured to" means that there are characteristics of the system, apparatus, structure, article, element, component, or hardware that enable the system, apparatus, structure, article, element, component, or hardware to perform the particular function without further modification. In this disclosure, a system, apparatus, device, structure, article, element, component, or hardware described as being "configured to" perform a particular function may additionally or alternatively be described as being "adapted to" and / or "operative to" perform that function.

[0065]

[0073] The terms "first," "second," "third," etc. are used herein merely as labels, unless otherwise indicated, and are not intended to impose any sequential, positional, or hierarchical requirements on the items to which they refer. Furthermore, reference to, for example, a "second" item does not require or preclude the presence of, for example, a "first" or lower numbered item and / or, for example, a "third" or higher numbered item.

[0066]

[0074] As used herein, the phrase "at least one of" used in conjunction with listed items means that various combinations of one or more of the listed items may be used and that only one of each listed item may be required. For example, "at least one of item A, item B, and item C" may include, but is not limited to, "item A" or "item A and item B." Examples may also include "item A, item B, and item C," or "item B and item C." In other examples, "at least one of" may be, but is not limited to, "two items A, one item B, and ten items C," "four items B and seven items C," and other suitable combinations. As used herein, the word "and / or" and the symbol " / " include any and all combinations of one or more of the associated listed items.

[0067]

[0075] As used herein, the terms "coupled," "coupling," and similar terms refer to two or more elements that are joined, linked, fastened, attached, connected, in communication, or otherwise associated with one another (e.g., mechanically, electrically, fluidly, optically, electromagnetically). These elements may be directly associated or indirectly associated in various examples. As an example, element A may be directly associated with element B. As another example, element A may be indirectly associated with element B, e.g., through another element C. It will be understood that not all associations between the various disclosed elements are necessarily depicted. Thus, other connections than those shown in the figures may exist.

[0068]

[0076] As used herein, the term "approximately" refers to or describes a condition that is close to, but not exactly the same as, a specified condition, yet still performs a desired function or obtains a desired result. As an example, the term "approximately" refers to a condition that is within an acceptable range of a given tolerance or precision (e.g., within 10% of a specified condition). However, the term "approximately" does not exclude a condition that is exactly the same as the specified condition. As used herein, the term "substantially" refers to a condition that is essentially the same as a specified condition that performs a desired function or obtains a desired result.

[0069]

[0077] In the previously referenced Figures 1-3, the blocks may represent processes, steps, and / or portions thereof, and the lines connecting the various blocks do not imply any particular order or dependency of the processes or portions thereof. It will be understood that not all dependencies between the various processes disclosed are necessarily depicted. Figures 1-3 and the associated disclosures describing the steps of the disclosed methods described herein should not be construed as absolutely dictating the sequence in which the steps are performed. Rather, even if one exemplary order is shown, it should be understood that the sequence of the steps may be modified accordingly. Thus, modifications, additions, and / or omissions may be made to the illustrated steps, and certain steps may be performed in a different order or simultaneously. In addition, those skilled in the art will recognize that it is not necessary to perform all the steps described.

[0070]

[0078] The previously referenced Figures 4-7 may depict functional elements, features, or components thereof, and do not necessarily imply any particular structure. Thus, modifications, additions, and / or omissions may be made to the illustrated configurations. In addition, those skilled in the art will recognize that not all elements, features, and / or components described and illustrated in the previously referenced Figures 4-7 need to be included in every example, and not all elements, features, and / or components described herein need to be described in each embodiment. Thus, some of the elements, features, and / or components described and illustrated in Figures 4-7 may be combined in various ways without the need to include other features described and illustrated in Figures 4-7, other figures, and / or related disclosure, and such combination or combinations may not be expressly illustrated herein. Similarly, additional features not limited to the examples presented may be combined with some or all of the features illustrated and described herein. The schematic diagrams of the examples illustrated in the previously referenced Figures 4-7 are not meant to imply architectural limitations on the embodiments, unless expressly stated. Rather, although one exemplary structure is shown, it should be understood that the structure may be modified accordingly. Thus, modifications, additions, and / or omissions may be made to the illustrated structure. Furthermore, although elements, features, and / or components that serve similar or at least substantially similar purposes are similarly numbered in each of Figures 4-7, such elements, features, and / or components may not be described in detail herein with reference to each of Figures 4-7. Similarly, although not all elements, features, and / or components are numbered in each of Figures 4-7, the reference numbers associated therewith may be used consistently herein.

[0071]

[0079] Additionally, references throughout this specification to "features," "advantages," or similar language used herein do not imply that all of the features and advantages that may be realized by the examples disclosed herein should be or are in any single example. Rather, language referring to features and advantages is understood to mean that the particular feature, advantage, or characteristic described in connection with an example is included in at least one example. Thus, references to "features," "advantages," and similar language used throughout this disclosure may, but do not necessarily, refer to the same example.

[0072]

[0080] Examples of the subject matter disclosed herein may be described in the context of an aircraft manufacturing and service method 800, shown in FIG. 8, and an aircraft 900, shown in FIG. 9. In one or more examples, the disclosed methods and systems for analyzing fastening structures may be used in aircraft manufacturing. The service method 800 may include specification and design (block 802) and material procurement (block 804) of the aircraft 900 during pre-production. During production, component and subassembly manufacturing (block 806) and system integration (block 808) of the aircraft 900 may occur. The aircraft 900 may then be placed into service (block 812) through certification and delivery (block 810). During its operational life, the aircraft 900 may be scheduled for routine maintenance and service (block 814). The routine maintenance and service may include modification, reconfiguration, refurbishment, etc. of one or more systems of the aircraft 900.

[0073]

[0081] Each process of maintenance method 800 may be performed or implemented by a system integrator, a third party, and / or an operator (e.g., a customer). As used herein, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors, a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers, and an operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0074]

[0082] As shown in FIG. 9 , an aircraft 900 produced by the maintenance method 800 may include an airframe 902 having a number of high level systems 904 and an interior 906. Examples of high level systems 904 include one or more of a propulsion system 908, an electrical system 910, a hydraulic system 912, and an environmental system 914. Any number of other systems may be included. Although an aerospace example is shown, the principles disclosed herein may be applied to other industries, such as the automotive industry. Thus, in addition to the aircraft 900, the principles disclosed herein may be applied to other vehicles, such as land vehicles, marine vehicles, space vehicles, etc.

[0075]

[0083] The disclosed methods and systems for analyzing fastening structures may be used during any one or more stages of manufacturing and maintenance method 800. For example, components or subassemblies corresponding to manufacturing of components and subassemblies (block 806) may be fabricated or manufactured in a manner similar to components or subassemblies manufactured during operation of aircraft 900 (block 812). Also, one or more examples of tooling set(s), system(s), method(s), or any combination thereof may be utilized during the manufacturing stage (blocks 806 and 808), for example, by significantly streamlining the assembly of aircraft 900 or significantly reducing the cost of aircraft 900. Similarly, one or more examples implementing tooling sets, systems, or methods, or combinations thereof may be utilized during operation of aircraft 900 (block 812) and / or during maintenance and service (block 814), for example and without limitation.

[0076]

[0084] The features, advantages, and characteristics of one described example may be combined in any suitable manner in one or more other examples. Those skilled in the art will recognize that the examples described herein may be practiced without one or more of the specific features or advantages of a particular example. In other cases, additional features and advantages may be recognized in certain examples that are not present in all examples. Furthermore, while various examples of the methods 100, 200, 300, fastening structure management system 600, and analysis computing system 700 for analyzing a fastening structure 500 have been shown and described, modifications may occur to those skilled in the art upon reading this specification. The present application is intended to include such modifications and is limited only by the scope of the claims.

Claims

1. A method (100) for analyzing a fastening structure (500), comprising: accessing (102) an electronic design model (400) of the fastening structure (500), the fastening structure (500) comprising at least two structural elements (502) assembled by a plurality of fastener elements (504), the electronic design model (400) comprising structural element parameters (610) for each structural element (502) and fastener parameters (612) for each fastener element (504), the structural element parameters (610) and the fastener parameters (612) representing properties and behavior of the corresponding structural elements (502) and the corresponding fastener elements (504) in an environment to which the assembled fastening structure (500) is expected to be exposed; embedding (104) at least one sensor element model (402) within the electronic design model (400), each sensor element model (402) being embedded at a selected location associated with a selected joint between two or more of the at least two structural elements (502), the at least one sensor element model (402) being configured to monitor a measurement parameter (614) at the selected location in response to application of one or more simulated loads (616) to the electronic design model (400); applying (106) at least one simulation load (616) to the electronic design model (400); monitoring (614) the measured parameters using the at least one sensor element model (402) to detect (108) a corresponding load condition (618) at the selected location based on the at least one simulated load (616); comparing (110) the detected load condition (618) with a predetermined measurement threshold (620) of the monitored measurement parameter (614); A method (100).

2. The method of claim 1 , wherein the fastening structure (500) comprises three or more structural elements (502) assembled by the plurality of fastener elements (504).

3. 10. The method of claim 1, wherein the fastening structure (500) forms at least one of a product structure, a vehicle structure, an automotive structure, an aerial vehicle structure, an aircraft structure, a missile structure, a rocket structure, a launch structure, a satellite structure, a bridge structure, and a tunnel structure.

4. 2. The method of claim 1, wherein the plurality of fastener elements (504) comprises a set of fastener elements (504), the at least two structural elements (502) comprise at least one composite structural element and at least one non-composite structural element, the at least one non-composite structural element being joined to one or more of the at least one composite structural element by the set of fastener elements (504).

5. 5. The method of claim 4, wherein the plurality of fastener elements (504) and the set of fastener elements (504) comprise at least one of a metal fastener, a metal screw, a metal machine screw, a metal bolt, a metal pin, a metal rivet, a metal nut, and a metal retention mechanism.

6. 5. The method of claim 4, wherein the at least one composite structural element comprises at least one of a thermoplastic composite, a thermoset composite, a reinforced composite, a fiber reinforced composite, a carbon fiber reinforced composite, a reinforced polymer, a fiber reinforced polymer, and a carbon fiber reinforced polymer.

7. 5. The method of claim 4, wherein the at least one non-composite structural element comprises at least one of titanium, titanium-based metals, titanium alloys, Ti-6Al-4V, Ti 6-4, aluminum, aluminum-based metals, aluminum alloys, vanadium, vanadium-based metals, and vanadium alloys.

8. The method of claim 1 , wherein the plurality of fastener elements (504) are represented in the electronic design model (400) as a plurality of fastener element models (404).

9. The method of claim 8, wherein each fastener element model (404) is represented in the electronic design model (400) as a truss element, a beam element, or a shell element.

10. The method of claim 1 , wherein the at least two structural elements (502) are represented in the electronic design model (400) as at least two structural element models (406).

11. The method of claim 10 , wherein each structural element model (406) is represented in the electronic design model (400) as a beam element, a shell element, or a solid element.

12. The method of claim 1 , wherein each sensor element model (402) is represented in the electronic design model (400) as a truss element, a beam element, or a shell element.

13. 2. The method of claim 1, wherein the selected locations include at least one of a selected surface location of the at least two structural elements (502), a selected interior location of the at least two structural elements (502), a selected gap location between the at least two structural elements (502), and a selected overlap location of two or more structural elements (502) of the at least two structural elements (502).

14. The method of claim 1 , wherein the at least one simulated load (616) comprises at least one of a simulated thermal load, a simulated humidity load, a simulated mechanical load, a simulated structural load, and a simulated axial load.

15. The method of claim 1 , wherein the detected load condition (618) comprises at least one of a displacement condition, a rotation condition, a stiffness condition, a clamp-up condition, a deformation condition, and a damage state condition.

16. The method of claim 1 , wherein the at least one sensor element model (402) comprises a zero stiffness model that has no effect on the detected loading condition (618).

17. The method of claim 1 , wherein the at least one sensor element model (402) comprises at least one of a one-dimensional element model and a two-dimensional element model.

18. 2. The method of claim 1, wherein the at least one sensor element model (402) represents at least one of a strain measuring device, an extensometer, a strain gauge, a strain transducer, a load sensor, a load cell, a force sensor, a piezoresistive force sensor, a torque sensor, a torque transducer, a torque cell, a stiffness sensor, and a tactile sensor.

19. The method of claim 1 , wherein the at least one sensor element model (402) comprises at least one fastener element model (404) associated with at least one fastener element model (404) of the plurality of fastener elements (504).

20. The method of claim 19, wherein the fastener element model (404) comprises a one-dimensional element model.

21. 20. The method of claim 19, wherein the fastener element model (404) comprises a model calibrated with fastener parameters (612) representative of properties and behavior of actual fasteners in an environment to which the assembled fastened structure (500) is expected to be exposed to respond to the at least one simulated load (616) in a manner that affects the detected loading condition (618).

22. The method of claim 19, wherein the fastener element model (404) includes a zero stiffness model that has no effect on the detected loading condition (618).

23. 2. The method of claim 1, further comprising: validating (112) the electronic design model (400) of the fastening structure (500) if the detected load condition (618) is within a predetermined tolerance of the predetermined measurement threshold (620).

24. modifying (202) the electronic design model (400) of the fastening structure (500) to generate a modified design model of a modified structure if the detected loading condition (622) is not within a predetermined tolerance of the predetermined measurement threshold (620); repeating (204) the method (200) for analyzing the fastening structure (500) based on the modified design model of the modified structure; The method of claim 1 further comprising:

25. 25. The method of claim 24, wherein the electronic design model (400) is modified by at least one of: modifying one or more structural elements (502) of the at least two structural elements (502), modifying one or more fastener elements (504) of the plurality of fastener elements (504), adding one or more fastener elements (504) to the plurality of fastener elements (504), and removing one or more fastener elements (504) from the plurality of fastener elements (504).

26. The method of claim 1 , wherein the at least one sensor element model (402) comprises a plurality of sensor element models (402).

27. determining (302) a distributed load condition (622) of the fastening structure (500) based on the load condition (618) detected by the plurality of sensor element models (402); comparing (304) the distributed load condition (622) with a predetermined distribution threshold (624) of the distributed load condition (622); 27. The method of claim 26, further comprising:

28. 28. The method of claim 27, wherein the distributed load condition (622) comprises at least one of a distributed displacement condition, a distributed rotation condition, a distributed stiffness condition, a distributed clamp-up condition, a distributed deformation condition, and a distributed damage state condition.

29. 28. The method of claim 27, further comprising validating (306) the electronic design model (400) of the fastening structure (500) if the distributed load condition (622) is within a predetermined tolerance of the predetermined distribution threshold (624).

30. modifying (308) the electronic design model (400) of the fastening structure (500) to generate a modified design model of a modified structure if the distributed load condition (622) is not within a predetermined tolerance of the predetermined distribution threshold (624); repeating (310) the method (300) for analyzing the fastening structure (500) based on the modified design model of the modified structure; 30. The method of claim 27, further comprising:

31. 31. The method of claim 30, wherein the electronic design model (400) is modified by at least one of modifying one or more structural elements (502) of the at least two structural elements (502), modifying one or more fastener elements (504) of the plurality of fastener elements (504), adding one or more fastener elements (504) to the plurality of fastener elements (504), and removing one or more fastener elements (504) from the plurality of fastener elements (504).

32. A fastening structure management system (600), a computing system (602) configured to execute a design analysis application program (604); a storage device (606) operative to communicate with the computing system (602); Equipped with The computing system (602) executes the design analysis application program (604) and accessing from a design computing system (608) an electronic design model (400) of a fastening structure (500), the fastening structure (500) comprising at least two structural elements (502) assembled by a plurality of fastener elements (504), the electronic design model (400) comprising structural element parameters (610) for each structural element (502) and fastener parameters (612) for each fastener element (504), the structural element parameters (610) and the fastener parameters (612) representing properties and behavior of the corresponding structural elements (502) and the corresponding fastener elements (504) in an environment to which the assembled fastening structure (500) is expected to be exposed; embedding at least one sensor element model (402) within the electronic design model (400), each sensor element model (402) being embedded at a selected location associated with a selected joint between two or more of the at least two structural elements (502), the at least one sensor element model (402) being configured to monitor a measurement parameter (614) at the selected location in response to application of one or more simulated loads (616) to the electronic design model (400); applying at least one simulation load (616) to the electronic design model (400); monitoring the measured parameters (614) using the at least one sensor element model (402) to detect a corresponding load condition (618) at the selected location based on the at least one simulated load (616); comparing the detected load condition (618) with a predetermined measurement threshold (620) of the monitored measurement parameter (614); is configured to execute A fastening structure management system (600).

33. The fastening structure management system of claim 32, wherein the fastening structure (500) comprises three or more structural elements (502) assembled by the plurality of fastener elements (504).

34. 33. The fastening structure management system of claim 32, wherein the fastening structure (500) forms at least one of a product structure, a vehicle structure, an automotive structure, an aerial vehicle structure, an aircraft structure, a missile structure, a rocket structure, a launch structure, a satellite structure, a bridge structure, and a tunnel structure.

35. 33. The fastening structure management system of claim 32, wherein the plurality of fastening elements (504) comprises a set of fastening elements (504), the at least two structural elements (502) comprise at least one composite structural element and at least one non-composite structural element, the at least one non-composite structural element being joined to one or more of the at least one composite structural element by the set of fastening elements (504).

36. 36. The fastener structure management system of claim 35, wherein the plurality of fastener elements (504) and the set of fastener elements (504) include at least one of a metal fastener, a metal screw, a metal machine screw, a metal bolt, a metal pin, a metal rivet, a metal nut, and a metal retention mechanism.

37. 36. The fastening structure management system of claim 35, wherein the at least one composite structural element comprises at least one of a thermoplastic composite, a thermoset composite, a reinforced composite, a fiber reinforced composite, a carbon fiber reinforced composite, a reinforced polymer, a fiber reinforced polymer, and a carbon fiber reinforced polymer.

38. 36. The fastener structure management system of claim 35, wherein the at least one non-composite structural element comprises at least one of titanium, titanium based metals, titanium alloys, Ti-6Al-4V, Ti 6-4, aluminum, aluminum based metals, aluminum alloys, vanadium, vanadium based metals, and vanadium alloys.

39. The fastener structure management system of claim 32 , wherein the plurality of fastener elements (504) are represented in the electronic design model (400) as a plurality of fastener element models (404).

40. The fastener structure management system of claim 39, wherein each fastener element model (404) is represented in the electronic design model (400) as a truss element, a beam element, or a shell element.

41. The fastener structure management system of claim 32 , wherein the at least two structural elements (502) are represented in the electronic design model (400) as at least two structural element models (406).

42. The fastener structure management system of claim 41 , wherein each structural element model (406) is represented in the electronic design model (400) as a beam element, a shell element, or a solid element.

43. The fastener structure management system of claim 32, wherein each sensor element model (402) is represented in the electronic design model (400) as a truss element, a beam element, or a shell element.

44. 33. The fastening structure management system of claim 32, wherein the selected locations include at least one of a selected surface location of the at least two structural elements (502), a selected interior location of the at least two structural elements (502), a selected gap location between the at least two structural elements (502), and a selected overlap location of two or more structural elements (502) of the at least two structural elements (502).

45. 33. The fastener structure management system of claim 32, wherein the at least one simulated load (616) comprises at least one of a simulated thermal load, a simulated humidity load, a simulated mechanical load, a simulated structural load, and a simulated axial load.

46. The fastener structure management system of claim 32 , wherein the detected load condition (618) comprises at least one of a displacement condition, a rotation condition, a stiffness condition, a clamp-up condition, a deformation condition, and a damage state condition.

47. The fastener structure management system of claim 32 , wherein the at least one sensor element model (402) comprises a zero stiffness model that has no effect on the detected load condition (618).

48. The fastener structure management system of claim 32 , wherein the at least one sensor element model (402) includes at least one of a one-dimensional element model and a two-dimensional element model.

49. 33. The fastener structure management system of claim 32, wherein the at least one sensor element model (402) represents at least one of a strain measuring device, an extensometer, a strain gauge, a strain transducer, a load sensor, a load cell, a force sensor, a piezoresistive force sensor, a torque sensor, a torque transducer, a torque cell, a stiffness sensor, and a tactile sensor.

50. 33. The fastener structure management system of claim 32, wherein the at least one sensor element model (402) comprises at least one fastener element model (404) associated with at least one fastener element model (404) of the plurality of fastener elements (504).

51. The fastener structure management system of claim 50, wherein the fastener element model (404) comprises a one-dimensional element model.

52. 51. The fastener structure management system of claim 50, wherein the fastener element model (404) includes a model calibrated with fastener parameters (612) representing properties and behavior of actual fasteners in an environment to which the assembled fastened structure (500) is expected to be exposed to respond to the at least one simulated load (616) in a manner that affects the detected loading condition (618).

53. The fastener structure management system of claim 50, wherein the fastener element model (404) includes a zero stiffness model that has no effect on the detected loading condition (618).

54. 33. The fastener structure management system of claim 32, wherein the computing system (602) is configured to execute the design analysis application program (604) and to certify the electronic design model (400) of the fastener structure (500) if the detected load condition (618) is within a predetermined tolerance of the predetermined measurement threshold (620).

55. The fastener structure management system of claim 32 , wherein the at least one sensor element model (402) comprises a plurality of sensor element models (402).

56. The computing system (602) executes the design analysis application program (604) and determining a distributed load condition (622) of the fastening structure (500) based on the load condition (618) detected by the plurality of sensor element models (402); comparing the distributed load condition (622) with a predetermined distribution threshold (624) of the distributed load condition (622); The fastening structure management system of claim 55, configured to execute the following:

57. 57. The fastener structure management system of claim 56, wherein the distributed load condition (622) comprises at least one of a distributed displacement condition, a distributed rotation condition, a distributed stiffness condition, a distributed clamp-up condition, a distributed deformation condition, and a distributed damage state condition.

58. 57. The fastener structure management system of claim 56, wherein the computing system (602) is configured to execute the design analysis application program (604) and to certify the electronic design model (400) of the fastener structure (500) if the distributed load condition (622) is within a predetermined tolerance of the predetermined distribution threshold (624).

59. An analytical computing system (700) for analyzing a fastening structure (500), comprising: At least one processor (702) and associated memory (704); at least one electronic storage device (706) storing a design analysis application program (604); a network interface (708) operative to communicate with the at least one processor (702) and configured to interface with a communications network (710); The analytical computing system (700) executes the design analysis application program (604) with the at least one processor (702), and further includes: accessing, from a design computing system (608) via the network interface (708) and the communications network (710), an electronic design model (400) of a fastening structure (500), the fastening structure (500) comprising at least two structural elements (502) assembled by a plurality of fastener elements (504), the electronic design model (400) comprising structural element parameters (610) for each structural element (502) and fastener parameters (612) for each fastener element (504), the structural element parameters (610) and the fastener parameters (612) representing properties and behavior of the corresponding structural elements (502) and the corresponding fastener elements (504) in an environment to which the assembled fastening structure (500) is expected to be exposed; embedding at least one sensor element model (402) within the electronic design model (400), each sensor element model (402) being embedded at a selected location associated with a selected joint between two or more of the at least two structural elements (502), the at least one sensor element model (402) being configured to monitor a measurement parameter (614) at the selected location in response to application of one or more simulated loads (616) to the electronic design model (400); applying at least one simulation load (616) to the electronic design model (400); monitoring the measured parameters (614) using the at least one sensor element model (402) to detect a corresponding load condition (618) at the selected location based on the at least one simulated load (616); comparing the detected load condition (618) with a predetermined measurement threshold (620) of the monitored measurement parameter (614); is configured to execute Analytical computing systems.

60. 60. The analytical computing system of claim 59, wherein the at least one electronic storage device (706) is configured to store the at least one sensor element model (402), the measurement parameters (614) associated with the at least one sensor element model (402), and the predetermined measurement thresholds (620) associated with the measurement parameters (614).

61. 60. The analytical computing system of claim 59, wherein the fastening structure (500) comprises three or more structural elements (502) assembled by the plurality of fastener elements (504).

62. 60. The analytical computing system of claim 59, wherein the fastening structure (500) forms at least one of a product structure, a vehicle structure, an automotive structure, an aerial vehicle structure, an aircraft structure, a missile structure, a rocket structure, a launch structure, a satellite structure, a bridge structure, and a tunnel structure.

63. 60. The analytical computing system of claim 59, wherein the plurality of fastener elements (504) comprises a set of fastener elements (504), and the at least two structural elements (502) comprise at least one composite structural element and at least one non-composite structural element, the at least one non-composite structural element being joined to one or more of the at least one composite structural element by the set of fastener elements (504).

64. 64. The analytical computing system of claim 63, wherein the plurality of fastener elements (504) and the set of fastener elements (504) include at least one of metal fasteners, metal screws, metal machine screws, metal bolts, metal pins, metal rivets, metal nuts, and metal retention mechanisms.

65. 64. The analytical computing system of claim 63, wherein the at least one composite structural element comprises at least one of a thermoplastic composite, a thermoset composite, a reinforced composite, a fiber reinforced composite, a carbon fiber reinforced composite, a reinforced polymer, a fiber reinforced polymer, and a carbon fiber reinforced polymer.

66. 64. The analytical computing system of claim 63, wherein the at least one non-composite structural element comprises at least one of titanium, titanium based metals, titanium alloys, Ti-6Al-4V, Ti 6-4, aluminum, aluminum based metals, aluminum alloys, vanadium, vanadium based metals, and vanadium alloys.

67. The analytical computing system of claim 59, wherein the plurality of fastener elements (504) are represented in the electronic design model (400) as a plurality of fastener element models (404).

68. 68. The analytical computing system of claim 67, wherein each fastener element model (404) is represented in the electronic design model (400) as a truss element, a beam element, or a shell element.

69. 60. The analytical computing system of claim 59, wherein the at least two structural elements (502) are represented in the electronic design model (400) as at least two structural element models (406).

70. 70. The analytical computing system of claim 69, wherein each structural element model (406) is represented in the electronic design model (400) as a beam element, a shell element, or a solid element.

71. 60. The analytical computing system of claim 59, wherein each sensor element model (402) is represented in the electronic design model (400) as a truss element, a beam element, or a shell element.

72. 60. The analytical computing system of claim 59, wherein the selected locations include at least one of a selected surface location of the at least two structural elements (502), a selected interior location of the at least two structural elements (502), a selected gap location between the at least two structural elements (502), and a selected overlap location of two or more structural elements (502) of the at least two structural elements (502).

73. 60. The analytical computing system of claim 59, wherein the at least one simulated load (616) comprises at least one of a simulated thermal load, a simulated humidity load, a simulated mechanical load, a simulated structural load, and a simulated axial load.

74. 60. The analytical computing system of claim 59, wherein the detected load conditions (618) include at least one of a displacement condition, a rotation condition, a stiffness condition, a clamp-up condition, a deformation condition, and a damage state condition.

75. 60. The analytical computing system of claim 59, wherein the at least one sensor element model (402) comprises a zero stiffness model that has no effect on the detected loading condition (618).

76. 60. The analytical computing system of claim 59, wherein the at least one sensor element model (402) comprises at least one of a one-dimensional element model and a two-dimensional element model.

77. 60. The analytical computing system of claim 59, wherein the at least one sensor element model (402) represents at least one of a strain measuring device, an extensometer, a strain gauge, a strain transducer, a load sensor, a load cell, a force sensor, a piezoresistive force sensor, a torque sensor, a torque transducer, a torque cell, a stiffness sensor, and a tactile sensor.

78. The analytical computing system of claim 59, wherein the at least one sensor element model (402) includes at least one fastener element model (404) associated with at least one fastener element model (404) of the plurality of fastener elements (504).

79. The analytical computing system of claim 78, wherein the fastener element model (404) comprises a one-dimensional element model.

80. 80. The analytical computing system of claim 78, wherein the fastener element model (404) includes a model calibrated with fastener parameters (612) representing properties and behavior of actual fasteners in an environment to which the assembled fastened structure (500) is expected to be exposed to respond to the at least one simulated load (616) in a manner that affects the detected loading condition (618).

81. The analytical computing system of claim 78, wherein the fastener element model (404) includes a zero stiffness model that has no effect on the detected loading condition (618).

82. 60. The analytical computing system of claim 59, wherein the analytical computing system (700), in conjunction with the at least one processor (702) executing the design analysis application program (604), is configured to certify the electronic design model (400) of the fastening structure (500) if the detected load condition (618) is within a predetermined tolerance of the predetermined measurement threshold (620).

83. 60. The analytical computing system of claim 59, wherein the at least one sensor element model (402) comprises a plurality of sensor element models (402).

84. The analytical computing system (700) executes the design analysis application program (604) with the at least one processor (702), and further includes: determining a distributed load condition (622) of the fastening structure (500) based on the load condition (618) detected by the plurality of sensor element models (402); comparing the distributed load condition (622) with a predetermined distribution threshold (624) of the distributed load condition (622); 84. The analytical computing system of claim 83, configured to execute:

85. 85. The analytical computing system of claim 84, wherein the distributed load conditions (622) include at least one of a distributed displacement condition, a distributed rotation condition, a distributed stiffness condition, a distributed clamp-up condition, a distributed deformation condition, and a distributed damage state condition.

86. 85. The analytical computing system of claim 84, wherein the analytical computing system (700), in conjunction with the at least one processor (702) executing the design analysis application program (604), is configured to certify the electronic design model (400) of the fastening structure (500) if the distributed load condition (622) is within a predetermined tolerance of the predetermined distribution threshold (624).

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