Patent Application
20250060258
Examples of the present disclosure generally relate to thermal detection assemblies and methods for operating the thermal detection assemblies.
Commercial turbofan nacelles of aircraft systems may be manufactured of various materials that have different material and/or thermal properties. For example, nacelle fan ducts may be manufactured from aluminum or composite materials, and nacelle structures may be manufactured of layers of bonded composite materials that may be susceptible to damage due to exposure to increased temperatures. For example, at least some of the layers of the bonded composite nacelle structures may be compromised after exposure to increased temperatures generated by a propulsion system of the aircraft system.
In order to regularly inspect the materials of the nacelle fan ducts and/or nacelle structure, an operator must remove thermal blankets that cover some of the fan ducts and/or nacelle structures. The thermal blankets may be designed to control an amount of exposure of the fan ducts and/or structures from thermal energy generated by the propulsion system.
However, the process of removing of the thermal blankets is a cumbersome activity, and can cause damage to the fan ducts, the nacelle structures, and the thermal blankets during the removal process and/or the reapplication process after an inspection event has been completed. Moreover, an operator is unable to determine if the fan ducts and/or structures have been compromised due to exposure to excess thermal energy without removing the thermal blankets from the fan ducts and/or structures, and therefore must regularly inspect the fan ducts and/or nacelle structures. For example, the thermal blankets may needlessly be removed during a regular maintenance activity even though the fan ducts and/or structures have not experienced any thermal damage.
A need exists for a thermal detection system and a method for indicating when one or more materials of an aircraft system may have been damaged due to exposure to thermal energy. Further, a need exists for a passive detection system that can indicate where and/or when thermal damage has occurred, and as a result no longer requires regular inspections of the aircraft system.
With those needs in mind, certain examples of the present disclosure provide a thermal detection assembly for a power system, such as an aircraft system. The thermal detection assembly can include a housing that is operably coupled with a surface of the aircraft system at a first end of the housing, and extends through a passage of the surface of the aircraft system. The housing includes plural interior surfaces that define a cavity that has an opening that is proximate to a second end of the housing. An indicator device and a thermal spring system are disposed within the cavity of the housing. The thermal spring system is engaged with the indicator device and maintains a position of the indicator device within the cavity. One or more characteristics of the thermal spring system may change responsive to the thermal spring system being exposed to a temperature exceeding a designated threshold. The thermal spring system controls movements of the indicator device to move the indicator device from a first position to a different, second position responsive to the one or more characteristics of the thermal spring system changing. A first portion of the indicator device is configured to move out of the cavity of the housing responsive to the thermal spring system moving the indicator device to the second position.
In at least one example, the surface of the power system includes plural layers that are operably coupled with each other. One or more characteristics of one or more of the plural layers may also change responsive to the plural layers being exposed to the temperature exceeding the designated threshold. For example, one or more of the plural layers may be one or more common or similar material and/or thermal properties as one or more materials of the thermal spring system. In at least another example, the surface of the power system may include plural layers operably coupled with each other. The thermal spring system may be manufactured of one or more materials. At least one of the plural layers and at least one of the one or more materials of the thermal spring system may have a common material property.
In at least one example, the thermal spring system may disengage from a second portion of the indicator device responsive to the one or more characteristics of the thermal spring system changing. The thermal spring system is configured to encourage the first portion of the indicator device to move out of the cavity of the housing responsive to the thermal spring system disengaging from the second portion of the indicator device.
In at least one example, the one or more characteristics of the thermal spring system may change responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold for a determined length of time.
In at least one example, the thermal spring system may include a spring device and a thermal component. The indicator device extends between a third end and a fourth end. The spring device may be operably coupled with the indicator device at a location between the third end and the fourth end of the indicator device, and the thermal component may be operably coupled with the third end of the indicator device. In another example, the spring device may be in a compressed state prior to the thermal spring system being exposed to the temperature exceeding the designated threshold, and the spring device may be in a non-compressed state responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold. In another example, the thermal component may have a first shape prior to being exposed to the temperature exceeding the designated threshold, and the thermal component may have a different, second shape responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold.
In at least one example, the thermal spring system may include a spring device, and one or more characteristics of the spring device may change responsive to the spring device being exposed to the temperature exceeding the designated threshold. In another example, the spring device may have a first spring constant prior to being exposed to the temperature exceeding the designated threshold, and the spring device may have a different, second spring constant responsive to the spring device being exposed to the temperature exceeding the designated threshold.
In at least one example, the power system may be an aircraft system, and the surface of the power system may be a surface of a propulsion system of the aircraft system.
Certain examples of the present disclosure provide an assembly that includes a housing having a body that extends between a first end and a second end. The first end of the housing may be operably coupled with a surface of a power system. The body of the housing extends through a passage of the surface of the power system. The housing may include one or more interior surfaces that define a cavity. The cavity may have an opening proximate the second end of the housing. An indicator device may be disposed within the cavity of the housing. The indicator device extends between a third end and a fourth end, wherein the fourth end is disposed proximate the opening of the cavity. A thermal spring system may also be disposed within the cavity of the housing and is engaged with the indicator device. The thermal spring system maintains a position of the indicator device within the cavity. The thermal spring system includes a spring device and a thermal component. The spring device is operably coupled with the indicator device at a location between the third end and the fourth end of the indicator device, and the thermal component is operably coupled with the third end of the indicator device. One or more characteristics of the thermal component may change responsive to the thermal component of the thermal spring system being exposed to a temperature exceeding a designated threshold. The thermal spring system is configured to control movement of the indicator device to move the indicator device from a first position to a second position responsive to the one or more characteristics of the thermal component changing. A portion of the fourth end of the indicator device may move out of the cavity of the housing responsive to the thermal spring system moving the indicator device from the first position to the second position.
Certain examples of the present disclosure provide a thermal detection assembly that includes a housing that extends between a first end operably coupled with a surface of a propulsion system of an aircraft system, through a passage of the surface of the propulsion system, and to a second end of the housing. The housing includes interior surfaces that define a cavity that has an opening proximate to the second end of the housing. An indicator device is disposed within the cavity, and a thermal spring system is disposed within the cavity and is engaged with the indicator device. The thermal spring system maintains a position of the indicator device within the cavity. One or more characteristics of the thermal spring system change responsive to the thermal spring system being exposed to an amount of thermal energy generated by the propulsion system exceeding a designated threshold. The thermal spring system encourages a portion of the indicator device to move out of the cavity of the housing responsive to the one or more characteristics of the thermal spring system changing.
The foregoing summary, as well as the following detailed description of certain examples will be better understood when read in conjunction with the appended drawings. As used herein, an element or step recited in the singular and preceded by the word “a” or “an” should be understood as not necessarily excluding the plural of the elements or steps. Further, references to “one example” are not intended to be interpreted as excluding the existence of additional examples that also incorporate the recited features. Moreover, unless explicitly stated to the contrary, examples “comprising” or “having” an element or a plurality of elements having a particular condition can include additional elements not having that condition.
Referring now to the drawings, which illustrate various embodiments of the present disclosure,
In the illustrated example, the aircraft system includes a first surface 306 and a second surface 308. The second surface 308 extends between an exterior surface 309 and an opposite interior surface 311 that faces towards the an exterior surface 313 of the first surface 306. In the illustrated embodiment, the first and second surfaces 306, 308 are separated by a gap, but alternatively may be directly mating with each other. In one example, the first surface 306 may represent an insulation layer and/or insulation material disposed within the nacelle 200 of the aircraft system 100, such as a thermal blanket of the nacelle, and the second surface 308 may represent one or more layers of a duct system of the nacelle 200.
For example,
In one embodiment, the first and third layers 602, 606 may be the same or substantially the same type of adhesive material, or alternatively may be different types of adhesive materials, may be different materials that have one or more different material properties, or the like. In another embodiment, the exterior and interior surfaces 309, 311 may be the same or substantially the same type of material (e.g., the same, substantially the same, or similar carbon fiber materials) such that the exterior and interior surfaces 309, 311 may have the same or substantially the same material properties. Alternatively, the exterior surface 309 may be a material or material composition that is different than a material or material composition of the interior surface 311 such that one or more material properties of the exterior surface 309 differ from one or more material properties of the interior surface 311.
Returning to
The housing 310 includes one or more interior surfaces 324 that define a cavity 326. The cavity 326 has an opening 327 proximate the second end 322 of the housing 310. In the illustrated embodiment, the cavity 326 includes a first cavity compartment 328 and a second cavity compartment 330. The first and second cavity compartments 328, 330 are separated by one or more surfaces of the housing defining a cavity passage 332 extending between the first and second cavity compartments 328, 330.
The thermal detection assembly 300 includes an indicator device 334 that is disposed within the cavity 326. In the illustrated example, the indicator device 334 extends between a third end 336 and a fourth end 338. In the illustrated example, the third end 336 of the indicator device 334 extends through the cavity passage 332 and is disposed in the first cavity compartment 328. The fourth end 338 is disposed in the second cavity compartment 330 and proximate to the opening 327 of the cavity 326. The indicator device 334 also includes a flange 350 that extends away from the body of the indicator device 334.
The thermal detection assembly 300 includes a thermal spring system 340 that is disposed within the cavity 326. In the illustrated example, the thermal spring system 340 includes a spring device 342 that is disposed within the second cavity compartment 330, and a thermal component 344 that is disposed within the first cavity compartment 328. In one example, the spring device 342 is a compression spring that is operably coupled with (e.g., is wrapped around) the indicator device 334 at a location between the third and fourth ends 336, 338 of the indicator device 334. In the illustrated example, the spring device 342 is positioned between the flange 350 of the indicator device 334 and interior surfaces of the cavity 326 defining the first and second cavity compartments 328, 330. The spring device 342 is shaped, sized, and arranged to encourage movement of the indicator device 334 in a first direction 352.
The third end 336 of the indicator device 334 is operably coupled with the thermal component 344 within the first cavity compartment 328. In the illustrated example, the thermal component 344 is sized to substantially fill the first cavity compartment 328, and is shaped to include one or more retaining features 348. For example, the retaining features 348 may be shaped and sized to engage with the third end 336 of the indicator device 334 to maintain a position of the indicator device 334 within the cavity of the housing. In alternative examples, the thermal component 344 may have any alternative shape, alternative retaining features, or the like.
In the illustrated embodiment of
The state of the thermal detection assembly 300 changes responsive to the thermal spring system 340 being exposed to an amount and/or level of thermal energy that exceeds a designated threshold (e.g., a designated temperature threshold). For example, the thermal detection assembly 300 may be exposed to thermal energy (e.g., heat) that is generated by the propulsion system of the aircraft system. One or more characteristics (e.g., material properties, shapes, sizes, etc.) of one or more of the components of the thermal spring system 340 may change responsive to the components of the thermal spring system 340 being exposed to temperatures exceeding the designated threshold. For example, the spring device 342 and/or the thermal component 344 may be manufactured of one or more materials that have material properties, thermal properties, etc., that may change based on the materials being exposed to temperatures exceeding the designated threshold. Optionally, the one or more characteristics may change responsive to the materials of the spring device 342 and/or the thermal component 344 being exposed to temperatures exceeding the designated threshold for a determined length of time (e.g., 30 seconds, 1 minute, 10 minutes, 30 minutes, 1 hour, 5 hours, etc.). In one example, the length of time may be a consecutive length of time, or alternatively may be a cumulative length of time.
As one example,
In one example, the material or material composition of the thermal component 344 may have one or more material properties that are the same as, substantially the same as, or similar to (e.g., within a determined percentage such as about 2%, about 5%, about 10%, or the like) one or more material properties of one or more materials of one or more layers of the first and/or second surfaces 306, 308. For example, the thermal component 344 may be manufactured of a material that has a thermal property that is the same as, substantially the same as, or similar to a thermal property of one or more materials of one or more layers of the first and/or second surfaces 306, 308 of the aircraft system. For example, the material of the thermal component 344 may have the same, substantially the same, and/or a similar (e.g., within a predetermined percentage threshold) melting point, thermal conductivity, thermal expansion, density, hardness, ductility, malleability, elasticity, or the like, as the material of one or more layers of the surfaces 306, 308.
As one example, the change in one or more characteristics of the thermal component 344 may cause the shape of the thermal component 344 to change from the first shape 344A to a different, second shape 344B shown in
As another example, the change in one or more characteristics of the thermal component 344 may cause a hardness of the material of the thermal component 344 to change. For example, the retention force that is exerted onto the third end 336 of the indicator device 334 by the retaining features 348 of the thermal component 344 may be less than the force generated by the spring device 342 that is exerted onto the flange 350. For example, the hardness of the material of the thermal component 344 prior to exposure to temperatures exceeding the designated threshold may be greater than the hardness of the material of the thermal component 344 after the exposure to temperatures exceeding the designated threshold, after the exposure to temperatures exceeding the designated threshold for the determined length of time, or the like.
The changing of the shape of the thermal component 344 and/or the reduction of hardness and/or strength of the thermal component 344 based at least on the exposure to temperatures exceeding the designated threshold allows the third end 336 of the indicator device 334 to disengage from the thermal component 344, thereby allowing the spring device 342 to move to a non-compressed and/or unloaded state. The spring device 342 moving to a non-compressed state encourages movement of the flange 350 of the indicator device 334 in the first direction 352 towards the opening 327 of the cavity 326. Additionally, moving the flange 350 towards the opening 327 by the spring device 342 causes a portion of the indicator device 334, including the fourth end 338 of the indicator device 334, to move out of the cavity 326 of the housing 310. For example, the disengagement of the indicator device from the thermal component 344 of the thermal spring system 340 allows the spring device 342 of the thermal spring system 340 to move the indicator device 334 from a first position to a different, second position.
In one example, the thermal component 344 and/or the spring device 342 may be manufactured of material(s) that have one or more properties that are similar to one or more properties of one or more layers of the first and/or second surfaces 306, 308 in order to indicate when the first and/or second surfaces 306, 308 may be exposed to thermal energy that may cause damage to the one or more layers. For example, the first layer 602 (e.g., the first layer of epoxy) and/or the third layer 606 (e.g., the second layer of epoxy) may be at risk of failing and/or may fail if the first and/or third layers 602, 606 are exposed to temperatures that exceed the designated threshold, but an operator of the aircraft system 100 may be unaware that the first and third layers were exposed to temperatures that exceed one or more design limitations. The thermal component 344 may be manufactured of a material that has the same and/or similar properties as the first and third layers 602, 606 in order to provide a visual indication to the operator of the aircraft system 100 that the first and third layers 602, 606 may have failed, may be at risk of failure, may require repair and/or replacement, or the like. For example, exposing the thermal component 344 and the first and third layers 602, 606 to temperatures that exceed the designated threshold may cause the material properties of the thermal component 344 and the first and third layers 602, 606 to change. Changing of the properties of the thermal component 344 causes the third end 336 of the indicator device 334 to disengage from the thermal component 344 and extend out of the cavity 326 by a distance 356 and be visible, such as to an operator doing a visual inspection of the nacelle 200 and/or propulsion system 108 of the aircraft system 100.
In one or more examples, the thermal component 344 may be manufactured of a material that has one or more material properties that change (e.g., return to) responsive to the thermal component 344 no longer being exposed to the temperatures exceeding the designated threshold. For example, subsequent to the indicator device 334 disengaging from the thermal component 344 and the indicator device 334 extending out of the cavity 326 (e.g., and visible to an operator, an inspection system such as a camera, or the like), the indicator device 334 may be able to re-engage with the thermal component 344. For example, the fourth end 338 of the indicator device 334 may be moved in the second direction 354 to compress the spring device 342 until the retaining features 348 re-engage with the third end 336 of the indicator device 334. For example, the thermal detection assembly 300 may be able to be used for one or more cycles of engaging and disengaging the indicator device 334 with the thermal component 344. In another example, the thermal detection assembly 300 may only be a single-use assembly such that the indicator device 334 may only move from an engaged position (e.g., shown in
In one or more examples, the aircraft system 100 may include plural thermal detection assemblies disposed at one or more different locations within the nacelle of the propulsion system 108. For example, plural thermal detection assemblies may be coupled with one or more different surfaces of the nacelle, surfaces of components of the propulsion system (e.g., the engine, combustor, fan ducts, or the like). The plural thermal detection assemblies may be positioned in a pattern or array along one or more surfaces, may be strategically positioned based on anticipated thermal damage due to thermal energy generated by the propulsion system, strategically positioned based on different materials of the nacelle and/or propulsion system (e.g., may be closed to and/or operably coupled with materials of the nacelle that are more easily damaged due to exposure to thermal energy relative to other materials that are less easily thermally damaged), or the like.
In one or more examples, the thermal component of different thermal detection assemblies may be manufactured of different materials. For example, a first group of thermal detection assemblies may be manufactured with a thermal component that is manufactured of a first type of solder material, and a second group of thermal detection assemblies may be manufactured with a thermal component that is manufactured of a second type of solder material. The first group of detection assemblies may be strategically positioned within the propulsion system proximate to materials of the propulsion system that have the same and/or similar material properties as the first type of solder. Additionally, the second group of detection assemblies may be strategically positioned within the propulsion system proximate to materials of the propulsion system that have the same and/or similar material properties as the second type of solder.
Like the thermal detection assembly 300 shown in
The thermal detection assembly 700 includes an indicator device 734 that is disposed within a cavity 726 of the housing 710. The cavity 726 has an opening 727 at an exterior surface 709 of the second surface 708. The indicator device 734 extends between a third end 736 disposed within the cavity 726 and a fourth end 738 disposed proximate to the opening 727 of the cavity 726.
The thermal detection assembly 700 includes a thermal spring system 740 that is disposed within the cavity 726 of the housing 710. The thermal spring system 740 is engaged with the third end 736 of the indicator device 734 and controls a position of the indicator device 734 within the cavity 726. In the illustrated example, the thermal spring system 740 includes a spring device 742. The spring device 742 may be a compression spring that is positioned within the cavity 726 such that the indicator device 734 is positioned between the spring device 742 and the opening 727 of the cavity.
In one or more examples, the spring device 742 may be designed and/or manufactured to have a varying spring constant. For example, the spring device 742 may have a first spring constant prior to exposure of the spring device 742 to temperatures exceeding a designated threshold, and a different, second spring constant responsive to exposure of the spring device 742 to temperatures exceeding the designated threshold. The spring device 742 may be manufactured to have the varying spring constant such that the spring constant changes responsive to exposure to temperatures that also change one or more characteristics of one or more layers of the first and/or second surfaces 706, 708, respectively, of the aircraft system 100.
In the illustrated example shown in
Alternatively, in the illustrated example shown in
In one or more examples, the spring device 742 may be designed and/or manufactured of a material that allows the spring constant to change from the second spring constant (e.g., with the spring having the longer length, shown in
Further, the disclosure comprises examples according to the following clauses:
Clause 1: an assembly, comprising:
Clause 2: the assembly of clause 1, wherein the surface of the power system includes plural layers, wherein one or more characteristics of one or more of the plural layers are configured to change responsive to the plural layers being exposed to the temperature exceeding the designated threshold.
Clause 3: the assembly of clauses 1 or 2, wherein the thermal spring system is configured to disengage from a second portion of the indicator device responsive to the one or more characteristics of the thermal spring system changing, wherein the thermal spring system is configured to encourage the first portion of the indicator device to move out of the cavity of the housing responsive to the thermal spring system disengaging from the second portion of the indicator device.
Clause 4: the assembly of clauses 1-3, wherein the surface of the power system includes plural layers operably coupled with each other, wherein the thermal spring system is manufactured of one or more materials, wherein at least one of the plural layers and at least one of the one or more materials of the thermal spring system have a common material property.
Clause 5: the assembly of clauses 1-4, wherein the one or more characteristics of the thermal spring system are configured to change responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold for a determined length of the time.
Clause 6: the assembly of clauses 1-5, wherein the thermal spring system includes a spring device and a thermal component, the indicator device extending between a third end and a fourth end, wherein the spring device is configured to be operably coupled with the indicator device at a location between the third end and the fourth end of the indicator device, and the thermal component is configured to be operably coupled with the third end of the indicator device.
Clause 7: the assembly of clause 6, wherein the spring device is configured to be in a compressed state prior to the thermal spring system being exposed to the temperature exceeding the designated threshold, and the spring device is configured to be in a non-compressed state responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold.
Clause 8: the assembly of clause 6, wherein the thermal component has a first shape prior to the thermal spring system being exposed to the temperature exceeding the designated threshold, and the thermal component is configured to have a different, second shape responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold.
Clause 9: the assembly of clauses 1-5, wherein the thermal spring system includes a spring device, wherein one or more characteristics of the spring device are configured to change responsive to the spring device being exposed to the temperature exceeding the designated threshold.
Clause 10: the assembly of clauses 1-9, wherein the spring device has s first spring constant prior to the spring device being exposed to the temperature exceeding the designated threshold, and the spring device is configured to have a different, second spring constant responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold.
Clause 11: the assembly of clauses 1-10, wherein the power system is an aircraft system, and the surface of the power system is a surface of a propulsion system of the aircraft system.
Clause 12: An assembly, comprising:
Clause 13: the assembly of clause 12, wherein the one or more characteristics of the thermal component are configured to change responsive to the thermal component being exposed to the temperature exceeding the designated threshold for a determined length of time.
Clause 14: the assembly of clauses 12 or 13: wherein the third end of the indicator device is configured to disengage from the thermal spring system, wherein the spring device is configured to encourage the fourth end of the indicator device to move out of the cavity of the housing responsive to the third end of the indicator device disengaging from the thermal component of the thermal spring system.
Clause 15: the assembly of clauses 12-14, wherein the surface of the power system includes plural layers, wherein one or more characteristics of one or more of the plural layers are configured to change responsive to the plural layers being exposed to the temperature exceeding the designated threshold.
Clause 16: the assembly of clauses 12-15, wherein the spring device is configured to be in a compressed state prior to the thermal component being exposed to the temperature exceeding the designated threshold, and the spring device is configured to be in a non-compressed state responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold.
Clause 17: the assembly of clauses 12-16, wherein the thermal component has a first shape prior to the thermal component being exposed to the temperature exceeding the designated threshold, and the thermal component is configured to have a different, second shape responsive to the thermal spring system being exposed to the temperature exceeding the designated threshold.
Clause 18: the assembly of clauses 12-17, wherein the surface of the power system includes plural layers operably coupled with each other, wherein a material of the thermal component of the thermal spring system and at least one of the plural layers have a common material property.
Clause 19: the assembly of clauses 12-18, wherein the power system is an aircraft system, and wherein the surface is a surface of a propulsion system of the aircraft system.
Clause 20: a thermal detection assembly, comprising:
While various spatial and directional terms, such as top, bottom, lower, mid, lateral, horizontal, vertical, front and the like can be used to describe examples of the present disclosure, it is understood that such terms are merely used with respect to the orientations shown in the drawings. The orientations can be inverted, rotated, or otherwise changed, such that an upper portion is a lower portion, and vice versa, horizontal becomes vertical, and the like.
As used herein, a structure, limitation, or element that is “configured to” perform a task or operation is particularly structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For purposes of clarity and the avoidance of doubt, an object that is merely capable of being modified to perform the task or operation is not “configured to” perform the task or operation as used herein.
It is to be understood that the above description is intended to be illustrative, and not restrictive. For example, the above-described examples (and/or aspects thereof) can be used in combination with each other. In addition, many modifications can be made to adapt a particular situation or material to the teachings of the various examples of the disclosure without departing from their scope. While the dimensions and types of materials described herein are intended to define the aspects of the various examples of the disclosure, the examples are by no means limiting and are exemplary examples. Many other examples will be apparent to those of skill in the art upon reviewing the above description. The scope of the various examples of the disclosure should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims and the detailed description herein, the terms “including” and “in which” are used as the plain-English equivalents of the respective terms “comprising” and “wherein.” Moreover, the terms “first,” “second,” and “third,” etc. are used merely as labels, and are not intended to impose numerical requirements on their objects. Further, the limitations of the following claims are not written in means-plus-function format and are not intended to be interpreted based on 35 U.S.C. § 112(f), unless and until such claim limitations expressly use the phrase “means for” followed by a statement of function void of further structure.
This written description uses examples to disclose the various examples of the disclosure, including the best mode, and also to enable any person skilled in the art to practice the various examples of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the various examples of the disclosure is defined by the claims, and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if the examples have structural elements that do not differ from the literal language of the claims, or if the examples include equivalent structural elements with insubstantial differences from the literal language of the claims.
