Patent Application
20230278279
The present disclosure relates generally to additive manufacturing methods, systems, and apparatuses and, more particularly, to methods, systems, and apparatuses for additive manufacturing of composite components.
Various components, for instance, vehicle components, are manufactured from composite materials. Traditional composite manufacturing techniques includes laying up layers of resin-soaked fiber on a mold, compressing the layered structure to diminish voids, and allowing the structure to cure. Subsequently, various processing techniques may be utilized to shape the cured combination of resin and fiber. Additive manufacturing techniques have accelerated the speed and increased the ready prototyping of other types of components. However, these techniques have difficulty processing composite materials, limiting the availability of additive manufacturing technology when constructing components from composite materials.
A method of additively manufacturing a composite component is provided. The method may include introducing a polymer into a probe. The method may include introducing a fiber into the probe. The method may include mixing the polymer and the fiber by a screw feeder disposed inside the probe to form a fiber-matrix mixture and extruding the fiber-matrix mixture from a nozzle of the probe to provide an extruded fiber-matrix body at the nozzle of the probe. The method may further include contacting the extruded fiber-matrix body to a workpiece supported by a build plate and moving the extruded fiber-matrix body relative to the workpiece to friction-stir additively manufacture a layer of the workpiece from the extruded fiber-matrix body by incorporating at least a portion of the extruded fiber-matrix body integrally into the workpiece to form the composite component.
In various instances the fiber is chopped carbon fiber. The extruded fiber-matrix body may at least partially harden prior to the contacting the extruded fiber-matrix body to the workpiece. The moving the extruded fiber-matrix body relative to the workpiece may include translating the build plate supporting the workpiece relative to the probe. The moving the extruded fiber-matrix body relative to the workpiece may include translating the probe relative to the build plate supporting the workpiece. The moving the extruded fiber-matrix body relative to the workpiece may include rotating the probe relative to the workpiece. The moving the extruded fiber-matrix body relative to the workpiece may include rotating the probe relative to the workpiece while translating the build plate supporting the workpiece relative to the probe. The moving the extruded fiber-matrix body relative to the workpiece may include rotating the probe relative to the workpiece while translating the probe relative to the build plate supporting the workpiece.
In various embodiments, at least one of the contacting and the moving generates heat causing the extruded fiber-matrix body and the workpiece to at least partially melt and weld together. Moreover, the method may include repeating the moving the extruded fiber-matrix body relative to the workpiece to friction-stir additively manufacture a subsequent layer atop the layer. The composite component may be a structural component of an aircraft.
An additive manufacturing system to manufacture a composite component is provided the system may include a probe. The probe may include a sleeve defining a cavity. The probe may include a first inlet duct in fluid communication with the cavity to provide at least a portion of a fiber-matrix mixture to the cavity. The probe may include a screw feeder disposed at least partially within the sleeve, and a nozzle. The screw feeder is configured to rotate causing the fiber-matrix mixture to translate towards and out the nozzle as an extruded fiber-matrix body. The system may also include a build plate adjacent the probe and at least one actuator configured to move at least one of the build plate and the probe to weld at least a portion of the extruded fiber-matrix body to a workpiece on the build plate by friction-stir additive manufacturing to form the composite component.
In various embodiments, the first inlet duct provides both the matrix and the fiber to the cavity. The probe may include a second inlet duct. The first inlet duct may provide the matrix to the cavity and the second inlet duct may provide the fiber to the cavity. The fiber may be a chopped carbon fiber. The matrix may be a polymer.
The at least one actuator may include a first actuator configured to rotate the probe and a second actuator configured to translate the probe relative to the build plate. In various instances, the at least one actuator includes a first actuator configured to rotate the probe and a second actuator configured to translate the build plate relative to the probe. The system may also have a controller operable to control the actuator according to a computer instruction.
Finally, the disclosure herein provides a method of additively manufacturing a composite component by an additive manufacturing system, the system including (i) a probe including a sleeve defining a cavity and at least one inlet in fluid communication with the cavity to provide a carbon fiber and a polymer of a fiber-polymer mixture to the cavity, (ii) a screw feeder disposed at least partially within the sleeve, and (iii) a nozzle, wherein the screw feeder is configured to rotate causing the carbon fiber and the polymer to mix to form the fiber-polymer mixture and to translate towards and out the nozzle as an extruded fiber-polymer body. The method may include introducing the polymer into the probe, introducing the fiber into the probe, and extruding the fiber-polymer mixture from the nozzle of the probe to provide the extruded fiber-polymer body at the nozzle of the probe. The method may include contacting the extruded fiber-polymer body to a workpiece supported by a build plate, and moving at least one of the extruded fiber-polymer body and the workpiece to friction-stir additively manufacture a layer of the workpiece from the extruded fiber-polymer body by incorporating at least a portion of the extruded fiber-polymer body integrally into the workpiece to form the composite component.
The forgoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated herein otherwise. These features and elements as well as the operation of the disclosed embodiments will become more apparent in light of the following description and accompanying drawings.
The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the following detailed description and claims in connection with the following drawings. While the drawings illustrate various embodiments employing the principles described herein, the drawings do not limit the scope of the claims.
The following detailed description of various embodiments herein makes reference to the accompanying drawings, which show various embodiments by way of illustration. While these various embodiments are described in sufficient detail to enable those skilled in the art to practice the disclosure, it should be understood that other embodiments may be realized and that changes may be made without departing from the scope of the disclosure. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation. Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, connected, or the like may include permanent, removable, temporary, partial, full or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. It should also be understood that unless specifically stated otherwise, references to “a,” “an” or “the” may include one or more than one and that reference to an item in the singular may also include the item in the plural. Further, all ranges may include upper and lower values and all ranges and ratio limits disclosed herein may be combined.
Frequently, components are desired to be manufactured from composite materials. However, prior additive manufacturing techniques involve the squeezing of molten polymers in a layer by layer fashion, building up a part. During melting, discontinuities arise or debonding occurs between the fibers and the matrix material. Other prior manufacturing techniques involve non-additive manufacturing technologies, such as layer-by-layer manual lay up of fiber mats in the matrix, followed by application of compression during curing. Such techniques are time intensive and lack the flexibility of additive manufacturing technologies.
Systems, methods, and apparatuses are disclosed herein to implement friction stir additive manufacturing for the manufacturing of composite components. These systems, methods, and apparatuses overcome the limitations of prior techniques by making available the speed and flexibility of additive manufacturing technology without the associated discontinuities and debonding arising between fibers and the matrix during melting processes. Consequently, bonding of fiber and matrix retains resiliency similar to or better than traditional composite manufacturing processes, while enjoying the speed and flexibility of additive manufacturing processes. As a result, composite components manufactured as provided herein may be utilized as structural components of aircraft and other vehicles.
Referring now to
Directing attention to
For instance, the sleeve 230 may hold a combination of a (i) matrix material and (ii) a fiber material. In various embodiments, the matrix material may be a resin and/or a polymer material. In various embodiments, the fiber material may be carbon fiber, fiberglass, aramid fiber, or the like. In various instances, the fiber material is short chopped carbon fiber. The fiber material may be provided to the cavity 235 by feeding from a spool, or may be provided in short, chopped configuration.
The probe 120 may also have a first inlet duct 240. The first inlet duct 240 may be in fluid communication with the cavity 235 and may receive at least a portion of the fiber-matrix mixture and admit the portion of the fiber-matrix mixture to the cavity 235.
In various instances, the first inlet duct 240 of the probe 120 provides both matrix and fiber to the cavity 235. However, in further instances, a second inlet duct 245 is provided. The second inlet duct 245 may be in fluid communication with the cavity 235 and may receive at least a portion of the fiber-matrix mixture and admit the portion of the fiber-matrix mixture to the cavity 235. For instance, the first inlet duct 240 may admit matrix to the cavity 235 and the second inlet duct 245 may admit fiber to the cavity 235. The matrix may be a polymer and the fiber may be a chopped carbon fiber.
The probe 120 may have a screw feeder 220. The screw feeder 220 may comprise an auger. The screw feeder 220 may be disposed at least partially within the sleeve 230. The screw feeder 220 may agitate the fiber-matrix mixture in the cavity 235 to facilitate mixing and even distribution of the fiber throughout the matrix. The screw feeder 220 may cause the fiber-matrix mixture to flow from the cavity 235 toward a nozzle 210 disposed at an end of the sleeve 230 for extrusion therefrom. Thus, the screw feeder 220 may be configured to rotate causing the fiber-matrix mixture to translate toward and out the nozzle 210 as an extruded fiber-matrix body 250.
The probe 120 may include the nozzle 210 mentioned above. The nozzle 210 may comprise an aperture fitted to an end of the sleeve 230 to receive fiber-matrix mixture from the cavity 235 and shape the fiber-matrix mixture into an extruded fiber-matrix body 250.
Adjacent to the probe 120, and as depicted in
Directing attention now to
In various instances of the method, the fiber is a chopped carbon fiber. Moreover, the extruded fiber-matrix body may at least partially harden prior to the contacting the extruded fiber-matrix body to the workpiece. In various instances, the moving the extruded fiber-matrix body relative to the workpiece comprises translating the build plate supporting the workpiece relative to the probe. The moving the extruded fiber-matrix body relative to the workpiece may also include rotating the probe relative to the workpiece. Thus, the moving the extruded fiber-matrix body relative to the workpiece may include rotating the probe relative to the workpiece while translating the build plate supporting the workpiece relative to the probe. At least one of the contacting and the moving generates heat causing the extruded fiber-matrix body and the workpiece to at least partially melt and weld together. The moving of the extruded fiber-matrix body may occur repeatedly relative to the workpiece and along the same first path to friction-stir additively manufacture subsequent layer(s).
Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the disclosure. The scope of the disclosure is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C. Different cross-hatching is used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
Systems, methods, and apparatus are provided herein. In the detailed description herein, references to “one embodiment,” “an embodiment,” “various embodiments,” etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112(f) unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises,” “comprising,” or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Finally, it should be understood that any of the above described concepts can be used alone or in combination with any or all of the other above described concepts. Although various embodiments have been disclosed and described, one of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. Accordingly, the description is not intended to be exhaustive or to limit the principles described or illustrated herein to any precise form. Many modifications and variations are possible in light of the above teaching.
