US20140162533A1 - Cutting tools and machining methods using cutting tools - Google Patents
Cutting tools and machining methods using cutting tools Download PDFInfo
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- US20140162533A1 US20140162533A1 US14/182,144 US201414182144A US2014162533A1 US 20140162533 A1 US20140162533 A1 US 20140162533A1 US 201414182144 A US201414182144 A US 201414182144A US 2014162533 A1 US2014162533 A1 US 2014162533A1
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- cutting surface
- cutting
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- cutting tool
- filler
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24D—TOOLS FOR GRINDING, BUFFING OR SHARPENING
- B24D7/00—Bonded abrasive wheels, or wheels with inserted abrasive blocks, designed for acting otherwise than only by their periphery, e.g. by the front face; Bushings or mountings therefor
- B24D7/18—Wheels of special form
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
- G05B19/4097—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/22—Single-purpose machines or devices for particular grinding operations not covered by any other main group characterised by a special design with respect to properties of the material of non-metallic articles to be ground
Definitions
- the disclosure generally relates to producing the shimming process where fillers are applied to assembly process of filling gaps in mechanical structures.
- There are two object classifications for filling gaps in structure shims which are made from peelable laminated materials and fillers which are precisely machined form solid monolithic materials. More particularly, the disclosure relates to an automated process of defining, producing and tracking the status of custom fillers produced on demand for immediate installation on an inline flow production line when the full design definition of a structure resides in a CAD/CAM system.
- a conventional method of defining and producing custom fillers may include measuring gaps between parts using feeler gauges, capacitive gap measuring instrumentation or computer/laser based scanning measurement systems.
- the gap measurement data may be documented and delivered via entry into a series of software capabilities which process the gap measurements, updated digital definitions of the fillers and generates portable Machine Control Data (MCD).
- MCD Machine Control Data
- the MCD is downloaded to a central server which delivers the MCD to a Computer Numerical Control (CNC) controlled machine tool.
- CNC machine tool machines the filler using cutting tool configurations which are specific to the filler and its material being manufactured. Following the machining of the filler on its surface and profile, it is de-burred and the filler marked with its identification to facilitate its installation in the structure.
- the conventional filler definition and elements of the production process may be paper-based.
- the full design definition of the structure which is being fabricated may be digitally defined and electronically stored and processed in a CAD/CAM system such as CATIA V5 and Enovia.
- the design definition of an aircraft may be defined by engineers from many companies which design various sections of the aircraft. That digital definition establishes and maintains the full definition of all components in their spatial relationship—in aircraft coordinates. The fabricated aircraft sections undergo final assembly at an aircraft assembly plant.
- the disclosure is generally directed to an automated filler production method.
- the automated filler production method is suitable for defining, producing and tracking the status of custom fillers on demand for immediate installation on an inline flow production line when the full design definition of a structure resides in a CAD/CAM system.
- the automated filler production method may include obtaining gap measurement data by measuring a gap between component parts of a structure; capturing and delivering the gap measurement data to a data collector function; generating a new CAD solid model definition with the gap measurements, creating portable Machine Control Data (MCD) using the CAM function of the CADCAM system, delivering the MCD to a filler machining center via a networked server, and machining a filler from a metallic or non-metallic composite materials using the MCD.
- MCD Machine Control Data
- the disclosure is further generally directed to a method of applying a diamond abrasive cutting tool configuration to the fabrication of fillers from large sheets of non-metallic composite material.
- An illustrative embodiment of the method includes providing a cutting tool including a tool shank, a tool head attached to the tool shank and individual diamond abrasive cutting edges attached to the tool head; providing a non-metallic composite filler materials; and machining a filler from the filler from larger sheets of material using the cutting tool.
- FIG. 1 is a flow diagram of an illustrative embodiment of the automated filler production method.
- FIG. 1A is a flow diagram of an illustrative embodiment of a method of applying a diamond abrasive cutting tool configuration which enables unique gauge reduction material removal capabilities for non-metallic composite materials.
- FIGS. 2 and 2A are side and end views, respectively, of a diamond abrasive cutting tool configuration which enables the unique gauge reduction material removal capabilities of non-metallic composite materials in implementation of the automated filler production method.
- FIGS. 3 and 3A are side and end views, respectively, of an alternative diamond abrasive cutting tool configuration.
- FIGS. 4 and 4A are side and end views, respectively, of another alternative diamond abrasive cutting tool configuration.
- FIGS. 5 and 5A are side and end views, respectively, of still another alternative diamond abrasive cutting tool configuration.
- FIG. 6 is a flow diagram of an aircraft production and service methodology.
- FIG. 7 is a block diagram of an aircraft.
- a solid model of the structure including the filler solid model, may be updated with the population of filler CAD definition carried out in block 104 .
- An automated update of the NC (Numeric control) program for the machining process may be generated from the updated solid model and the creation of portable Machine Control Data (MCD) may be accomplished.
- An automated download of the MCD to a central server may be accomplished.
- a status update to note availability of the MCD may be accomplished.
- changes in the status of the filler through out its fabrication process may be logged and reported as required.
- deburring of the filler may be carried out and the filler may be marked for incorporation into the structure.
- the filler may be immediately installed on an inline flow production line or retained for future use depending on the production strategy.
- the method of the disclosure may be implemented to define, produce, and ascertain and distribute the status of fillers that are custom-produced on demand for immediate installation on an inline flow production line in applications in which the full design requirement of an aircraft or other structure resides solely in a CAD/CAM system.
- the method 100 may support 5-axis machine tools, 3D engineering definition of an aircraft or other structure, automatic capture of gap measurement data, automated delivery of the gap measurement data, machining of composite materials, automated generation of the Machine Control Data (MCD), delivery of the MCD to the machine tool and automated filler status collection, communication, and storage for future performance and process analysis.
- MCD Machine Control Data
- FIG. 1A a flow diagram 100 a of an illustrative embodiment of a method of applying a diamond abrasive cutting tool configuration which enables unique gauge reduction and complex surface generation via material removal techniques of non-metallic composite materials is shown.
- the flow diagram 100 a may be implemented as part of block 110 of the flow diagram 100 which was heretofore described with respect to FIG. 1 .
- a cutting tool having a tool shank, an attached material removal cutting head on the tool shank and diamond abrasive cutting material applied on all material removal surfaces including grooves formed to facilitate the material removal process is provided.
- the cutting tool may have one of the cutting tool configurations which are described with respect to FIGS. 2-5A herein below.
- a non-metallic filler material sheet is provided.
- the non-metallic filler material sheet may be a composite material, such as CFRP and GFRP.
- a filler may be fabricated from the filler material sheet using the cutting tool provided in block 102 a. It should be noted that a filler or multiple instances of the filler may be located in a single sheet of material. Additionally, multiple filler configurations may grouped in a single sheet of filler material and sequentially without interruption of the process to load material or to unload material and/or fillers.
- FIGS. 2-5A of the drawings various cutting tool configurations for production of fillers according to the method of the disclosure are shown.
- the cutting tool configurations shown in FIGS. 2-5A may be implemented in block 110 of the flow diagram 100 which was heretofore described with respect to FIG. 1 and in the flow diagram 100 a which was heretofore described with respect to FIG. 1A .
- Application of the cutting tool configurations may enable the unique gauge reduction and complex surface generation via material removal capabilities of the non-metallic composite materials (such as GFRP and CFRP).
- the cutting tool 1 may include a generally elongated tool shank 2 having an attached material removal cutting head 3 on the tool shank 2 .
- the attached material removal cutting head 3 may have a generally semispherical proximal head portion 3 a and a generally semispherical cutting surface 3 b which extends from the proximal head portion 3 a.
- Diamond abrasive is applied on the material removal surfaces including grooves formed to facilitate the material removal process 4 may extend along the cutting surface 3 b of the attached material removal cutting head 3 .
- the grooves formed to facilitate the material removal process 4 may be generally arranged in helical or straight patterns on the cutting surface 3 b to facilitate the material removal process.
- the attached material removal cutting head 3 of the cutting tool lb may include a generally cylindrical proximal head portion 3 a and a generally cylindrical side cutting surface 3 b with a generally planar end cutting surface 3 c.
- Diamond abrasive coated grooves formed to facilitate the material removal process 4 may extend along the side cutting surface 3 b, the radiused cutting surface edge 3 d and the end cutting surface 3 c.
- the attached material removal cutting head 3 of the cutting tool 1 c may include a generally cylindrical proximal head portion 3 a and a generally cylindrical side cutting surface 3 b with an annular cutting surface edge 3 d.
- the material removal cutting head 3 may have a cutting surface bore 3 e to facilitate material removal.
- Diamond abrasive cutting ridges 4 may extend along the side cutting surface 3 b and onto the cutting surface edge 3 d of the material removal cutting head 3 and into the area defined by 3 e.
- embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 78 as shown in FIG. 6 and an aircraft 94 as shown in FIG. 7 .
- exemplary method 78 may include specification and design 80 of the aircraft 94 and material procurement 82 .
- component and subassembly manufacturing 84 and system integration 86 of the aircraft 94 takes place.
- the aircraft 94 may go through certification and delivery 88 in order to be placed in service 90 .
- the aircraft 94 may be scheduled for routine maintenance and service 92 (which may also include modification, reconfiguration, refurbishment, and so on).
- Each of the processes of method 78 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer).
- a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors
- a third party may include without limitation any number of vendors, subcontractors, and suppliers
- an operator may be an airline, leasing company, military entity, service organization, and so on.
- the aircraft 94 produced by exemplary method 78 may include an airframe 98 with a plurality of systems 96 and an interior 116 .
- high-level systems 96 include one or more of a propulsion system 118 , an electrical system 120 , a hydraulic system 122 , and an environmental system 124 . Any number of other systems may be included.
- the assembly and/or installation requires filler to assure proper assembly and installation procedure as defined by the product design criteria.
- an aerospace example is shown, the principles of the invention may be applied to other industries, such as the automotive industry.
- the apparatus embodied herein may be employed during any one or more of the stages of the production and service method 78 .
- components or subassemblies corresponding to production process 84 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 94 is in service.
- one or more apparatus embodiments may be utilized during the production stages 84 and 86 , for example, by substantially expediting assembly of or reducing the cost of an aircraft 94 .
- one or more apparatus embodiments may be utilized while the aircraft 94 is in service, for example and without limitation, to maintenance and service 92 .
Abstract
Cutting tools and machining methods using cutting tools are disclosed. An example cutting tool comprises a shank and a head on the shank, the head comprising a diamond abrasive-coated cutting surface, the cutting head having grooves interrupting the cutting surface and extending from the cutting surface toward an axis of rotation of the head, the cutting surface having a substantially constant radius.
Description
- This patent arises from a continuation of U.S. patent application Ser. No. 12/987,364, filed Jan. 10, 2011, which claims priority to Provisional U.S. Patent Application No. 61/412,522 filed Nov. 11, 2010. The entireties of U.S. patent application Ser. No. 12/987,364 and Provisional U.S. Patent Application No. 61/412,522 are incorporated herein by reference.
- The disclosure generally relates to producing the shimming process where fillers are applied to assembly process of filling gaps in mechanical structures. There are two object classifications for filling gaps in structure, shims which are made from peelable laminated materials and fillers which are precisely machined form solid monolithic materials. More particularly, the disclosure relates to an automated process of defining, producing and tracking the status of custom fillers produced on demand for immediate installation on an inline flow production line when the full design definition of a structure resides in a CAD/CAM system.
- In the fabrication of mechanical structures such as aircraft, it may be necessary to introduce fillers between interfacing surfaces of the component parts to assure proper and safe structure. Fillers (also known as shims) are pieces of metallic or non-metallic materials which are placed in gaps between the component parts to compensate for dimensional variations or tolerance buildup between the parts. In the aircraft industry, fillers may be used in fitting and joining major structural sections to one another and throughout substructures as they are built-up into a full aircraft structure. The use of fillers may compensate for dimensional variation between parts or bring parts into proper alignment.
- A conventional method of defining and producing custom fillers may include measuring gaps between parts using feeler gauges, capacitive gap measuring instrumentation or computer/laser based scanning measurement systems. The gap measurement data may be documented and delivered via entry into a series of software capabilities which process the gap measurements, updated digital definitions of the fillers and generates portable Machine Control Data (MCD). The MCD is downloaded to a central server which delivers the MCD to a Computer Numerical Control (CNC) controlled machine tool. The CNC machine tool machines the filler using cutting tool configurations which are specific to the filler and its material being manufactured. Following the machining of the filler on its surface and profile, it is de-burred and the filler marked with its identification to facilitate its installation in the structure.
- In previous applications, the conventional filler definition and elements of the production process may be paper-based. In some production schemes, however, the full design definition of the structure which is being fabricated may be digitally defined and electronically stored and processed in a CAD/CAM system such as CATIA V5 and Enovia. For large-scale production of aircraft, the design definition of an aircraft may be defined by engineers from many companies which design various sections of the aircraft. That digital definition establishes and maintains the full definition of all components in their spatial relationship—in aircraft coordinates. The fabricated aircraft sections undergo final assembly at an aircraft assembly plant.
- In current aircraft production schemes, an automated process of defining, producing and tracking the status of custom fillers on demand for immediate installation on an inline flow production line when the full design definition of a structure resides in a CAD/CAM system is required.
- The disclosure is generally directed to an automated filler production method. The automated filler production method is suitable for defining, producing and tracking the status of custom fillers on demand for immediate installation on an inline flow production line when the full design definition of a structure resides in a CAD/CAM system. An illustrative embodiment of the method includes obtaining gap measurement data by measuring a gap between component parts of a structure, delivering the gap measurement data to a data collector function, updating the CAD solid model of the filler (in its relationship in the structure) using the gap measurement data, creating portable Machine Control Data (MCD) using the CAM function of the CADCAM system, delivering the MCD to a filler machining center via a networked server, and machining a filler from a metallic or non-metallic composite materials using the MCD.
- In some embodiments, the automated filler production method may include obtaining gap measurement data by measuring a gap between component parts of a structure; capturing and delivering the gap measurement data to a data collector function; generating a new CAD solid model definition with the gap measurements, creating portable Machine Control Data (MCD) using the CAM function of the CADCAM system, delivering the MCD to a filler machining center via a networked server, and machining a filler from a metallic or non-metallic composite materials using the MCD.
- The disclosure is further generally directed to a method of applying a diamond abrasive cutting tool configuration to the fabrication of fillers from large sheets of non-metallic composite material. An illustrative embodiment of the method includes providing a cutting tool including a tool shank, a tool head attached to the tool shank and individual diamond abrasive cutting edges attached to the tool head; providing a non-metallic composite filler materials; and machining a filler from the filler from larger sheets of material using the cutting tool.
- The features, functions, and advantages that have been discussed can be achieved independently in various embodiments of the present disclosure or may be combined in yet other embodiments further details of which can be seen with reference to the following description and drawings.
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FIG. 1 is a flow diagram of an illustrative embodiment of the automated filler production method. -
FIG. 1A is a flow diagram of an illustrative embodiment of a method of applying a diamond abrasive cutting tool configuration which enables unique gauge reduction material removal capabilities for non-metallic composite materials. -
FIGS. 2 and 2A are side and end views, respectively, of a diamond abrasive cutting tool configuration which enables the unique gauge reduction material removal capabilities of non-metallic composite materials in implementation of the automated filler production method. -
FIGS. 3 and 3A are side and end views, respectively, of an alternative diamond abrasive cutting tool configuration. -
FIGS. 4 and 4A are side and end views, respectively, of another alternative diamond abrasive cutting tool configuration. -
FIGS. 5 and 5A are side and end views, respectively, of still another alternative diamond abrasive cutting tool configuration. -
FIG. 6 is a flow diagram of an aircraft production and service methodology. -
FIG. 7 is a block diagram of an aircraft. - The following detailed description is merely exemplary in nature and is not intended to limit the described embodiments or the application and uses of the described embodiments. As used herein, the word “exemplary” or “illustrative” means “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” or “illustrative” is not necessarily to be construed as preferred or advantageous over other implementations. All of the implementations described below are exemplary implementations provided to enable persons skilled in the art to practice the disclosure and are not intended to limit the scope of the claims. Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary or the following detailed description.
- The disclosure is generally directed to an integrated automated filler production method from gap measurement, filler definition, NC (Numerical Control) programming, filler machining (regardless of the material type), delivery of fillers for the assembly of a structure such as a composite aircraft, and filler status tracking The method may be embodied in software which enables integration of these processes and assures the quality of the finished filler. The disclosure is further generally directed to the configuration, features and method of application of a diamond abrasive cutting tool configuration which enables the unique gauge reduction material removal capabilities of non-metallic composite materials (GFRP and CFRP). Additionally, the methods may enable the production of multiple metallic material fillers utilizing their unique required cutter configurations.
- Referring initially to
FIG. 1 , a flow diagram 100 of an illustrative embodiment of the automated filler production method is shown. The method 100 may be implemented in the integration of fillers during the production of aircraft or other structures. In block 102, measurement of a gap between component parts of the aircraft or other structure may be made. The gap measurement may be made by multiple methods—mechanical, electrical, or computer based, for example and without limitation. The accuracy of the gap measurement capture is assured through a graphical user interface for the data collection function. - In block 104, the gap measurement data obtained in block 102 may be captured and delivered to a data collector function which is adapted to display and assess all measurement points and then to deliver the properly formatted measurement data to a proper server location. A “watcher” function transmit notifications to personnel who are responsible for supporting the filler machining process that new measurement data has arrived and if the gap measurements meet specified design criteria. Automated entry of the gap measurement data to the data collector function may be made via interfaces with the measurement equipment. The gap measurement data may be transmitted to the data collector function via a factory wireless network or via direct hardwired network connection. Upon receipt of the gap measurement file, an automatic population of a filler CAD definition with the measurement data may occur.
- In block 106, a solid model of the structure, including the filler solid model, may be updated with the population of filler CAD definition carried out in block 104. An automated update of the NC (Numeric control) program for the machining process may be generated from the updated solid model and the creation of portable Machine Control Data (MCD) may be accomplished. An automated download of the MCD to a central server may be accomplished. In block 108, a status update to note availability of the MCD may be accomplished.
- In block 110, a direct delivery of the MCD to a machining center may be generated such as by request from a machinist and the filler may be machined from a larger sheet of material. In some embodiments, the sheet of material from which the filler is machined may be a composite material in the form of Glass Fiber Re-enforced Plastic (GFRP) or Carbon Fiber Re-enforced Plastic (CFRP) or other non-metallic materials. In other embodiments, the material sheet from which the filler is machined may be metallic in nature. If necessary, machining of the filler may be shifted within the material sheet envelope to assure maximum material utilization. Highly-specialized cutting tool configurations may be utilized by the MCD to machine the complex filler surfaces. The filler may be machined from a material which may be of any type including composite non-metallic, and metallic materials, for example and without limitation.
- In block 112, changes in the status of the filler through out its fabrication process may be logged and reported as required. In block 114, deburring of the filler may be carried out and the filler may be marked for incorporation into the structure. The filler may be immediately installed on an inline flow production line or retained for future use depending on the production strategy.
- It will be appreciated by those skilled in the art that the method of the disclosure may be implemented to define, produce, and ascertain and distribute the status of fillers that are custom-produced on demand for immediate installation on an inline flow production line in applications in which the full design requirement of an aircraft or other structure resides solely in a CAD/CAM system. It will be further appreciated by those skilled in the art that the method 100 may support 5-axis machine tools, 3D engineering definition of an aircraft or other structure, automatic capture of gap measurement data, automated delivery of the gap measurement data, machining of composite materials, automated generation of the Machine Control Data (MCD), delivery of the MCD to the machine tool and automated filler status collection, communication, and storage for future performance and process analysis.
- Referring next to
FIG. 1A , a flow diagram 100 a of an illustrative embodiment of a method of applying a diamond abrasive cutting tool configuration which enables unique gauge reduction and complex surface generation via material removal techniques of non-metallic composite materials is shown. In some applications, the flow diagram 100 a may be implemented as part of block 110 of the flow diagram 100 which was heretofore described with respect toFIG. 1 . In block 102 a, a cutting tool having a tool shank, an attached material removal cutting head on the tool shank and diamond abrasive cutting material applied on all material removal surfaces including grooves formed to facilitate the material removal process is provided. The cutting tool may have one of the cutting tool configurations which are described with respect toFIGS. 2-5A herein below. In block 104 a, a non-metallic filler material sheet is provided. In some embodiments, the non-metallic filler material sheet may be a composite material, such as CFRP and GFRP. In block 106 a, a filler may be fabricated from the filler material sheet using the cutting tool provided in block 102 a. It should be noted that a filler or multiple instances of the filler may be located in a single sheet of material. Additionally, multiple filler configurations may grouped in a single sheet of filler material and sequentially without interruption of the process to load material or to unload material and/or fillers. - Referring next to
FIGS. 2-5A of the drawings, various cutting tool configurations for production of fillers according to the method of the disclosure are shown. For example and without limitation, the cutting tool configurations shown inFIGS. 2-5A may be implemented in block 110 of the flow diagram 100 which was heretofore described with respect toFIG. 1 and in the flow diagram 100 a which was heretofore described with respect toFIG. 1A . Application of the cutting tool configurations may enable the unique gauge reduction and complex surface generation via material removal capabilities of the non-metallic composite materials (such as GFRP and CFRP). - As illustrated in
FIGS. 2 and 2A , in some embodiments thecutting tool 1 may include a generally elongatedtool shank 2 having an attached materialremoval cutting head 3 on thetool shank 2. The attached materialremoval cutting head 3 may have a generally semisphericalproximal head portion 3 a and a generallysemispherical cutting surface 3 b which extends from theproximal head portion 3 a. Diamond abrasive is applied on the material removal surfaces including grooves formed to facilitate thematerial removal process 4 may extend along the cuttingsurface 3 b of the attached materialremoval cutting head 3. As shown inFIG. 2A , in some embodiments, the grooves formed to facilitate thematerial removal process 4 may be generally arranged in helical or straight patterns on the cuttingsurface 3 b to facilitate the material removal process. - As shown in
FIGS. 3 and 3A , in some embodiments thecutting tool 1 a may include attached materialremoval cutting head 3 having a generally cylindricalproximal head portion 3 a and a generallysemispherical cutting surface 3 b which extends from theproximal head portion 3 a. The grooves formed to facilitate thematerial removal process 4 may extend along the cuttingsurface 3 b of the attached materialremoval cutting head 3. - As shown in
FIGS. 4 and 4A , in some embodiments, the attached materialremoval cutting head 3 of the cutting tool lb may include a generally cylindricalproximal head portion 3 a and a generally cylindricalside cutting surface 3 b with a generally planarend cutting surface 3 c. An annular cutting surface to facilitate the material removal process and to enable the generation ofcomplex surfaces 3 d which may be curved in cross-section and may circumscribe theend cutting surface 3 c. Diamond abrasive coated grooves formed to facilitate thematerial removal process 4 may extend along theside cutting surface 3 b, the radiused cuttingsurface edge 3 d and theend cutting surface 3 c. - As shown in
FIGS. 5 and 5A , in some embodiments the attached materialremoval cutting head 3 of thecutting tool 1 c may include a generally cylindricalproximal head portion 3 a and a generally cylindricalside cutting surface 3 b with an annularcutting surface edge 3 d. As shown inFIG. 5A , the materialremoval cutting head 3 may have a cutting surface bore 3 e to facilitate material removal. Diamondabrasive cutting ridges 4 may extend along theside cutting surface 3 b and onto the cuttingsurface edge 3 d of the materialremoval cutting head 3 and into the area defined by 3 e. - Referring next to
FIGS. 6 and 7 , embodiments of the disclosure may be used in the context of an aircraft manufacturing andservice method 78 as shown inFIG. 6 and anaircraft 94 as shown inFIG. 7 . During pre-production,exemplary method 78 may include specification anddesign 80 of theaircraft 94 andmaterial procurement 82. During production, component andsubassembly manufacturing 84 andsystem integration 86 of theaircraft 94 takes place. Thereafter, theaircraft 94 may go through certification anddelivery 88 in order to be placed inservice 90. While in service by a customer, theaircraft 94 may be scheduled for routine maintenance and service 92 (which may also include modification, reconfiguration, refurbishment, and so on). - Each of the processes of
method 78 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on. - As shown in
FIG. 7 , theaircraft 94 produced byexemplary method 78 may include anairframe 98 with a plurality ofsystems 96 and an interior 116. Examples of high-level systems 96 include one or more of apropulsion system 118, anelectrical system 120, ahydraulic system 122, and anenvironmental system 124. Any number of other systems may be included. The assembly and/or installation requires filler to assure proper assembly and installation procedure as defined by the product design criteria. Although an aerospace example is shown, the principles of the invention may be applied to other industries, such as the automotive industry. - The apparatus embodied herein may be employed during any one or more of the stages of the production and
service method 78. For example, components or subassemblies corresponding toproduction process 84 may be fabricated or manufactured in a manner similar to components or subassemblies produced while theaircraft 94 is in service. Also one or more apparatus embodiments may be utilized during the production stages 84 and 86, for example, by substantially expediting assembly of or reducing the cost of anaircraft 94. Similarly, one or more apparatus embodiments may be utilized while theaircraft 94 is in service, for example and without limitation, to maintenance andservice 92. - Although the embodiments of this disclosure have been described with respect to certain exemplary embodiments, it is to be understood that the specific embodiments are for purposes of illustration and not limitation, as other variations will occur to those of skill in the art.
Claims (16)
1. A cutting tool, comprising:
a shank; and
a head on the shank, the head comprising a diamond abrasive-coated cutting surface, the head having grooves interrupting the cutting surface and extending from the cutting surface toward an axis of rotation of the head, the cutting surface having a substantially constant radius.
2. A cutting tool as defined in claim 1 , wherein the cutting surface is cylindrical, the head further comprises a planar end cutting surface, and an edge of the head between the cutting surface and the end cutting surface is radiused.
3. A cutting tool as defined in claim 2 , wherein the grooves extend from the planar end cutting surface to an upper edge of the cutting surface.
4. A cutting tool as defined in claim 1 , wherein the shank is to be operatively coupled to a Computer Numerical Control (CNC) machine.
5. A cutting tool as defined in claim 1 , wherein the head is hemispherically shaped.
6. A cutting tool as defined in claim 1 , wherein the grooves are helically shaped.
7. A cutting tool as defined in claim 1 , wherein the cutting surface has the substantially constant radius in an axial direction of the head.
8. A cutting tool as defined in claim 1 , wherein the cutting tool is to perform cutting with the diamond abrasive-coated cutting surface.
9. A method of applying a diamond abrasive cutting tool configuration to machining of a filler from a non-metallic composite material, comprising:
engaging a filler material sheet with a cutting tool, the cutting tool including a shank and a head on the shank, the head comprising a diamond abrasive-coated cutting surface, the head having grooves interrupting the cutting surface and extending from the cutting surface toward an axis of rotation of the head, the cutting surface having a substantially constant radius; and
machining a filler from the filler material sheet using the cutting tool.
10. A method as defined in claim 9 , wherein engaging the filler material sheet comprises engaging the filler material sheet with a cylindrical cutting surface, the head further comprises a planar end cutting surface, and an edge of the head between the cutting surface and the end cutting surface is radiused.
11. A method as defined in claim 10 , wherein the grooves extend from the planar end cutting surface to an upper edge of the cutting surface.
12. A method as defined in claim 9 , wherein the shank is to be operatively coupled to a Computer Numerical Control (CNC) machine.
13. A method as defined in claim 9 , wherein the head is hemispherically shaped.
14. A method as defined in claim 9 , wherein the grooves are helically shaped.
15. A method as defined in claim 9 , wherein the cutting surface has the substantially constant radius in an axial direction of the head.
16. A method as defined in claim 9 , wherein the cutting tool is to perform cutting with the diamond abrasive-coated cutting surface.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US14/182,144 US20140162533A1 (en) | 2010-11-11 | 2014-02-17 | Cutting tools and machining methods using cutting tools |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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US41252210P | 2010-11-11 | 2010-11-11 | |
US12/987,364 US8655480B1 (en) | 2010-11-11 | 2011-01-10 | Automated filler production method |
US14/182,144 US20140162533A1 (en) | 2010-11-11 | 2014-02-17 | Cutting tools and machining methods using cutting tools |
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CN104008201A (en) * | 2014-06-16 | 2014-08-27 | 安徽工业大学 | Numerical control machine tool production information obtaining method |
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US8655480B1 (en) * | 2010-11-11 | 2014-02-18 | The Boeing Company | Automated filler production method |
US8756792B2 (en) * | 2011-06-08 | 2014-06-24 | The Boeing Company | Digitally designed shims for joining parts of an assembly |
US9990446B2 (en) | 2014-04-15 | 2018-06-05 | The Boeing Company | Predictive shimming for flexible surfaces |
US9599983B2 (en) * | 2015-01-21 | 2017-03-21 | The Boeing Company | Systems, methods, and apparatus for automated predictive shimming for large structures |
US10521551B2 (en) * | 2015-11-16 | 2019-12-31 | The Boeing Company | Methods for shimming flexible bodies |
US9952580B2 (en) | 2016-01-29 | 2018-04-24 | The Boeing Company | Method and an apparatus for machining a part for an assembly |
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