A system and method for a composite finishing system. The composite finishing system comprises an abrasive bit with an abrasive material on a removal surface of the abrasive bit, where in the abrasive bit has a pilot structure that positions an abrasive surface relative to an edge break intersection of a hole in a composite structure when a pilot structure is placed into the hole.

BACKGROUND INFORMATION

The present disclosure relates generally to manufacturing and, in particular, to a method and apparatus for reducing inconsistencies in a hole by using a multi-functional debur tool.

Aircraft are being designed and manufactured with greater and greater percentages of composite materials. Composite materials are used in aircraft to decrease the weight of the aircraft. This decreased weight improves performance features such as payload capacities and fuel efficiencies. Further, composite materials provide longer service life for various components in an aircraft.

Composite materials are tough, light-weight materials created by combining two or more functional components. For example, a composite material may include reinforcing fibers bound in a polymer resin matrix. The fibers may be unidirectional or may take the form of a woven cloth or fabric. The fibers and resins are arranged and cured to form a composite material.

Further, using composite materials to create aerospace composite structures potentially allows for portions of an aircraft to be manufactured in larger pieces or sections. For example, a fuselage in an aircraft may be created in cylindrical sections and then be assembled to form the fuselage of the aircraft. Other examples include, without limitation, wing sections joined to form a wing or stabilizer sections joined to form a stabilizer.

Holes are often created in composite structures using tools such as drills. In some cases, the holes are chamfered holes. A chamfered hole is a hole in which the cutter creates a counter sink in the hole. This counter sink is a portion near the surface that is enlarged relative to the other portion the hole. This enlarged portion may be designed to allow the head of a screw, a bolt, or other fastener to lie flush or below the surface of the composite structure when installed.

In performing machining operations to form these holes, sharp fibers often remain at an edge break intersection of a chamfered hole within a composite structure, such as a composite laminated panel. Currently, these fibers are sanded by human operators using abrasive cleaning pads. This type of process is time-consuming and labor-intensive and could potentially introduce ergonomic or safety issues for the operators, such as repetitive motion or carbon fiber slivers embedded in the skin of the operators.

Therefore, it would be desirable to have a method and apparatus that take into account at least some of the issues discussed above, as well as other possible issues. For example, it would be desirable to have a method and apparatus that overcome a technical problem with forming holes in composite structures. It would be desirable to have a method and apparatus that overcomes a technical problem with removing inconsistencies, such as carbon fiber slivers that extend from edge break intersections of the holes formed in composite structures.

SUMMARY

An embodiment of the present disclosure provides for a composite finishing system. The composite finishing system provides for an abrasive bit. The abrasive bit has an abrasive material on a removal surface of the abrasive bit, wherein the abrasive bit has a pilot structure that positions an abrasive surface relative to an edge break intersection of a hole in a composite structure when the pilot structure is placed into the hole.

Another embodiment of the present disclosure provides for a method for removing inconsistencies from a hole in a composite structure. The method comprises moving a pilot structure on an abrasive bit into the hole of the composite structure in a direction along a rotation axis for the abrasive bit. The pilot structure positions an abrasive surface relative to an edge break intersection of the hole when the pilot structure is placed into the hole. The abrasive bit is rotated while the pilot structure is in the hole. The abrasive bit has an abrasive material on a removal surface of the abrasive bit that removes undesired fibers from the edge break intersection of the hole.

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account one or more different considerations. Those embodiments recognize and take into account that the current techniques for removing inconsistencies from holes, such as undesired fibers at the edge break intersections of chamfered holes, are not as efficient as desired. The illustrative embodiments recognize and take account that ergonomics with respect to human operators is not as optimal as desired with current techniques for using abrasive pads. Further, the time and effort needed to remove these inconsistencies are greater than desired.

Thus, the illustrative embodiments provide a method and apparatus for removing undesired fibers from holes. In one illustrative example, a composite finishing system includes an abrasive bit having an abrasive material on a removal surface of the abrasive bit. The abrasive bit has a pilot structure that positions an abrasive surface relative to an edge break intersection of a hole in a composite structure when the pilot structure is placed into the hole.

With reference now to the figures, and in particular with reference toFIG. 1, an illustration of a manufacturing environment is depicted in accordance with an illustrative embodiment. In this example, manufacturing environment100includes composite spar102and composite spar104that are used to form a wing.

For example, holes106are formed in composite spar102. Holes106include fibers (not shown) that extend from surface108of composite spar102as a result of the formation of holes106. Holes110are present in composite spar104and have fibers that extend from surface112of composite spar104.

In this example, fibers that extend from surface108in holes106and from surface112in holes110are inconsistencies and also referred to as “undesired fibers”.

In this illustrative example, there may be thousands of holes106or holes110. This number of holes per spar is an extremely large number of holes for performing operations to reduce inconsistencies, such as undesired fibers, using currently available techniques.

As depicted, these undesired fibers are reduced on composite spar102by human operator114. In this illustrative example, human operator114operates drill116with abrasive bit118to reduce the undesired fibers.

The undesired fibers may also be reduced on composite spar104by a robotic machine in the form of robotic arm120. End effector122is connected to robotic arm120and abrasive bit124is connected to end effector122. In this example, end effector122is configured to perform machining operations. As depicted, robotic arm120with end effector122is configured to use abrasive bit124to reduce undesired fibers in holes110.

With reference next toFIG. 2, an illustration of a block diagram of a manufacturing environment is depicted in accordance with an illustrative embodiment. As depicted, manufacturing environment200inFIG. 2is an example of one implementation for manufacturing environment100inFIG. 1.

In this illustrative example, composite structure202is a structure on platform204. As depicted, composite structure202is comprised of composite materials. These composite materials typically weigh less than metals. The composite materials may be constructed from fibers and a resin. These fibers may be, for example, carbon fibers, fiberglass fibers, or some other suitable type of fiber. In this example, composite structure202is comprised of a carbon fiber reinforced polymer.

Composite spar102inFIG. 1is an example of an implementation for composite structure202. Platform204may take various forms. For example, platform204may be selected from one of a mobile platform, a stationary platform, a land-based structure, an aquatic-based structure, a space-based structure, an aircraft, a surface ship, a tank, a personnel carrier, a train, a spacecraft, a space station, a satellite, a submarine, an automobile, a power plant, a bridge, a dam, a house, a manufacturing facility, a building, or other suitable platform in which composite structure202may be used.

In this illustrative example, composite structure202has a group of holes206. As used herein, a “group of” when used with reference items means one or more items. For example, a group of holes206is one or more of holes206.

In this example, hole208is a hole in the group of holes206. Hole208has inconsistency210. As depicted, inconsistency210takes the form of undesired fibers212. For example, undesired fibers212extend from surface214of hole208. Undesired fibers212extend from surface214at edge break intersection216of hole208. As depicted, edge break intersection216is any location where a change in surface214occurs such that undesired fibers212may be present.

In this illustrative example, abrasive bit218is part of composite finishing system219and is used to remove undesired fibers212. Abrasive bit218has abrasive material220on removal surface222of abrasive bit218.

Abrasive material220is selected from at least one of a diamond coating or a flexible diamond coating. Abrasive material220also may be selected from other materials, including at least one of a ceramic, a ceramic aluminum oxide, silicon carbide, a ceramic iron oxide, horizontal, or other suitable types of materials.

For example, without limitation, “at least one of item A, item B, or item C” may include item A, item A and item B, or item B. This example also may include item A, item B, and item C or item B and item C. Of course, any combinations of these items may be present. In some illustrative examples, “at least one of” may be, for example, without limitation, two of item A, one of item B, and ten of item C; four of item B and seven of item C; or other suitable combinations. Additionally, abrasive bit218has pilot structure224that positions removal surface222relative to edge break intersection216of hole208in composite structure202when pilot structure224is placed into hole208.

In this illustrative example, wherein removal surface222has portion226that may taper. For example, portion226may taper such that removal surface222contacts edge break intersection216of hole208having feature228selected from a group consisting of chamfer230and fillet relief232when pilot structure224is inserted into hole208and moved in a direction along rotation axis234for abrasive bit218. In this illustrative example, rotation axis234is an axis that extends through abrasive bit218. This axis is one about which abrasive bit218rotates during operation of abrasive bit218.

As depicted, pilot structure224is centrally located about rotation axis234extending through abrasive bit218. Pilot structure224has diameter236sized to hole diameter238for hole208that allows pilot structure224to fit within hole208and position removal surface222such that undesired fibers212may be reduced from surface214of edge break intersection216. In this illustrative example, diameter236has a size that allows pilot structure224to fit within hole208. In other words, diameter236is smaller than hole diameter238such that pilot structure224may fit within hole208and position removal surface222in a desired manner to allow for reduction of undesired fibers212extending from surface214of edge break intersection216during operation of abrasive bit218.

In removing undesired fibers212, abrasive bit218may be rotated at different speeds. In this illustrative example, abrasive bit218rotates about rotation axis234at a speed such that undesired fibers212extending from surface214of hole208are reduced in size without removing undesired fibers212from composite structure202.

In this illustrative example, abrasive bit218is a tool that may be connected to equipment244in composite finishing system219. For example, equipment244may take the form of drill246. As another example, equipment244may include end effector248for robotic machine250.

In one illustrative example, one or more technical solutions are present that overcome a technical problem with forming holes in composite structures. Also, one or more technical solutions are present for a technical problem with removing inconsistencies, such as carbon fibers that extend from edge break intersections of the holes, formed in composite structures.

Further, one or more technical solutions may have a technical effect of reducing repetitive motion issues that occur from human operators using current sanding tools. Also, one or more of the technical solutions also may have a technical effect of reducing the occurrence of carbon fiber slivers entering skin of human operators through the use of an abrasive bit. Further, one or more technical solutions also may reduce the time needed to reduce undesired fibers extending from edge break intersections of holes. As a result, one or more technical solutions provide a technical effect in which an abrasive bit removes undesired fibers that extend from surfaces of holes in the composite structure.

With reference next toFIG. 3, an illustration of a block diagram of an indicator system for corresponding abrasive bits to holes is depicted in accordance with an illustrative embodiment. In this illustrative example, abrasive bits300have indicator system302that identifies hole sizes304for holes306that correspond to abrasive bits300. In other words, each one of abrasive bits300may have a diameter that is set for a particular hole size and hole sizes304for holes306.

For example, indicator system302includes a group of graphical indicators307selected from at least one of a color, an image, a graphic, text, a barcode, a symbol, or some other type of indicator. One or more of these indicators in indicator system302may be used by an operator such as human operator114or robotic arm120, shown inFIG. 1, to identify an appropriate abrasive bit in abrasive bits300for a particular hole in holes306.

In this illustrative example, the corresponding indicator in indicator system302may be associated with holes306. For example, if a color is used in indicator system302, abrasive bit308may have color312. Hole310also has color312to allow matching up abrasive bit308with hole310in holes306. In other words, color312identifies hole size316in holes sizes304that matches diameter318for abrasive bit308. In this manner, the use of indicator system302may reduce the possibility that a human operator, such as human operator114inFIG. 1, may use an abrasive bit with the wrong size.

For example, although abrasive bit218is shown as being used in manufacturing environment200, abrasive bit218also may be used in a maintenance environment in which holes may be formed in composite parts for performing maintenance such as part replacement, upgrades, refurbishment, or other types of routine maintenance.

With reference now toFIGS. 4-7, illustrations of an abrasive bit are depicted in accordance with an illustrative embodiment. With reference first toFIG. 4, abrasive bit400is an example of one implementation for abrasive bit218inFIG. 2, abrasive bits300inFIG. 3, abrasive bit308inFIG. 3shown in the block diagrams in these figures. In other words, the blocks showing physical and functional components for these abrasive bits in prior figures may be implemented physically in the illustrative example shown in this figure.

In this illustrative example, body402may be formed from a variety of different types of materials. For example, body402may be comprised of a material selected from one of a metal, an alloy, steel, aluminum, titanium, a plastic, a ceramic, or other suitable type of material.

In this illustrative example, body402has base410at second end406. Base410has a shape that is designed to allow body402of abrasive bit400to be connected to a piece of equipment such as a drill, an end effector, or some other suitable type of equipment that may be used to rotate abrasive bit400about rotational axis408.

In this illustrative example, body402has pilot structure412at first end404. Pilot structure412has a size and shape that is used to guide abrasive bit400into a hole. In this illustrative example, pilot structure412has diameter414. Diameter414is configured to fit into the hole in which inconsistencies are to be removed.

In this illustrative example, abrasive section416is a part of body402on which removal surface418has abrasive material420. In another illustrative example, abrasive section416may be a separate physical component that is connected to body402. For example, abrasive section416may be a flexible diamond coating that is attached to or formed on surface422of body402when abrasive section416is a separate component from body402.

In this illustrative example, removal surface418is a portion of surface422on body402that has abrasive material420that may contact an edge break intersection in a hole in a manner that allows for undesired fibers or other inconsistencies to be reduced.

Further, abrasive bit400also has channel424, channel426, and channel428in removal surface418of abrasive section416. These channels allow for debris to be moved away from removal surface418. As depicted, the debris is generated from removal surface418of abrasive section416reducing undesired fibers in a hole. This reduction may take the form of sanding in which particles are generated.

With reference next toFIG. 5, an illustration of a side view of an abrasive bit is depicted in accordance with an illustrative embodiment. In this illustrative example, a side view of abrasive bit400is shown in the direction of lines5-5inFIG. 4.

In this cross-sectional view, body402has length500. Base410has length504, and pilot structure412has length506. As shown in the cross-section view ofFIG. 5, channel426does not exceed the depth of removal surface418that has abrasive material420.

Turning now toFIG. 6, an illustration of an end of an abrasive bit is depicted in accordance with an illustrative embodiment. In this illustrative example, the end view of abrasive bit400is shown from first end404of body402for abrasive bit400.

With reference next toFIG. 7, an illustration of an abrasive bit positioned in a hole is depicted in accordance with an illustrative embodiment. In this illustrative example, abrasive bit400is positioned in hole700in composite structure702. Hole700in composite structure702is shown in a cross-sectional view. As can be seen in this figure, removal surface418on body402of abrasive bit400is in contact with edge break intersection704. Removal surface418is in contact such that inconsistencies such as fibers extending away from the surface of edge break intersection704may be reduced when abrasive bit400is rotated.

FIG. 8andFIG. 9illustrate an abrasive bit for use in a hole with a chamfer. With reference now toFIG. 8, an illustration of an abrasive bit is depicted in accordance with an illustrative embodiment. As depicted, abrasive bit800is configured for use in a hole with a chamfer.

InFIG. 9, an illustration of an abrasive bit positioned in a hole is depicted in accordance with an illustrative embodiment. In this illustrative example, abrasive bit800is positioned in hole900in composite structure902. Hole900in composite structure902is shown in a cross-sectional view. As depicted, hole900has chamfer904

The abrasive bit shown inFIG. 10andFIG. 11is designed for use in a hole with a fillet relief. With reference first toFIG. 10, an illustration of an abrasive bit is depicted in accordance with an illustrative embodiment. As depicted, abrasive bit1000is configured for use in a hole with the fillet relief.

In this illustrative example, abrasive bit1000has body1002and base1004. Abrasive bit1000also has pilot structure1006. Removal surface1008is located in abrasive section1010and abrasive section1012. Channel1014and channel1016are present in removal surface1008in abrasive section1010. Abrasive section1012is an optional location for removal surface1008.

InFIG. 11, an illustration of an abrasive bit positioned in a hole is depicted in accordance with an illustrative embodiment. In this illustrative example, abrasive bit1000is positioned in hole1100in composite structure1102. Hole1100in composite structure1102is shown in a cross-sectional view. As depicted, hole1100has fillet relief1104.

The illustration of the abrasive bits inFIGS. 4-11are only meant as illustrations of some possible implementations for abrasive bit218shown in block form inFIG. 2. These illustrations are not meant to limit the manner in which other abrasive bits may be implemented.

For example, other abrasive bits may have different shapes and dimensions depending on the particular hole for which the other abrasive bits are designed for use in reducing inconsistencies. As another example, although the abrasive material is shown in two abrasive sections, other illustrative examples may have a single abrasive section that includes removal surface at desired locations for contacting edge break intersections. This single section also may include abrasive material and other locations that may or may not contact undesired fibers. For example, abrasive section810inFIG. 8may be extended to include abrasive section812rather than being two separate sections.

Turning next toFIG. 12, an illustration of a flowchart of a process for removing inconstancies from a hole is depicted in accordance with an illustrative embodiment. The process illustrated inFIG. 12may be implemented using abrasive bit218inFIG. 2to remove inconsistencies from a hole in a composite structure. Abrasive bit400inFIG. 4, abrasive bit800inFIG. 8, and abrasive bit1000inFIG. 10are physical illustrations of examples of an abrasive bit that may be used in this process. In this example, the inconsistencies are undesired fibers that extend from surfaces of the composite structure as a result of operations performed to form the hole.

The process begins by moving a pilot structure on the abrasive bit into the hole in the composite structure in a direction along the rotation axis for the abrasive bit (operation1200). The pilot structure positions an abrasive surface relative to an edge break intersection of the hole when the pilot structure is placed into the hole.

The process rotates the abrasive bit while the pilot structure is in the hole (operation1202). The abrasive bit has an abrasive material on a removal surface of the abrasive bit that removes undesired fibers from the edge break intersection of the hole during rotation of the abrasive bit. The process terminates thereafter.

With reference now toFIG. 13, an illustration of a flowchart of a process for removing inconsistencies from holes in a composite structure is depicted in accordance with an illustrative embodiment. In this illustrative example, an abrasive bit shown in block form inFIG. 1may be used in this process. Abrasive bit400inFIG. 4, abrasive bit800inFIG. 8, and abrasive bit1000inFIG. 10are physical illustrations of examples of an abrasive bit that may be used in this process.

The process begins by selecting an unprocessed hole in the composite structure (operation1300). The process then identifies a selection criteria associated with the hole (operation1302). The selection criteria may take various forms. For example, selection criteria may be a color, an image, a graphic, text, a barcode, a symbol, or some other type of indicator. The process then selects an abrasive bit having the same selection criteria identified for the hole (operation1304). The process positions the selected abrasive bit in the hole (operation1306). The process rotates the abrasive bit of the abrasive bits in the hole (operation1308). This rotation may be performed at a speed such that undesired fibers are reduced by sanding rather than removing the undesired fibers from the composite structure.

The process determines whether another unprocessed hole is present in the composite structure (operation1310). If another unprocessed hole is present, the process returns to operation at1300. Otherwise, the process terminates.

For example, the abrasive bit described in the process in the flowchart inFIG. 12may be rotated prior to moving the abrasive bit towards or into the hole in which inconsistencies, such as undesired fibers, are present. In other examples, the abrasive bit may be rotated after the abrasive bit is positioned as desired.

The illustrative embodiments of the disclosure may be described in the context of aircraft manufacturing and service method1400as shown inFIG. 14and aircraft1500as shown inFIG. 15. Turning first toFIG. 14, an illustration of a block diagram of an aircraft manufacturing and service method is depicted in accordance with an illustrative embodiment. During pre-production, aircraft manufacturing and service method1400may include specification and design1402of aircraft1500inFIG. 15and material procurement1404.

During production, component and subassembly manufacturing1406and system integration1408of aircraft1500inFIG. 15takes place. Thereafter, aircraft1500inFIG. 15may go through certification and delivery1410in order to be placed in service1412. While in service1412by a customer, aircraft1500inFIG. 15is scheduled for routine maintenance and service1414, which may include modification, reconfiguration, refurbishment, and other maintenance or service.

With reference now toFIG. 15, an illustration of a block diagram of an aircraft is depicted in which an illustrative embodiment may be implemented. In this example, aircraft1500is produced by aircraft manufacturing and service method1400inFIG. 14and may include airframe1502with plurality of systems1504and interior1506. Examples of systems1504include one or more of propulsion system1508, electrical system1510, hydraulic system1512, and environmental system1514. Any number of other systems may be included.

Although an aerospace example is shown, different illustrative embodiments may be applied to other industries, such as the automotive industry. Apparatuses and methods embodied herein may be employed during at least one of the stages of aircraft manufacturing and service method1400inFIG. 14.

In one illustrative example, components or subassemblies produced in component and subassembly manufacturing1406inFIG. 14may be fabricated or manufactured in a manner similar to components or subassemblies produced while aircraft1500is in service1412inFIG. 14. The fabrication or manufacturing of these components may be performed using abrasive bits in accordance with illustrative examples to reduce inconsistencies, such as undesired fibers formed during the drilling of holes in composite structures in the components.

As yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production stages, such as component and subassembly manufacturing1406and system integration1408inFIG. 14. One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized while aircraft1500is in service1412, during maintenance and service1414inFIG. 14, or both.

The use of a number of the different illustrative embodiments may substantially expedite the assembly of aircraft1500, reduce the cost of aircraft1500, or both expedite the assembly of aircraft1500and reduce the cost of aircraft1500. The speed at which the assembly of aircraft may be reduced through the use of less time to remove inconsistencies from holes formed in composite structures that are to be assembled. Further, using abrasive bits increases the ergonomics as compared to current sanding of holes by human operators.

Turning now toFIG. 16, an illustration of a block diagram of a product management system is depicted in accordance with an illustrative embodiment. Product management system1600is a physical hardware system. In this illustrative example, product management system1600may include at least one of manufacturing system1602or maintenance system1604.

Manufacturing system1602is configured to manufacture products, such as aircraft1500inFIG. 15. As depicted, manufacturing system1602includes manufacturing equipment1606. Manufacturing equipment1606includes at least one of fabrication equipment1608or assembly equipment1610.

Fabrication equipment1608is equipment that may be used to fabricate components for parts used to form aircraft1500. For example, fabrication equipment1608may include machines and tools. These machines and tools may be at least one of a drill, a hydraulic press, a furnace, a mold, a composite tape laying machine, a vacuum system, a lathe, or other suitable types of equipment. Fabrication equipment1608may be used to fabricate at least one of metal parts, composite parts, semiconductors, circuits, fasteners, ribs, skin panels, spars, antennas, or other suitable types of parts.

Assembly equipment1610is equipment used to assemble parts to form aircraft1500. In particular, assembly equipment1610may be used to assemble components and parts to form aircraft1500. Assembly equipment1610also may include machines and tools. These machines and tools may be at least one of a robotic arm, a crawler, a faster installation system, a rail-based drilling system, or a robot. The tools also include abrasive bits that may be used to remove inconsistencies, such as undesired fibers resulting from holes drilled in composite components. Assembly equipment1610may be used to assemble parts, such as seats, horizontal stabilizers, wings, engines, engine housings, landing gear systems, and other parts for aircraft1500.

In this illustrative example, maintenance system1604includes maintenance equipment1612. Maintenance equipment1612may include any equipment needed to perform maintenance on aircraft1500. Maintenance equipment1612may include tools for performing different operations on parts on aircraft1500. These operations may include at least one of disassembling parts, refurbishing parts, inspecting parts, reworking parts, manufacturing replacement parts, or other operations for performing maintenance on aircraft1500. These operations may be for routine maintenance, inspections, upgrades, refurbishment, or other types of maintenance operations.

In the illustrative example, maintenance equipment1612may include ultrasonic inspection devices, x-ray imaging systems, vision systems, drills, crawlers, and other suitable devices. In some cases, maintenance equipment1612may include fabrication equipment1608, assembly equipment1610, or both to produce and assemble parts that may be needed for maintenance. Equipment may include the use of abrasive bits for removing inconsistencies from holes formed during the drilling of holes in composite structures.

Product management system1600also includes control system1614. Control system1614is a hardware system and may also include software or other types of components. Control system1614is configured to control the operation of at least one of manufacturing system1602or maintenance system1604. In particular, control system1614may control the operation of at least one of fabrication equipment1608, assembly equipment1610, or maintenance equipment1612. For example, control system1614may control the operation of robots that have abrasive bits used to reduce inconsistencies, such as undesired fibers formed during drilling of holes in composite structures

The hardware in control system1614may be using hardware that may include computers, circuits, networks, and other types of equipment. The control may take the form of direct control of manufacturing equipment1606. For example, robots, computer-controlled machines, and other equipment may be controlled by control system1614. In other illustrative examples, control system1614may manage operations performed by human operators1616in manufacturing or performing maintenance on aircraft1500. For example, control system1614may assign tasks, provide instructions, display models, or perform other operations to manage operations performed by human operators1616.

In the different illustrative examples, human operators1616may operate or interact with at least one of manufacturing equipment1606, maintenance equipment1612, or control system1614. This interaction may be performed to manufacture aircraft1500.

Of course, product management system1600may be configured to manage other products other than aircraft1500. Although aircraft management system1600has been described with respect to manufacturing in the aerospace industry, product management system1600may be configured to manage products for other industries. For example, product management system1600may be configured to manufacture products for the automotive industry as well as any other suitable industries.

Thus, those embodiments provide a method and apparatus for reducing inconsistencies from holes formed in composite structures. These inconsistencies include undesired fibers at edge break intersections in the hole. Inconsistencies may be reduced by using an abrasive bit having an abrasive material on a removal surface of the abrasive bit. The removal surface is configured to contact the edge break intersections when the abrasive bit is positioned within the hole. The abrasive bit has a pilot structure that positions an abrasive surface relative to an edge break intersection of a hole in a composite structure when the pilot structure is placed into the hole. In this illustrative example, the abrasive bit is rotated while the abrasive bit is positioned in the hole in a manner that reduces the inconsistencies. For example, the abrasive bit may be rotated in a manner that causes sanding of undesired fibers resulting from drilling the hole.

The description of the different illustrative embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the embodiments in the form disclosed. The different illustrative examples describe components that perform actions or operations. In an illustrative embodiment, a component may be configured to perform the action or operation described. For example, the component may have a configuration or design for a structure that provides the component an ability to perform the action or operation that is described in the illustrative examples as being performed by the component.

With the use of an abrasive bit, repetitive motion issues that occur from human operators using current sanding tools may be reduced. Additionally, the entry of carbon fiber slivers into skin of human operators also may be reduced through the use of an abrasive bit.