Patent Application
20060293906
The present invention relates to a method of developing a plan for repairing a product and, more particularly, to a method of developing a plan for repairing a product using a scanning process to identify a preferred replacement part.
Product repairs often involve replacing a defective or damaged part with a replacement part. To save cost and time, replacement parts are sometimes obtained from used products. For example, a damaged vertical tail of an aircraft can be replaced with a undamaged tailfin from an aircraft taken out of commission for other reasons (e.g., having a damaged fuselage). Due to high tolerance requirements of many assembled products, interchangeability of product parts is often difficult. When attachment features on the replacement part do not align with mating attachment features on the product, various measures must be taken to obtain an acceptable fit. For example, holes in the product may need to be enlarged and other interface characteristics may need to be reshaped to allow the part to fit to the product. The work required for fitting a part that does not easily mate to the receiving product can be costly and time consuming.
Fit problems occur during original manufacture as well. A very small dimensional variation from specifications in a new part or product can result in an improper fit. As a result, the part and/or product must be altered to allow fit, other parts must be tried on the product, or the product must be discarded. Whether a part and product are new or used, a method of accurately matching and mating parts with the products is needed to improve repair/manufacturing cycle time, and cost margins and to ensure products are within desired tolerances.
The present invention relates to a method of developing a plan for repairing an aircraft by attaching a replacement part to a receiving portion of the aircraft. The method comprises scanning the receiving portion of the aircraft to acquire information about at least one of dimensions, a position, and an orientation of the receiving portion. The method further comprises scanning a plurality of potential replacement parts to acquire dimensional information about the potential replacement parts. The method also comprises creating a repair plan including processing the information acquired in the scanning steps to identify a preferred replacement part of the plurality of potential replacement parts for attaching to the receiving portion of the aircraft.
In another aspect, the present invention includes a method of developing a plan for repairing a product having a receiving portion and a defective part mounted on the receiving portion. The method comprises scanning the receiving portion of the product to acquire information about at least one of dimensions, a position, and an orientation of the receiving portion. The method further comprises scanning a plurality of potential replacement parts to acquire dimensional information about the potential replacement parts. The method also comprises creating a repair plan including processing the information acquired in the scanning steps to identify a preferred replacement part of the plurality of potential replacement parts for mounting to the product at the receiving portion of the product in place of the defective part.
Other aspects of the present invention will be in part apparent and in part pointed out hereinafter.
Corresponding reference characters indicate corresponding parts throughout the several views of the drawings.
The present invention relates to a method of developing a plan for repairing a product and, more particularly, to a method of developing a plan for repairing a product using a scanning process to identify a preferred replacement part. Reference will now be made in detail to an implementation in accordance with methods, systems, and articles of manufacture consistent with the present invention as illustrated in the accompanying drawings. Methods, systems, and articles of manufacture consistent with the present invention allow accurate repair and manufacture of aircraft. Although use of the methods, systems, and articles of manufacture consistent with the present invention are primarily discussed with reference to aircraft, they may be applied to improve repair and manufacturing of other products (e.g., automobiles, tanks, ships, and other multi-component assemblies) without departing from the scope of the present invention.
Referring now to the figures, and more particularly to
The process 10 includes scanning 12 a part of an aircraft (e.g., a tail fin as shown in
The part to be replaced can be scanned 12 in a variety of ways. One way to scan the part to be replaced is to scan 14 the part while it is mounted on the aircraft to acquire information about position and/or orientation of the part. That is, the scanning device is used to determine the position and/or orientation of the part to be replaced with respect to the aircraft it is mounted on before it is removed from the aircraft. The positional and/or orientational information acquired by scanning 14 the part to be replaced in place (i.e., while it is mounted on the aircraft) can be helpful for accurately attaching a replacement part (not shown in
The process 10 further includes scanning 20 the receiving portion of the aircraft to acquire information about the dimensions, a position, or an orientation of the receiving portion. Scanning 20 the aircraft can be performed using any of a variety of scanning devices as previously described. For example, the receiving portion of the aircraft may be scanned 20 after the part to be replaced is removed and before a replacement part is attached. The information about the receiving portion of the aircraft will be used to identify one or more preferred replacement parts from multiple replacement part candidates.
The process 10 also includes scanning 22 potential replacement parts (not shown in
After the scanning steps 14, 18, 20, 22, the process 10 includes a step 26 of processing the information acquired in those steps to identify a preferred replacement part of the multiple potential replacement parts scanned 22. In one embodiment, the processing 26 is performed by a data processor (not shown). Although the data processor may be another type without departing from the scope of the present invention, in one embodiment the data processor is a conventional personal computer having Polyworks, available from Innovmetric, of Sainte-Foy, Quebec, Canada. It is envisioned the storing step 24 and the processing step 26 may be performed using a single computer or system of computers. In one embodiment, the programmed software includes a best fit algorithm to select a preferred replacement part. The algorithm may be any best fit algorithm known in the art. In one embodiment, the algorithm includes specifications that prioritize potential replacement parts based on variations each part is determined to require with respect to an optimal part location. For example, considering that positional variables include X, Y, Z, pitch, roll, and yaw directions, a particular repair specification may only allow changes in the yaw direction as a last resort, require a special inspection of the product if any change is made in the Z direction, and restrict movement in all other directions to certain ranges. Under this repair specification, the best fit algorithm would prefer parts that do not require position changes in either the yaw or Z directions and that only required changes in the other directions within the allowable ranges. In another embodiment, the programmed software selects a preferred replacement part based on preferences programmed into the software. For example, the software can include a hierarchy of variables whereby particular dimensional aspects of a potential replacement part are preferred over others. The programmed preferences include, but are not limited to, engineering requirements, such as allowable degrees of freedom, and design requirements, such as the necessity of a particular minimum clearance or edge distance. It is envisioned the processing step 26 may include identifying more than one of the potential replacement parts as preferred. It may be beneficial to have multiple preferred replacement parts in the event the most preferred part becomes unavailable. When more than one preferred replacement part is identified, the identified parts can be ranked from most to least preferred.
The processing step 26 further includes creating a plan for repairing the aircraft. Creating the repair plan can include developing a schedule for delivering the preferred replacement part to a location of the aircraft for attachment thereto. For example, once identified, a preferred replacement part can be scheduled for transport on an already planned shipment of other parts from a location of the replacement part to the location of the aircraft. The repair plan can also include procurement of hardware or a kit of hardware needed for the repair, such as necessary tooling and fasteners. For example, based on the information acquired by scanning 12, 20, 22, the data processor may determine that a small drill and drill bit of particular diameter (not shown) are required to slightly enlarge a hole in the receiving portion of the aircraft. Lead times for procuring rare or custom tooling, fasteners, and other hardware can have a significant impact on the cycle time of repair. The repair plan can also include identification of personnel needed to attach the preferred replacement part to the aircraft. For example, if work required to attach the replacement part to the aircraft can only be done by certified individuals, then those individuals can be identified. In these ways, efficient procurement can save time, resources, and costs in the repair process. The information acquired in the scanning steps 14, 18, 20, 22 can also be used for other predictive analyses, such as determining needs for downstream manufacture or repair.
The process 10 further includes attaching 28 the preferred replacement part to the receiving portion of the aircraft in place of the defective part. The attaching step 28 can include using the dimensional, positional, and/or orientational information acquired by scanning 14 the part to be replaced in place to position and orient the preferred replacement part on the aircraft. For example, the preferred replacement part can be positioned and oriented as close as possible to the manner in which the part to be replaced was positioned and oriented when it was mounted on the aircraft. In one embodiment, the positional and orientational data from the part to be replaced is used in the attaching step 28 by scanning the preferred replacement part during positioning and moving the preferred replacement part until it is in the desired position and orientation, as confirmed by feedback from the real time scanning. In another embodiment, the positional and orientational data from the part to be replaced is used in the attaching step 28 by projecting lasers corresponding to the desired position and orientation around the preferred replacement part so the replacement part is properly positioned and orientated when it matches up with the projections.
Positioning and orienting using the digitized positioning data can be performed using relatively simple or “soft” tools instead of the heavy and expensive “hard” tools often needed in conventional part replacement processes. One type of hard tool is a robust framework that contacts the aircraft and part to be replaced at various points to identify the position of the part with respect to the aircraft. The framework is designed to allow removal of the part to be removed. When mounting the replacement part to the aircraft, the replacement part is positioned by mating it with the contact features of the framework corresponding to the position of the part to be replaced. Soft positioning tools, on the other hand, are only needed to prop the preferred replacement part adjacent the desired position so the part can be slightly maneuvered into proper position. The type of soft positioning tool(s) used varies depending on the application. Soft tools can be light scaffolding, a crane, or even more common manufacturing implements, such as a sawhorse or dolly. Soft and hard tools can be specially developed for particular applications. Methods of manufacturing such tools include machining, forging, hydro-forming, selective laser sintering (SLS), directed metal disposition (DMD), and laminate object manufacturing (LOM). These methods may be used in various combinations or with other manufacturing techniques. For example, a tool created with SLS may be back-filled with concrete for added strength. Before and after the preferred replacement part has been positioned and oriented, the part and/or the aircraft can be worked as needed to facilitate proper mating between the part and the aircraft. For example the mounting portion of the preferred replacement part and the receiving portion of the aircraft can be drilled, cut, or otherwise modified for better fit between the two. Although the aircraft and/or preferred replacement part may require working during the attaching step 28 to obtain a proper fit, the amount of work and time needed to perform the repair will generally be less than would be needed to attach a random replacement part. After the preferred replacement part and aircraft are prepared, positioned, and oriented as desired, the part is fastened to the aircraft.
In one embodiment, the processing step 26 includes creating an apply template (not shown). An apply template is a representation of at least a portion of an object that can be measured, moved, compared to other objects, and otherwise analyzed with relative ease. For example, a physical mold can be made of the receiving portion of the aircraft using the dimensional information acquired in the scanning step 20. Apply templates can be used in a variety of ways. For example, measurements taken from a template can be used to identify a preferred replacement part. The template can also be used during the attaching step 28. For example, information about how a potential part and the receiving portion of the aircraft would interact during mating of the two can be acquired using transparent templates or templates representing only part of a scanned interface, thereby allowing a partial cross-sectional view of the mating features.
Although shown and discussed in a particular order, those skilled in the art will appreciate the pre-attachment steps 12, 16, 20, 22, 24, 26 of the process 10 can be performed in various orders. For example, in one embodiment, the potential replacement parts may be scanned 22 before the part to be replaced and aircraft are scanned 12, 20. Further, the process may be performed without scanning 12 the part to be replaced.
As discussed above, preferences can be programmed into the software for use during the processing step 26. As an example,
When introducing elements of the present invention or the preferred embodiment(s) thereof, the articles “a”, “an”, “the”, and “said” are intended to mean that there are one or more of the elements. The terms “comprising”, “including”, and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.
As various changes could be made in the above constructions without departing from the scope of the invention, it is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense.
