Abstract:
New 7xxx aluminum alloy bodies and methods of producing the same are disclosed. The new 7xxx aluminum alloy bodies may be produced by preparing the aluminum alloy body for post-solutionizing cold work, cold working by at least 25%, and then thermally treating. The new 7xxx aluminum alloy bodies may realize improved strength and other properties.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This patent application claims priority to each of U.S. Provisional Patent Application No. 61/381,040, filed Sep. 8, 2010, and U.S. Provisional Patent Application No. 61/391,461, filed Oct. 8, 2010, and U.S. Provisional Patent Application No. 61/425,024, filed Dec. 20, 2010, and U.S. Provisional Patent Application No. 61/437,515, filed Jan. 28, 2011. Each of the above-identified patent applications is incorporated herein by reference in its entirety. 
     This patent application is also related to WO2013/172910A2 entitled IMPROVED 2XXX ALUMINUM ALLOYS, AND METHODS FOR PRODUCING THE SAME, published Nov. 21, 2013, and WO2013/133960A1 entitled IMPROVED 7XXX ALUMINUM ALLOYS, AND METHODS FOR PRODUCING THE SAME, published Sep. 12, 2013, and WO2013/172912A1 entitled IMPROVED ALUMINUM LITHIUM ALLOYS, AND METHODS FOR PRODUCING THE SAME, published Nov. 21, 2013. 
    
    
     BACKGROUND 
     Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property is elusive. For example, it is difficult to increase the strength of an alloy without decreasing the toughness of an alloy. Other properties of interest for aluminum alloys include corrosion resistance and fatigue crack growth rate resistance, to name two. 
     SUMMARY OF THE DISCLOSURE 
     Broadly, the present patent application relates to improved wrought, heat treatable aluminum alloys, and methods for producing the same. Specifically, the present patent application relates to improved wrought, 7xxx aluminum alloy products, and methods for producing the same. Generally, the 7xxx aluminum alloy products achieve an improved combination of properties due to, for example, the post-solutionizing cold work and post-cold-working thermal treatments, as described in further detail below. 
     7xxx aluminum alloys are aluminum alloys containing zinc as the predominate alloying ingredient other than aluminum. For purposes of the present application, 7xxx aluminum alloys are aluminum alloys having at least 2.0 wt. % Zn, and up to 22 wt. % Zn, with the zinc being the predominate alloying element other than aluminum. 
     One conventional process for producing 7xxx aluminum alloy products in rolled form is illustrated in  FIG. 1 . In the conventional process, a 7xxx aluminum alloy body is cast ( 10 ), after which it is homogenized ( 11 ) and then hot rolled to an intermediate gauge ( 12 ). Next, the 7xxx aluminum alloy body is cold rolled ( 13 ) to final gauge, after which it is solution heat treated and quenched ( 14 ). “Solution heat treating and quenching” and the like, generally referred to herein as “solutionizing”, means heating an aluminum alloy body- to a suitable temperature, generally above the solvus temperature, holding at that temperature long enough to allow soluble elements to enter into solid solution, and cooling rapidly enough to hold the elements in solid solution. The solid solution formed at high temperature may be retained in a supersaturated state by cooling with sufficient rapidity to restrict the precipitation of the solute atoms as coarse, incoherent particles. After solutionizing ( 14 ), the 7xxx aluminum alloy body may be optionally stretched a small amount (e.g., 1-5%) for flatness ( 15 ), thermally treated ( 16 ) and optionally subjected to final treatment practices ( 17 ).  FIG. 1  is consistent with a process path for producing aluminum alloys in a T6 temper (the T6 temper is defined later in this patent application). 
     One embodiment of a new process for producing new 7xxx aluminum alloy products is illustrated in  FIG. 2 . In this new process, a 7xxx aluminum alloy body is prepared for post-solutionizing cold work ( 100 ), after which it is cold worked ( 200 ), and then thermally treated ( 300 ). The new process may also include optional final treatment(s) ( 400 ), as described in further detail below. “Post-solutionizing cold work” and the like means cold working of an aluminum alloy body after solutionizing. The amount of post-solutionizing cold work applied to the 7xxx aluminum alloy body is generally at least 25%, such as more than 50% cold work. By first solutionizing, and then cold working by at least 25%, and then appropriately thermally treating the 7xxx aluminum alloy body, the 7xxx aluminum alloy body may realize improved properties, as described in further detail below. For example, strength increases of 5-25%, or more, may be realized relative to conventional aluminum alloy products in the T6 temper, and in a fraction of the time required to process those conventional aluminum alloy products to the T6 temper (e.g., 10%-90% faster than T6 temper processed alloys). The new 7xxx aluminum alloy body may also realize good ductility, generally realizing an elongation of more than 4%, such as elongations of 6-12%, or higher. Other properties may also be maintained and/or improved (e.g., fracture toughness, corrosion resistance, fatigue crack growth resistance). 
     A. Preparing for Post-Solutionizing Cold Work 
     As illustrated in  FIG. 2 , the new process includes preparing an aluminum alloy body for post-solutionizing cold work ( 100 ). The aluminum alloy body may be prepared for post-solutionizing cold work ( 100 ) in a variety of manners, including the use of conventional semi-continuous casting methods (e.g., direct chill casting of ingot) and continuous casting methods (e.g., twin-roll casting). As illustrated in  FIG. 3 , the preparing step ( 100 ) generally comprises placing the aluminum alloy body in a form suitable for the cold working ( 120 ) and solutionizing the aluminum alloy body ( 140 ). The placing step ( 120 ) and solutionizing step ( 140 ) may occur sequentially or concomitant to one another. Some non-limiting examples of various preparing steps ( 100 ) are illustrated in  FIGS. 4-8 , which are described in further detail below. Other methods of preparing an aluminum alloy body for post-solutionizing cold work ( 100 ) are known to those skilled in the art, and these other methods are also within the scope of the preparing step ( 100 ) present invention, even though not explicitly described herein. 
     In one approach, the preparing step ( 100 ) comprises a semi-continuous casting method. In one embodiment, and with reference now to  FIG. 4 , the placing step ( 120 ) includes casting the aluminum alloy body ( 122 ) (e.g., in the form of an ingot or billet), homogenizing the aluminum alloy body ( 124 ), hot working the aluminum alloy body ( 126 ), and optionally cold working the aluminum alloy body ( 128 ). After the placing step ( 120 ), the solutionizing step ( 140 ) is completed. Similar steps may be completed using continuous casting operations, although the aluminum alloy body would not be in the form of an ingot/billet after casting ( 120 ). 
     In another embodiment, and with reference now to  FIG. 5 , a preparing step ( 100 ) includes casting the aluminum alloy body ( 122 ), homogenizing the aluminum alloy body ( 124 ) and hot working the aluminum alloy body ( 126 ). In this embodiment, the hot working step ( 126 ) may be completed to place soluble elements in solid solution, after which the aluminum alloy body is quenched (not illustrated), thereby resulting in the solutionizing step ( 140 ). This is one example of the placing step ( 120 ) and solutionizing step ( 140 ) being completed concomitant to one another. This embodiment may be applicable to press-quenched products (e.g., extrusions) and hot rolled products that are quenched after hot rolling, among others. 
     In another approach, the preparing step ( 100 ) comprises a continuous casting method, such as belt casting, rod casting, twin roll casting, twin belt casting (e.g., Hazelett casting), drag casting, and block casting, among others. One embodiment of a preparing step ( 100 ) employing a continuous casting methodology is illustrated in  FIG. 6 . In this embodiment, the aluminum alloy body is cast and solutionized at about the same time ( 142 ), i.e., concomitant to one another. The casting places the aluminum alloy body in a form sufficient to cold work. When the solidification rate during casting is sufficiently rapid, the aluminum alloy body is also solutionized. In this embodiment, the casting/solutionizing step ( 142 ) may include quenching of the aluminum alloy body after casting (not illustrated). This embodiment may be applicable to twin-roll casting processes, among other casting processes. Some twin-roll casting processes capable of completing the process of  FIG. 6  are described in U.S. Pat. No. 7,182,825 and U.S. Pat. No. 6,672,368. 
     In another embodiment, and with reference now to  FIG. 7 , a preparing step ( 100 ) includes casting the aluminum alloy body ( 122 ) and, after the casting step ( 122 ), then solutionizing the aluminum alloy body ( 140 ). In this embodiment, the placing step ( 120 ) comprises the casting ( 122 ). This embodiment is applicable to twin-roll casting processes, among other casting processes. 
     In another embodiment, and with reference now to  FIG. 8 , a preparing step ( 100 ) includes casting the aluminum alloy body ( 122 ), hot working the aluminum alloy body ( 126 ), and optionally cold working the aluminum alloy body ( 128 ). In this embodiment, the placing step ( 120 ) includes the casting ( 122 ), the hot working ( 126 ), and optional cold working ( 128 ) steps. After the placing step ( 120 ), the solutionizing step ( 140 ) is completed. This embodiment may be applicable to continuous casting processes. 
     Many of the steps illustrated in  FIGS. 2-8  can be completed in batch or continuous modes. In one example, the cold working ( 200 ) and thermal treatment step ( 300 ) are completed continuously. In this example, a solutionized aluminum alloy body may enter the cold working operation at ambient conditions. Given the relatively short thermal treatment times achievable with the new processes described herein, the cold worked aluminum alloy body could be immediately thermally treated ( 300 ) after cold working (e.g., in-line). Conceivably, such thermal treatments could occur proximal the outlet of the cold working apparatus, or in a separate heating apparatus connected to the cold working apparatus. This could increase productivity. 
     As described above, the preparing step ( 100 ) generally comprises solutionizing of the aluminum alloy body. As noted above, “solutionizing” includes quenching (not illustrated) of the aluminum alloy body, which quenching may be accomplished via a liquid (e.g., via an aqueous or organic solution), a gas (e.g., air cooling), or even a solid (e.g., cooled solids on one or more sides of the aluminum alloy body). In one embodiment, the quenching step includes contacting the aluminum alloy body with a liquid or a gas. In some of these embodiments, the quenching occurs in the absence of hot working and/or cold working of the aluminum alloy body. For example, the quenching may occur by immersion, spraying and/or jet drying, among other techniques, and in the absence of deformation of the aluminum alloy body. 
     Those skilled in the art recognize that other preparing steps ( 100 ) can be used to prepare an aluminum alloy body for post-solutionizing cold work (e.g., powder metallurgy methods), and that such other preparing steps fall within the scope of the preparing step ( 100 ) so long as they place the aluminum alloy body in a form suitable for cold working ( 120 ) and solutionize the aluminum alloy body ( 140 ), and irrespective of whether these placing ( 120 ) and solutionizing ( 140 ) steps occur concomitantly (e.g., contemporaneously) or sequentially, and irrespective of whether the placing step ( 120 ) occurs before the solutionizing step ( 140 ), or vice-versa. 
     B. Cold Working 
     Referring back to  FIG. 2 , and as noted above, the new process includes cold working ( 200 ) the aluminum alloy body a high amount. “Cold working” and the like means deforming an aluminum alloy body in at least one direction and at temperatures below hot working temperatures (e.g., not greater than 400° F.). Cold working may be imparted by one or more of rolling, extruding, forging, drawing, ironing, spinning, flow-forming, and combinations thereof, among other types of cold working methods. These cold working methods may at least partially assist in producing various 7xxx aluminum alloy products (see, Product Applications, below). 
     i. Cold Rolling 
     In one embodiment, and with reference now to  FIG. 9 , the cold working step ( 200 ) comprises cold rolling ( 220 ) (and in some instances consists of cold rolling ( 220 ), with optional stretching or straightening for flatness ( 240 )). In this embodiment, and as described above, the cold rolling step ( 220 ) is completed after the solutionizing step ( 140 ). Cold rolling ( 220 ) is a fabrication technique where an aluminum alloy body is decreased in thickness, generally via pressure applied by rollers, and where the aluminum alloy body enters the rolling equipment at a temperature below that used for hot rolling ( 124 ) (e.g., not greater than 400° F.). In one embodiment, the aluminum alloy body enters the rolling equipment at ambient conditions, i.e., the cold rolling step ( 220 ) is initiated at ambient conditions in this embodiment. 
     The cold rolling step ( 220 ) reduces the thickness of a 7xxx aluminum alloy body by at least 25%. The cold rolling step ( 220 ) may be completed in one or more rolling passes. In one embodiment, the cold rolling step ( 220 ) rolls the aluminum alloy body from an intermediate gauge to a final gauge. The cold rolling step ( 220 ) may produce a sheet, plate, or foil product. A foil product is a rolled product having a thickness of less than 0.006 inch. A sheet product is a rolled product having a thickness of from 0.006 inch to 0.249 inch. A plate product is a rolled product having a thickness of 0.250 inch or greater. 
     “Cold rolled XX %” and the like means XX CR %, where XX CR % is the amount of thickness reduction achieved when the aluminum alloy body is reduced from a first thickness of T 1  to a second thickness of T 2  by cold rolling, where T 1  is the thickness prior to the cold rolling step ( 200 ) (e.g., after solutionizing) and T 2  is the thickness after the cold rolling step ( 200 ). In other words, XX CR % is equal to:
 
 XX   CR %=(1 −T   2   /T   1 )*100%
 
For example, when an aluminum alloy body is cold rolled from a first thickness (T 1 ) of 15.0 mm to a second thickness of 3.0 mm (T 2 ), XX CR % is 80%. Phrases such as “cold rolling 80%” and “cold rolled 80%” are equivalent to the expression XX CR %=80%.
 
     In one embodiment, the aluminum alloy body is cold rolled ( 220 ) at least 30% (XX CR %≧30%), i.e., is reduced in thickness by at least 30%. In other embodiments, the aluminum alloy body is cold rolled ( 220 ) at least 35% (XX CR %≧35%), or at least 40% (XX CR %≧40%), or at least 45% (XX CR %≧45%), or at least 50% (XX CR %≧50%), or at least 55% (XX CR %≧55%), or at least 60% (XX CR %≧60%), or at least 65% (XX CR %≧65%), or at least 70% (XX CR %≧70%), or at least 75% (XX CR %≧75%), or at least 80% (XX CR %≧80%), or at least 85% (XX CR %≧85%), or at least 90% (XX CR %≧90%), or more. 
     In some embodiments, it may be impractical or non-ideal to cold roll ( 220 ) by more than 90% (XX CR %≦90%). In these embodiments, the aluminum alloy body may be cold rolled ( 220 ) by not greater than 87% (XX CR %≦87%), such as cold rolled ( 220 ) not more than 85% (XX CR %≦85%), or not greater than 83% (XX CR %≦83%), or not greater than 80% XX CR %≦80%). 
     In one embodiment, the aluminum alloy body is cold rolled in the range of from more than 50% to not greater than 85% (50%&lt;XX CR %≦85%). This amount of cold rolling may produce an aluminum alloy body having preferred properties. In a related embodiment, the aluminum alloy body may be cold rolled in the range of from 55% to 85% (55%≦XX CR %≦85%). In yet another embodiment, the aluminum alloy body may be cold rolled in the range of from 60% to 85% (60%≦XX CR %≦85%). In yet another embodiment, the aluminum alloy body may be cold rolled in the range of from 65% to 85% (65%≦XX CR %≦85%). In yet another embodiment, the aluminum alloy body may be cold rolled in the range of from 70% to 80% (70%≦XX CR %≦80%). 
     Still referring to  FIG. 9 , in this embodiment of the process, optional pre-cold rolling ( 128 ) may be completed. This pre-cold rolling step ( 128 ) may further reduce the intermediate gauge of the aluminum alloy body (due to the hot rolling  126 ) to a secondary intermediate gauge before solutionizing ( 140 ). As an example, the optional cold rolling step ( 128 ) may be used to produce a secondary intermediate gauge that facilitates production of a final cold rolled gauge during the cold rolling step ( 220 ). 
     ii. Other Cold Working Techniques 
     Aside from cold rolling, and referring back to  FIG. 2 , cold working may be imparted by one or more of extruding, forging, drawing, ironing, spinning, flow-forming, and combinations thereof, among other types of cold working methods, alone or in combination with cold rolling. As noted above, the aluminum alloy body is generally cold worked by at least 25% after solutionizing. In one embodiment, the cold working works the aluminum alloy body to its substantially final form (i.e., no additional hot working and/or cold working steps are required to achieve the final product form). 
     “Cold working by XX %” (“XX CW %”) and the like means cold working the aluminum alloy body an amount sufficient to achieve an equivalent plastic strain (described below) that is at least as large as the amount of equivalent plastic strain that would have been achieved if the aluminum alloy body had been cold rolled XX % (XX CR %). For example, the phrase “cold working 68.2%” means cold working the aluminum alloy body an amount sufficient to achieve an equivalent plastic strain that is at least as large as the amount of equivalent plastic strain that would have been achieved if the aluminum alloy body had been cold rolled 68.2%. Since XX CW % and XX CR % both refer to the amount of equivalent plastic strain induced in an aluminum alloy body as if the aluminum alloy body was cold rolled XX % (or actually is cold rolled XX % in the case of actual cold rolling), those terms are used interchangeably herein to refer to this amount of equivalent plastic strain. 
     Equivalent plastic strain is related to true strain. For example, cold rolling XX %, i.e., XX CR %, may be represented by true strain values, where true strain (ε true ) is given by the formula:
 
ε true =ln(1−% CR/100)  (1)
 
Where % CR is XX CR %, true strain values may be converted to equivalent plastic strain values. In the case where biaxial strain is achieved during cold rolling, the estimated equivalent plastic strain will be 1.155 times greater than the true strain value (2 divided by the √3 equals 1.155). Biaxial strain is representative of the type of plastic strain imparted during cold rolling operations. A table correlating cold rolling XX % to true strain vales and equivalent plastic strain values is provided in Table 1, below.
 
                             TABLE 1               Cold Rolling Thickness   Cold Rolling   Estimated Equivalent       Reduction (XX CR  %)   True Strain Value   Plastic Strain                   25%   0.2877   0.3322       30%   0.3567   0.4119       35%   0.4308   0.4974       40%   0.5108   0.5899       45%   0.5978   0.6903       50%   0.6931   0.8004       55%   0.7985   0.9220       60%   0.9163   1.0583       65%   1.0498   1.2120       70%   1.2040   1.3902       75%   1.3863   1.6008       80%   1.6094   1.8584       85%   1.8971   2.1906       90%   2.3026   2.6588                    
These equivalent plastic strain values assume:
 
     A. no elastic strain; 
     B. the true plastic strains preserve volume constancy; and 
     C. the loading is proportional. 
     For proportional loading, the above and/or other principles may be used to determine an equivalent plastic strain for various cold working operations. For non-proportional loading, the equivalent plastic strain due to cold working may be determined using the formula: 
     
       
         
           
             
               
                 
                   
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     where de p  is the equivalent plastic strain increment and dε i   p  (i=1,2,3) represent the increment in the principal plastic strain components. See, Plasticity, A. Mendelson, Krieger Pub Co; 2nd edition (August 1983), ISBN-10: 0898745829. 
     Those skilled in the art appreciate that the cold working step ( 200 ) may include deforming the aluminum alloy body in a first manner (e.g., compressing) and then deforming the aluminum alloy body in a second manner (e.g., stretching), and that the equivalent plastic strain described herein refers to the accumulated strain due to all deformation operations completed as a part of the cold working step ( 200 ). Furthermore, those skilled in the art appreciate that the cold working step ( 200 ) will result in inducement of strain, but not necessarily a change in the final dimensions of the aluminum alloy body. For example, an aluminum alloy body may be cold deformed in a first manner (e.g., compressing) after which it is cold deformed in a second manner (e.g., stretching), the accumulated results of which provide an aluminum alloy body having about the same final dimensions as the aluminum alloy body before the cold working step ( 200 ), but with an increased strain due to the various cold deformation operations of the cold working step ( 200 ). Similarly, high accumulated strains can be achieved through sequential bending and reverse bending operations. 
     The accumulated equivalent plastic strain, and thus XX CR %, may be determined for any given cold working operation, or series of cold working operations, by computing the equivalent plastic strain imparted by those cold working operations and then determining its corresponding XX CR % value, via the methodologies shown above, and other methodologies known to those skilled in the art. For example, an aluminum alloy body may be cold drawn, and those skilled in the art may compute the amount of equivalent plastic strain imparted to the aluminum alloy body based on the operation parameters of the cold drawing. If the cold drawing induced, for example, an equivalent plastic strain of about 0.9552, then this cold drawing operation would be equivalent to an XX CR % of about 56.3% (0.9552/1.155 equals a true strain value of 0.8270 (ε true ); in turn, the corresponding XX CR % is 56.3% using equation (1), above). Thus, in this example, XX CR %=56.3, even though the cold working was cold drawing and not cold rolling. Furthermore, since “cold working by XX %” (“XX CW %”) is defined (above) as cold working the aluminum alloy body an amount sufficient to achieve an equivalent plastic strain that is at least as large as the amount of equivalent plastic strain that would be achieved if the aluminum alloy body had been reduced in thickness XX % solely by cold rolling (“XX CR %”), then XX CW  is also 56.3%. Similar calculatibns may be completed when a series of cold working operations are employed, and in those situations the accumulated equivalent plastic strain due to the series of cold working operations would be used to determine the XX CR %. 
     As described earlier, the cold working ( 200 ) is accomplished such that the aluminum alloy body realizes an XX CW % or XX CR %≧25%, i.e., ≧0.3322 equivalent plastic strain. “Cold working XX %” and the like means XX CW %. Phrases such as “cold working 80%” and “cold worked 80%” are equivalent to the expression XX CW %=80. For tailored non-uniform cold working operations, the amount of equivalent plastic strain, and thus the amount of XX CW  or XX CR , is determined on the portion(s) of the aluminum alloy body receiving the cold work ( 200 ). 
     In one embodiment, the aluminum alloy body is cold worked ( 200 ) sufficiently to achieve, and realizes, an equivalent plastic strain (“EPS”) of at least 0.4119 (i.e., XX CW %≧30%). In other embodiments, the aluminum alloy body is cold worked ( 200 ) sufficiently to achieve, and realizes, an EPS of at least 0.4974 (XX CW %≧35%), or at least 0.5899 (XX CW %≧40%), or at least 0.6903 (XX CW %≧45%), or at least 0.8004, (XX CW %≧50%), or at least 0.9220 (XX CW %≧55%), or at least 1.0583 (XX CW %≧60%), or at least 1.2120 (XX CW %≧65%), or at least 1.3902 (XX CW %≧70%), or at least 1.6008 (XX CW %≧75%), or at least 1.8584 (XX CW %≧80%), or at least 2.1906 (XX CW %≧85%), or at least 2.6588 (XX CW %≧90%), or more. 
     In some embodiments, it may be impractical or non-ideal to cold work ( 200 ) by more than 90% (XX CW %≦90% and EPS≦2.6588). In these embodiments, the aluminum alloy body may be cold worked ( 200 ) not more than 87% (XX CW %≦87% and EPS≦2.3564), such as cold worked ( 200 ) not more than 85% (XX CW %≦85% and EPS≦2.1906), or not more than 83% (XX CW %≦83% and EPS≦2.0466), or not more than 80% (XX CW %≦80% and EPS≦1.8584). 
     In one embodiment, the aluminum alloy body is cold worked ( 200 ) in the range of from more than 50% to not greater than 85% (50%≦XX CW %≦85%). This amount of cold working ( 200 ) may produce an aluminum alloy body having preferred properties. In a related embodiment, the aluminum alloy body is cold worked ( 200 ) in the range of from 55% to 85% (55%≦XX CW %≦85%). In yet another embodiment, the aluminum alloy body is cold worked ( 200 ) in the range of from 60% to 85% (60%≦XX CW %≦85%). In yet another embodiment, the aluminum alloy body is cold worked ( 200 ) in the range of from 65% to 85% (65%≦XX CW %≦85%). In yet another embodiment, the aluminum alloy body is cold worked ( 200 ) in the range of from 70% to 80% (70%≦XX CW %≦80%). 
     iii. Gradients 
     The cold working step ( 200 ) may be tailored to deform the aluminum alloy body in a generally uniform manner, such as via rolling, described above, or conventional extruding processes, among others. In other embodiments, the cold working step may be tailored to deform the aluminum alloy body in a generally non-uniform manner. Thus, in some embodiments, the process may produce an aluminum alloy body having tailored cold working gradients, i.e., a first portion of the aluminum alloy body receives a first tailored amount of cold work and a second portion of the aluminum alloy body receives a second tailored amount of cold work, where the first tailored amount is different than the second tailored amount. Examples of cold working operations ( 200 ) that may be completed, alone or in combination, to achieve tailored non-uniform cold work include forging, burnishing, shot peening, flow forming, and spin-forming, among others. Such cold working operations may also be utilized in combination with generally uniform cold working operations, such as cold rolling and/or extruding, among others. As mentioned above, for tailored non-uniform cold working operations, the amount of equivalent plastic strain is determined on the portion(s) of the aluminum alloy body receiving the cold work ( 200 ). 
     iv. Cold Working Temperature 
     The cold working step ( 200 ) may be initiated at temperatures below hot working temperatures (e.g., not greater than 400° F.). In one approach, the cold working step ( 200 ) is initiated when the aluminum alloy body reaches a sufficiently low temperature after solutionizing ( 140 ). In one embodiment, the cold working step ( 200 ) may be initiated when the temperature of the aluminum alloy body is not greater than 250° F. In other embodiments, the cold working step ( 200 ) may be initiated when the temperature of the aluminum alloy body is not greater than 200° F., or not greater than 175° F., or not greater than 150° F., or not greater than 125° F., or less. In one embodiment, a cold working step ( 200 ) may be initiated when the temperature of the aluminum alloy body is around ambient. In other embodiments, a cold working step ( 200 ) may be initiated at higher temperatures, such as when the temperature of the aluminum alloy body is in the range of from 250° F. to less than hot working temperatures (e.g., less than 400° F.). 
     In one embodiment, the cold working step ( 200 ) is initiated and/or completed in the absence of any purposeful/meaningful heating (e.g., purposeful heating that produces a material change in the microstructure and/or properties of the aluminum alloy body). Those skilled in the art appreciate that an aluminum alloy body may realize an increase in temperature due to the cold working step ( 200 ), but that such cold working steps ( 200 ) are still considered cold working ( 200 ) because the working operation began at temperatures below those considered to be hot working temperatures. When a plurality of cold working operations are used to complete the cold working step ( 200 ), each one of these operations may employ any of the above-described temperature(s), which may be the same as or different from the temperatures employed by a prior or later cold working operation. 
     As noted above, the cold working ( 200 ) is generally initiated when the aluminum alloy body reaches a sufficiently low temperature after solutionizing ( 140 ). Generally, no purposeful/meaningful thermal treatments are applied to the aluminum alloy body between the end of the solutionizing step ( 140 ) and the beginning of the cold working step ( 200 ), i.e., the process may be absent of thermal treatments between the completion of the solutionizing step ( 140 ) and the initiation of the cold working step ( 200 ). In some instances, the cold working step ( 200 ) is initiated soon after the end of the solutionizing step ( 140 ) (e.g., to facilitate cold working). In one embodiment, the cold working step ( 200 ) is initiated not more than 72 hours after the completion of the solutionizing step ( 140 ). In other embodiments, the cold working step ( 200 ) is initiated in not greater than 60 hours, or not greater than 48 hours, or not greater than 36 hours, or not greater than 24 hours, or not greater than 20 hours, or not greater than 16 hours, or not greater than 12 hours, or less, after the completion of the solutionizing step ( 140 ). In one embodiment, the cold working step ( 200 ) is initiated within a few minutes, or less, of completion of the solutionizing step ( 140 ) (e.g., for continuous casting processes). In another embodiment, the cold working step ( 200 ) is initiated concomitant to completion of the solutionizing step ( 140 ) (e.g., for continuous casting processes). 
     In other instances, it may be sufficient to begin the cold working ( 200 ) after a longer elapse of time relative to the completion of the solutionizing step ( 140 ). In these instances, the cold working step ( 200 ) may be completed one or more weeks or months after the completion of the solutionizing step ( 140 ). 
     C. Thermally Treating 
     Referring still to  FIG. 2 , a thermally treating step ( 300 ) is completed after the cold working step ( 200 ). “Thermally treating” and the like means purposeful heating of an aluminum alloy body such that the aluminum alloy body reaches an elevated temperature. The thermal treatment step ( 300 ) may include heating the aluminum alloy body for a time and at a temperature sufficient to achieve a condition or property (e.g., a selected strength, a selected ductility, among others). 
     After solutionizing, most heat treatable alloys, such as 7xxx aluminum alloys, exhibit property changes at room temperature. This is called “natural aging” and may start immediately after solutionizing, or after an incubation period. The rate of property changes during natural aging varies from one alloy to another over a wide range, so that the approach to a stable condition may require only a few days or several years. Since natural aging occurs in the absence of purposeful heating, natural aging is not a thermal treatment step ( 300 ). However, natural aging may occur before and/or after the thermal treatment step ( 300 ). Natural aging may occur for a predetermined period of time prior to the thermal treatment step ( 300 ) (e.g., from a few minutes or hours to a few weeks, or more). Natural aging may occur between or after any of the solutionizing ( 140 ), the cold working ( 200 ) and the thermal treatment steps ( 300 ). 
     The thermally treating step ( 300 ) heats the aluminum alloy body to a temperature within a selected temperature range. For the purposes of the thermally treating step ( 300 ), this temperature refers to the average temperature of the aluminum alloy body during the thermally treating step ( 300 ). The thermally treating step ( 300 ) may include a plurality of treatment steps, such as treating at a first temperature for a first period of time, and treating at a second temperature for a second period of time. The first temperature may be higher or lower than the second temperature, and the first period of time may be shorter or longer than the second period of time. 
     The thermally treating step ( 300 ) is generally completed such that the aluminum alloy body achieves/maintains a predominately unrecrystallized microstructure, as defined below. As described in further detail below, a predominately unrecrystallized microstructure may achieve improved properties. In this regard, the thermally treating step ( 300 ) generally comprises heating the aluminum alloy body to an elevated temperature, but below the recrystallization temperature of the aluminum alloy body, i.e., the temperature at which the aluminum alloy body would not achieve a predominately unrecrystallized microstructure. For example, the thermally treating step ( 300 ) may comprise heating the 7xxx aluminum alloy body to a temperature in the range of from 150° F. to 400° F. (or higher), but below the recrystallization temperature of the aluminum alloy body. 
     The thermally treating step ( 300 ) may be completed in any suitable manner that maintains the aluminum alloy body at one or more selected temperature(s) for one or more selected period(s) of time (e.g., in order to achieve a desired/selected property or combination of properties). In one embodiment, the thermally treating step ( 300 ) is completed in an aging furnace, or the like. In another embodiment, the thermally treating step ( 300 ) is completed during a paint-bake cycle. Paint-bake cycles are used in the automotive and other industries to cure an applied paint by baking it for a short period of time (e.g., 5-30 minutes). Given the ability for the presently described processes to produce aluminum alloy bodies having high strength within a short period of time, as described below, paint-bake cycles, and the like, may be used to complete the thermally treating step ( 300 ), thereby obviating the need for separate thermal treatment and paint-bake steps. Similarly, in another embodiment, the thermally treating step ( 300 ) may be completed during a coating cure step, or the like. 
     D. Cold Working and Thermally-Treating Combination 
     The combination of the cold working step ( 200 ) and the thermally treating step ( 300 ) are capable of producing aluminum alloy bodies having improved properties. It is believed that the combination of the high deformation of the cold working step ( 200 ) in combination with the appropriate thermally treatment conditions ( 300 ) produce a unique microstructure (see, Microstructure, below) capable of achieving combinations of strength and ductility that have been heretofore unrealized. The cold working step ( 200 ) facilitates production of a severely deformed microstructure while the thermally treating step ( 300 ) facilitates precipitation hardening. When the cold working ( 200 ) is at least 25%, and preferably more than 50%, and when an appropriate thermal treatment step ( 300 ) is applied, improved properties may be realized. 
     In one approach, the cold working ( 200 ) and thermally treating ( 300 ) steps are accomplished such that the aluminum alloy body achieves an increase in strength (e.g., tensile yield strength (R 0.2 ) or ultimate tensile strength (R m )). The strength increase may be realized in one or more of the L, LT or ST directions. 
     In one embodiment, the cold working ( 200 ) and thermally treating ( 300 ) steps are accomplished such that the aluminum alloy body achieves an increase in strength as compared to a reference-version of the aluminum alloy body in the “as-cold worked condition”. In another embodiment, the cold working ( 200 ) and thermally treating ( 300 ) steps are accomplished such that the aluminum alloy body achieves an increase in strength as compared to a reference-version of the aluminum alloy body in the T6 temper. In another embodiment, the cold working ( 200 ) and thermally treating ( 300 ) steps are accomplished such that the aluminum alloy body achieves an increase a higher R-value as compared to a reference-version of the aluminum alloy body in the T4 temper. These and other properties are described in the Properties section, below. 
     The “as-cold worked condition” (ACWC) means: (i) the aluminum alloy body is prepared for post-solutionizing cold work, (ii) the aluminum alloy body is cold worked, (iii) not greater than 4 hours elapse between the completion of the solutionizing step ( 140 ) and the initiation of the cold working step ( 200 ), and (iv) the aluminum alloy body is not thermally treated. The mechanical properties of the aluminum alloy body in the as-cold worked condition should be measured within 4-14 days of completion of the cold working step ( 200 ). To produce a reference-version of the aluminum alloy body in the “as-cold worked condition”, one would generally prepare an aluminum alloy body for post-solutionizing cold work ( 100 ), and then cold work the aluminum alloy body ( 200 ) according to the practices described herein, after which a portion of the aluminum alloy body is removed to determine its properties in the as-cold worked condition per the requirements described above. Another portion of the aluminum alloy body would be processed in accordance with the new processes described herein, after which its properties would be measured, thus facilitating a comparison between the properties of the reference-version of the aluminum alloy body in the as-cold worked condition and the properties of an aluminum alloy body processed in accordance with the new processes described herein (e.g., to compare strength, ductility, fracture toughness). Since the reference-version of the aluminum alloy body is produced from a portion of the aluminum alloy body, it would have the same composition as the aluminum alloy body. 
     The “T6 temper” and the like means an aluminum alloy body that has been solutionized and then thermally treated to a maximum strength condition (within 1 ksi of peak strength); applies to bodies that are not cold worked after solutionizing, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits. As described in further detail below, aluminum alloy bodies produced in accordance with the new processes described herein may achieve superior as compared to the aluminum alloy body in a T6 temper. To produce a reference-version of the aluminum alloy body in a T6 temper, one would prepare an aluminum alloy body for post-solutionizing cold work ( 100 ), after which a portion of the aluminum alloy body would be processed to a T6 temper (i.e., a referenced aluminum alloy body in the T6 temper). Another portion of the aluminum alloy body would be processed in accordance with the new processes described herein, thus facilitating a comparison between the properties of the reference-version of the aluminum alloy body in the T6 temper and the properties of an aluminum alloy body processed in accordance with the new processes described herein (e.g., to compare strength, ductility, fracture toughness). Since the reference-version of the aluminum alloy body is produced from a portion of the aluminum alloy body, it would have the same composition as the aluminum alloy body. The reference-version of the aluminum alloy body may require work (hot and/or cold) before the solutionizing step ( 140 ) to place the reference-version of the aluminum alloy body in a comparable product form to the new aluminum alloy body (e.g., to achieve the same final thickness for rolled products). 
     The “T4 temper” and the like means an aluminum alloy body that has been solutionized and then naturally aged to a substantially stable condition; applies to bodies that are not cold worked after solutionizing, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits. To produce a reference-version of the aluminum alloy body in a T4 temper, one would prepare an aluminum alloy body for post-solutionizing cold work ( 100 ), after which a portion of the aluminum alloy body would be allowed to naturally age to a T4 temper (i.e., a referenced aluminum alloy body in the T4 temper). Another portion of the aluminum alloy body would be processed in accordance with the new processes described herein, thus facilitating a comparison between the properties of the reference-version of the aluminum alloy body in the T4 temper and the properties of an aluminum alloy body processed in accordance with the new processes described herein (e.g., to compare strength, ductility, fracture toughness). Since the reference-version of the aluminum alloy body is produced from a portion of the aluminum alloy body, it would have the same composition as the aluminum alloy body. The reference-version of the aluminum alloy body may require work (hot and/or cold) before the solutionizing step ( 140 ) to place the reference-version of the aluminum alloy body in a comparable product form to the new aluminum alloy body (e.g., to achieve the same thickness for rolled products). 
     E. Microstructure 
     i. Recrystallization 
     The cold working ( 200 ) and thermally treating ( 300 ) steps may be accomplished such that the aluminum alloy body achieves/maintains a predominately unrecrystallized microstructure. A predominately unrecrystallized microstructure means that the aluminum alloy body contains less than 50% of first type grains (by volume fraction), as defined below. 
     An aluminum alloy body has a crystalline microstructure. A “crystalline microstructure” is the structure of a polycrystalline material. A crystalline microstructure has crystals, referred to herein as grains. “Grains” are crystals of a polycrystalline material. 
     “First type grains” means those grains of a crystalline microstructure that meet the “first grain criteria”, defined below, and as measured using the OIM (Orientation Imaging Microscopy) sampling procedure, described below. Due to the unique microstructure of the aluminum alloy body, the present application is not using the traditional terms “recrystallized grains” or “unrecrystallized grains”, which can be ambiguous and the subject of debate, in certain circumstances. Instead, the terms “first type grains” and “second type grains” are being used where the amount of these types of grains is accurately and precisely determined by the use of computerized methods detailed in the OIM sampling procedure. Thus, the term “first type grains” includes any grains that meet the first grain criteria, and irrespective of whether those skilled in the art would consider such grains to be unrecrystallized or recrystallized. 
     The OIM analysis is to be completed from the T/4 (quarter-plane) location to surface of the L-ST plane. The size of the sample to be analyzed will generally vary by gauge. Prior to measurement, the OIM samples are prepared by standard metallographic sample preparation methods. For example, the OIM samples are generally polished with Buehler Si—C paper by hand for 3 minutes, followed by polishing by hand with a Buehler diamond liquid polish having an average particle size of about 3 microns. The samples are anodized in an aqueous fluoric-boric solution for 30-45 seconds. The samples are then stripped using an aqueous phosphoric acid solution containing chromium trioxide, and then rinsed and dried. 
     The “OIM sample procedure” is as follows:
         The software used is TexSEM Lab OIM Data Collection Software version 5.31 (EDAX Inc., New Jersey, U.S.A.), which is connected via FIREWIRE (Apple, Inc., California, U.S.A.) to a DigiView 1612 CCD camera (TSL/EDAX, Utah, U.S.A.). The SEM is a JEOL JSM6510 (JEOL Ltd. Tokyo, Japan).   OIM run conditions are 70° tilt with a 18 mm working distance and an accelerating voltage of 20 kV with dynamic focusing and spot size of 1 times 10 −7  amp. The mode of collection is a square grid. A selection is made such that orientations are collected in the analysis (i.e., Hough peaks information is not collected). The area size per scan (i.e., the frame) is 2.0 mm by 0.5 mm for 2 mm gauge samples and 2.0 mm by 1.2 mm for 5 mm gauge samples at 3 micron steps at 80×. Different frame sizes can be used depending upon gauge. The collected data is output in an *.osc file. This data may be used to calculate the volume fraction of first type grains, as described below.   Calculation of volume fraction of first type grains: The volume fraction of first type grains is calculated using the data of the *.osc file and the TexSEM Lab OIM Analysis Software version 5.31. Prior to calculation, data cleanup may be performed with a 15° tolerance angle, a minimum grain size=3 data points, and a single iteration cleanup. Then, the amount of first type grains is calculated by the software using the first grain criteria (below).   First grain criteria: Calculated via grain orientation spread (GOS) with a grain tolerance angle of 5°, minimum grain size is three (3) data points, and confidence index is zero (0). All of “apply partition before calculation”, “include edge grains”, and “ignore twin boundary definitions” should be required, and the calculation should be completed using “grain average orientation”. Any grain whose GOS is ≦3° is a first type grain. If multiple frames are used, the GOS data are averaged.       

     “First grain volume” (FGV) means the volume fraction of first type grains of the crystalline material. 
     “Percent Unrecrystallized” and the like is determined via the formula:
 
 U   RX %=(1−FGV)*100%
 
As mentioned above, the aluminum alloy body generally comprises a predominately unrecrystallized microstructure, i.e., FGV&lt;0.50 and U RX %≧50%. In one embodiment, the aluminum alloy body contains (by volume fraction) not greater than 0.45 first type grains (i.e., the aluminum alloy body is at least 55% unrecrystallized (U RX %≧55%), per the definitions provided above). In other embodiments, the aluminum alloy body may contain (by volume fraction) not greater than 0.40 first type grains (U RX %≧60%), or not greater than 0.35 first type grains (U RX %≧65%), or not greater than 0.30 first type grains (U RX %≧70%), or not greater than 0.25 first type grains (U RX %≧75%), or not greater than 0.20 first type grains (U RX %≧80%), or not greater than 0.15 first type grains (U RX %≧85%), or not greater than 0.10 first type grains (U RX %≧90%), or less.
 
     ii. Texture 
     The aluminum alloy body may achieve a unique microstructure. This unique microstructure may be illustrated by the R-values of the aluminum alloy body derived from crystallographic texture data. The microstructure of an aluminum alloy body relates to its properties (e.g., strength, ductility, toughness, corrosion resistance, among others). 
     For purposes of the present application, R-values are generated according to the R-value generation procedure, described below. 
     R-Value Generation Procedure: 
     
         
         
           
             Instrument: An x-ray generator with a computer-controlled pole figure unit (e.g., Rigaku Ultima III diffractometer (Rigaku USA, The Woodlands, Tex.) and data collection software and ODF software for processing pole figure data (e.g., Rigaku software included with the Rigaku diffractometer) is used. The reflection pole figures are captured in accordance with “Elements of X-ray Diffraction” by B. D. Cullity, 2 nd  edition 1978 (Addison-Wesley Series in Metallurgy and Materials) and the Rigaku User Manual for the Ultima III Diffractometer and Multipurpose Attachment (or other suitable manual of other comparable diffractometer equipment). 
             Sample preparation: The pole figures are to be measured from the T/4 location to surface. Thus, the sample used for R-value generation is (preferably) ⅞ inch (LT) by 1¼ inches (L). Sample size may vary based on measurement equipment. Prior to measurement of the R-value, the sample may be prepared by: 
           
         
       
    
     1. machine the rolling plane from one side to 0.01″ thicker than the T/4 plane (if thickness justifies); and 
     2. chemically etching to the T/4 location.
         X-Ray measurement of pole figures: Reflection of pole figure (based on Schulz Reflection Method)   1. Mount a sample on the sample ring holder with an indication of the rolling direction of the sample   2. Insert the sample holder unit into the pole figure unit   3. Orient the direction of the sample to the same horizontal plane of the pole figure unit (β=0°)   4. Use a normal divergence slit (DS), standard pole figure receiving slit (RS) with Ni K β  filter, and standard scatter slit (SS) (slit determination will depend on radiation used, the 2θ of the peaks, and the breadth of the peaks). The Rigaku Ultima III diffractometer uses ⅔ deg DS, 5 mm RS, and 6 mm SS.   5. Set the power to recommended operating voltage and current (default 40 KV 44 mA for Cu radiation with Ni filter on the Ultima III)   6. Measure the background intensity from α=15°, β=0° to α=90°, β=355° of the Al (111) , Al (200) , and Al (220)  peaks at 5° steps and counting for 1 second at each step (three pole figures are usually sufficient for an accurate ODF)   7. Measure the peak intensity from α=15°, β=0° to α=90°, β=355° of Al (111) , Al (200) , Al (220) , and Al (311)  peaks at 5° steps and counting for 1 second at each step   8. During measurements, the sample should be oscillated 2 cm per second to achieve a larger sampling area for improved sampling statistics   9. Subtract the background intensity from the peak intensity (this is usually done by the user-specific software)   10. Correct for absorption (usually done by the user-specific software)
 
The output data are usually converted to a format for input into ODF software. The ODF software normalizes the data, calculates the ODF, and recalculates normalized pole figures. From this information, R-values are calculated using the Taylor-Bishop-Hill model (see, Kuroda, M. et al.,  Texture optimization of rolled aluminum alloy sheets using a genetic algorithm , Materials Science and Engineering A 385 (2004) 235-244 and Man, Chi-Sing,  On the r - value of textured sheet metals , International Journal of Plasticity 18 (2002) 1683-1706).
       

     Aluminum alloy bodies produced in accordance with the presently described methods may achieve high normalized R-values as compared to conventionally produced materials. “Normalized R-value” and the like means the R-value as normalized by the R-value of the RV-control sample at an angle of 0° relative to the rolling direction. For example, if the RV-control sample achieves an R-value of 0.300 at an angle of 0° relative to the rolling direction, this and all other R-values would be normalized by dividing by 0.300. 
     “RV-control sample” and the like means a control sample taken from a reference-version aluminum alloy body in a T4 temper (defined above). 
     “Rolling direction” and the like means the L-direction for rolled products (see,  FIG. 13 ). For non-rolled products, and in the context of R-values “rolling direction” and the like means the principle direction of extension (e.g., the extrusion direction). For purposes of the present application, the various R-values of a material are calculated from an angle of 0° to an angle of 90° relative to the rolling direction, and in increments of 5°. For purposes of simplicity, “orientation angle” is sometimes used to refer to the phrase “angle relative to the rolling direction”. 
     “Maximum normalized R-value” and the like means the maximum normalized R-value achieved at any angle relative to the rolling direction. 
     “Max RV angle” and the like means the angle at which the maximum normalized R-value is achieved. 
     As a non-limiting example, a chart containing R-values (both non-normalized and normalized) of an RV-control sample and an aluminum alloy body processed in accordance with the new processes described herein is provided in Table 2, below. 
     
       
         
               
               
               
               
               
             
               
               
               
               
               
             
           
               
                 TABLE 2 
               
               
                   
               
               
                   
                   
                 Normalized 
                 R-value 
                 Normalized R-value 
               
               
                 Rolling 
                 R-value 
                 R-value 
                 (New Process) 
                 (New Process) 
               
               
                 Angle 
                 (Control) 
                 (Control) 
                 (75% CW) 
                 (75% CW) 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                 0 
                 0.300 
                 1.000 
                 0.781 
                 2.604 
               
               
                 5 
                 0.298 
                 0.996 
                 0.776 
                 2.589 
               
               
                 10 
                 0.304 
                 1.014 
                 0.777 
                 2.593 
               
               
                 15 
                 0.310 
                 1.033 
                 0.897 
                 2.992 
               
               
                 20 
                 0.325 
                 1.084 
                 1.097 
                 3.660 
               
               
                 25 
                 0.353 
                 1.177 
                 1.318 
                 4.397 
               
               
                 30 
                 0.382 
                 1.274 
                 1.549 
                 5.168 
               
               
                 35 
                 0.408 
                 1.361 
                 1.794 
                 5.983 
               
               
                 40 
                 0.410 
                 1.368 
                 2.087 
                 6.962 
               
               
                 45 
                 0.424 
                 1.415 
                 2.364 
                 7.886 
               
               
                 50 
                 0.410 
                 1.367 
                 2.456 
                 8.192 
               
               
                 55 
                 0.415 
                 1.384 
                 2.423 
                 8.082 
               
               
                 60 
                 0.383 
                 1.277 
                 2.372 
                 7.912 
               
               
                 65 
                 0.376 
                 1.253 
                 1.958 
                 6.532 
               
               
                 70 
                 0.357 
                 1.192 
                 1.512 
                 5.043 
               
               
                 75 
                 0.342 
                 1.141 
                 1.237 
                 4.125 
               
               
                 80 
                 0.327 
                 1.091 
                 1.056 
                 3.523 
               
               
                 85 
                 0.319 
                 1.064 
                 0.881 
                 2.939 
               
               
                 90 
                 0.314 
                 1.047 
                 0.866 
                 2.888 
               
               
                   
               
             
          
         
       
     
     The normalized R-values for the Control and the 75% Cold Work samples are plotted as function of orientation angle in  FIG. 10 .  FIG. 10  also contains the normalized R-values for aluminum alloy bodies with 25%, 50% and 85% cold work. 
     As illustrated in  FIG. 10 , the example aluminum alloy bodies achieve much higher R-values than the RV-control sample, especially between orientation angles of 20° and 70° relative to the rolling direction. For the 75% cold worked body, a maximum normalized R-value of 8.192 is achieved at a max RV angle of 50°. The RV-control sample achieves a maximum normalized R-value of 1.415 at a max RV angle of 45°. These R-values may be indicative of the texture (and hence microstructure) of the new aluminum alloy bodies as compared to conventionally produced aluminum alloy bodies. 
     In one approach, an aluminum alloy body processed in accordance with the new methods described herein may achieve a maximum normalized R-value of at least 2.0. In one embodiment, the new aluminum alloy body may achieve a maximum normalized R-value of at least 2.5. In other embodiments, the new aluminum alloy body may achieve a maximum normalized R-value of at least 3.0, or at least 3.5, or at least 4.0, or at least 4.5, or at least 5.0, at least 5.5, or at least 6.0, or at least 6.5, or at least 7.0, or at least 7.5, or at least 8.0, or at least 8.25, or higher. The maximum normalized R-value may be achieved at an orientation angle of from 20° to 70°. In some embodiments, the maximum normalized R-value may be achieved at an orientation angle of from 30° to 70°. In other embodiments, the maximum normalized R-value may be achieved at an orientation angle of from 35° to 65°. In yet other embodiments, the maximum normalized R-value may be achieved at an orientation angle of from 40° to 65°. In yet other embodiments, the maximum normalized R-value may be achieved at an orientation angle of from 45° to 60°. In other embodiments, the maximum normalized R-value may be achieved at an orientation angle of from 45° to 55°. 
     In another approach, an aluminum alloy body processed in accordance with the new methods described herein may achieve a maximum normalized R-value that is at least 200% higher than the RV-control sample at the max RV angle of the new aluminum alloy body. In this approach, the normalized R-value of the new aluminum alloy body is compared to the normalized R-value of the RV-control sample at the angle where the max RV angle of the new aluminum alloy body occurs. For example, as shown in  FIG. 10  and Table 2, above, the 75% cold worked aluminum alloy body realizes a 599% increase in normalized R-value at its max RV angle of 50° as compared to the normalized R-value of the RV-control sample at the same angle of 50° (8.192/1.367*100%=599%). In one embodiment, an aluminum alloy body may achieve a maximum normalized R-value that is at least 250% higher than the RV-control sample at the max RV angle of the new aluminum alloy body. In other embodiments, the aluminum alloy body may achieve a maximum normalized R-value that is at least 300% higher, or at least 350% higher, or at least 400% higher, or at least 450% higher, or at least 500% higher, or at least 550% higher, or at least 600% higher, or more, than the RV-control sample at the max RV angle of the aluminum alloy body. 
     In another approach, an aluminum alloy body processed in accordance with the new methods described herein may achieve a maximum normalized R-value that is at least 200% higher than the maximum normalized R-value of the RV-control sample. In this approach, the maximum normalized R-value of the new aluminum alloy body is compared to the maximum normalized R-value of the RV-control sample, irrespective of the angle at which the maximum normalized R-values occur. For example, as shown in  FIG. 10  and Table 2, above, the 75% cold worked aluminum alloy body alloy realizes a maximum normalized R-value of 8.192 at an orientation angle of 50°. The maximum normalized R-value of the RV-control sample is 1.415 at an orientation angle of 45°. Thus, the 75% cold worked aluminum alloy body realizes a 579% increase in maximum normalized R-value over the RV-control sample (8.192/1.415=579%). In one embodiment, an aluminum alloy body may achieve a maximum normalized R-value that is at least 250% higher than the maximum normalized R-value of the RV-control sample. In other embodiments, the aluminum alloy body may achieve a maximum normalized R-value that is at least 300% higher, or at least 350% higher, or at least 400% higher, or at least 450% higher, or at least 500% higher, or at least 550% higher, or at least 600% higher, or more, than the maximum normalized R-value of the RV-control sample. 
     iii. Micrographs 
     Optical micrographs of some 7xxx aluminum alloys bodies produced in accordance with the new processes described herein are illustrated in  FIGS. 11   b - 11   e .  FIG. 11   a  is a microstructure of a reference-version of the aluminum alloy body in the T6 temper.  FIGS. 11   b - 11   e  are microstructures of new aluminum alloy bodies having 25%, 50%, 75% and 85% cold work, respectively. These micrographs illustrate some aspects of the unique microstructures that may be attained using the new processes described herein. As illustrated, the grains of the new aluminum alloy bodies appear to be non-equiaxed (elongated) grains. For the 75% and 85% cold-worked bodies, the grain structure appears fibrous/rope-like, and with a plurality of shear bands. These unique microstructures may contribute to the improved properties of the new aluminum alloy bodies. 
     F. Optional Post-Thermal Treatments 
     After the thermal treatment step ( 300 ), the 7xxx aluminum alloy body may be subjected to various optional final treatment(s) ( 400 ). For example, concomitant to or after the thermal treatments step ( 300 ), the 7xxx aluminum alloy body may be subjected to various additional working or finishing operations (e.g., forming operations, flattening or straightening operations that do not substantially affect mechanical properties, such as stretching, and/or other operations, such as machining, anodizing, painting, polishing, buffing). The optional final treatment(s) step ( 400 ) may be absent of any purposeful/meaningful thermal treatment(s) that would materially affect the microstructure of the aluminum alloy body (e.g., absent of any anneal steps). Thus, the microstructure achieved by the combination of the cold working ( 200 ) and thermally treating ( 300 ) steps may be retained. 
     In one approach, one or more of the optional final treatment(s) ( 400 ) may be completed concomitant to the thermal treatment step ( 300 ). In one embodiment, the optional final treatment(s) step ( 400 ) may include forming, and this forming step may be completed concomitant to (e.g., contemporaneous to) the thermal treatment step ( 300 ). In one embodiment, the aluminum alloy body may be in a substantially final form due to concomitant forming and thermal treatment operations (e.g., forming automotive door outer and/or inner panels during the thermal treatment step). 
     G. Composition 
     As noted above, the 7xxx aluminum alloy body is made from a 7xxx aluminum alloy. 7xxx aluminum alloys are aluminum alloys containing zinc as the predominate alloying ingredient other than aluminum. For purposes of the present application, 7xxx aluminum alloys are aluminum alloys having at least 2.0 wt. % Zn, and up to 22 wt. % Zn, with the zinc being the predominate alloying element other than aluminum. The 7xxx aluminum alloy may also include secondary elements, tertiary elements and/or other elements, as defined below. The zinc, secondary elements and/or tertiary elements may promote a strain hardening response, a precipitation hardening response, and combinations thereof. In one embodiment, at least some of the alloying elements promote both a strain hardening response and a precipitation hardening response. In turn, improved properties may be realized. 
     In one embodiment, the 7xxx aluminum alloy includes at least 3.0 wt. % Zn. In another embodiment, the 7xxx aluminum alloy includes at least 4.0 wt. % Zn. In yet another embodiment, the 7xxx aluminum alloy body includes at least 5.0 wt. % Zn. 
     In one embodiment, the 7xxx aluminum alloy includes not greater than 18 wt. % Zn. In another embodiment, the 7xxx aluminum alloy includes not greater than 15.0 wt. % Zn. In another embodiment, the 7xxx aluminum alloy includes not greater than 12.0 wt. % Zn. In yet another embodiment, the 7xxx aluminum alloy includes not greater than 10.0 wt. % Zn. In another embodiment, the 7xxx aluminum alloy includes not greater than 9.0 wt. % Zn. 
     The 7xxx aluminum alloy may include secondary elements. The secondary elements are selected from the group consisting of magnesium, copper and combinations thereof. In one embodiment, the 7xxx aluminum alloy includes magnesium. In another embodiment, the 7xxx aluminum alloy includes copper. In yet another embodiment, the 7xxx aluminum alloy includes both magnesium and copper. 
     When magnesium is used, the 7xxx aluminum alloy generally includes at least 0.25 wt. % Mg. In one embodiment, the 7xxx aluminum alloy includes at least 0.5 wt. % Mg. In another embodiment, the 7xxx alloy includes at least 1.0 wt. % Mg. The 7xxx aluminum alloy generally includes not greater than 6.0 wt. % Mg, such as not greater than 5.0 wt. % Mg. In one embodiment, the 7xxx aluminum alloy includes not greater than 4.0 wt. % Mg. In another embodiment, the 7xxx aluminum alloy includes not greater than 3.0 wt. % Mg. In other embodiments, magnesium may be present as an impurity, and in these embodiments is present at levels of 0.24 wt. % or less. 
     When copper is used, the 7xxx aluminum alloy generally includes at least 0.25 wt. % Cu. In one embodiment, the 7xxx aluminum alloy includes 0.5 wt. % Cu. In yet another embodiment, the 7xxx aluminum alloy includes at least 1.0 wt. % Cu. The 7xxx aluminum alloy generally includes not greater than 6.0 wt. % Cu. In one embodiment, the 7xxx aluminum alloy includes not greater than 5.0 wt. % Cu. In other embodiments, the 7xxx aluminum alloy includes not greater than 4.0 wt. % Cu, or not greater than 3.5 wt. % Cu. In one embodiment, the 7xxx aluminum alloy includes not greater than 3.0 wt. % Cu. In other embodiments, copper may be present as an impurity, and in these embodiments is present at levels of 0.24 wt. % or less. 
     The 7xxx aluminum alloy may include a variety of tertiary elements for various purposes, such as to enhance mechanical, physical or corrosion properties (i.e., strength, toughness, fatigue resistance, corrosion resistance), to enhance properties at elevated temperatures, to facilitate casting, to control cast or wrought grain structure, and/or to enhance machinability, among other purposes. When present, these tertiary elements may include one or more of: (i) up to 5.0 wt. % Li, (ii) up to 2.0 wt. % each of one or more of Mn, Si, Ag, Sn, Bi, and Pb, (iii) up to 1.0 wt. % each of one or more of Fe, Sr, and Sb, and (iv) up to 0.5 wt. % each of one or more of Ni, V, Cr, Zr, Sc, Ti, Hf, Mo, Co, and rare earth elements. When present, a tertiary element is usually contained in the alloy by an amount of at least 0.01 wt. %. 
     In some embodiments, the 7xxx aluminum alloy may include at least one grain structure control element, such as any of Zr, Sc and Hf. In less preferred embodiments, Mn, Cr, Ni and/or V may be used for grain structure control. In one embodiment, the grain structure control element is Zr and the alloy includes 0.05 to 0.25 wt. % Zr. In some of these embodiments, the 7xxx aluminum alloy may contain less than 0.25 wt. % of each of Cr, Ni, V, and Mn, such as not greater than 0.15 wt. % of each of Cr, Ni, V, and Mn, or not greater than 0.10 wt. % of each of Cr, Ni, V, and Mn. In one embodiment, the 7xxx aluminum alloy includes Cr, Ni, V, and Mn as impurities, i.e., not more than 0.05 wt. % of each of Cr, Ni, V, and Mn. 
     In one embodiment, the 7xxx aluminum alloy includes at least one grain refiner, such as titanium, usually with either boron or carbon (e.g., when using semi-continuous casting processes). When utilized, the 7xxx aluminum alloy may include from 0.01 to 0.06 wt. % Ti. 
     The 7xxx aluminum alloy may include impurities, such as iron and silicon. When silicon and/or iron are not included in the alloy as a tertiary element, silicon and/or iron may be included in the 7xxx aluminum alloy as an impurity. In these embodiments, the 7xxx aluminum alloy generally includes not greater than 0.50 wt. % of either silicon and iron. In one embodiment, the 7xxx aluminum alloy includes not greater than 0.25 wt. % of either silicon and iron. In another embodiment, the 7xxx aluminum alloy includes not greater than 0.15 wt. % of either silicon and iron. In yet another embodiment, the 7xxx aluminum alloy includes not greater than 0.10 wt. % of either silicon and iron. In another embodiment, the 7xxx aluminum alloy includes not greater than 0.05 wt. % of at least one of silicon and iron. 
     The 7xxx aluminum alloy generally contains low amounts of “other elements” (e.g., casting aids and impurities, other than Fe and Si). Other elements means any other element of the periodic table that may be included in the 7xxx aluminum alloy, except for the aluminum, the zinc, the secondary elements (when included), the tertiary elements (when included), and the Fe and Si impurities (when included), described above. When any element of the secondary and/or tertiary elements is contained within the alloy only as an impurity, such elements fall within the scope of “other elements”, except for iron and silicon. For example, if a 7xxx alloy includes copper as an impurity, and not as an alloying addition, the copper would fall within the scope of “other elements”. As another example, if Mn, Ag, and Zr are included in the 7xxx alloy as alloying additions, those tertiary elements would not fall within the scope of “other elements”, but the other tertiary elements would be included within the scope of other elements since they would be included in the alloy only as an impurity. However, if silicon or iron is contained in the 7xxx alloy as an impurity, they would not fall within the scope of “other elements” since they have their own defined impurity limits, as described above. 
     Generally, the aluminum alloy body contains not more than 0.25 wt. % each of any element of the other elements, with the total combined amount of these other elements not exceeding 0.50 wt. %. In one embodiment, each one of these other elements, individually, does not exceed 0.10 wt. % in the 7xxx aluminum alloy, and the total combined amount of these other elements does not exceed 0.35 wt. %, in the 7xxx aluminum alloy. In another embodiment, each one of these other elements, individually, does not exceed 0.05 wt. % in the 7xxx aluminum alloy, and the total combined amount of these other elements does not exceed 0.15 wt. % in the 7xxx aluminum alloy. In another embodiment, each one of these other elements, individually, does not exceed 0.03 wt. % in the 7xxx aluminum alloy, and the total combined amount of these other elements does not exceed 0.1 wt. % in the 7xxx aluminum alloy. 
     In one approach, the 7xxx aluminum alloy includes: 
     2.0 to 22 wt. % Zn, wherein the Zn is the predominate alloying element other than aluminum; 
     optionally one or more of the secondary elements of:
         0.25 to 6.0 wt. % Mg,   0.25 to 5.0 wt. % Cu,       

     optionally with one or more of the tertiary elements of:
         (i) up to 5.0 wt. % Li,   (ii) up to 2.0 wt. % each of one or more of Mn, Si, Ag, Sn, Bi, and Pb;   (iii) up to 1.0 wt. % each of one or more of Fe, Sr and Sb;   (iv) up to 0.5 wt. % each of one or more of Ni, V, Cr, Zr, Sc, Ti, Hf, Mo, Co, and rare earth elements,       

     if not included in the 7xxx aluminum alloy as a tertiary element:
         up to 0.5 wt. % Fe as an impurity;   up to 0.5 wt. % Si as an impurity;
 
the balance being aluminum and other elements, wherein the other elements are limited to not more than 0.25 wt. % each, and not more than 0.5 wt. % in total.
       

     The total amount of the primary, secondary, and tertiary alloying elements should be chosen so that the aluminum alloy body can be appropriately solutionized (e.g., to promote hardening while restricting the amount of constituent particles). 
     In one embodiment, the 7xxx aluminum alloy is one of the following wrought 7xxx aluminum alloys, as defined by the Aluminum Association: 7003, 7004, 7204, 7005, 7108, 7108A, 7009, 7010, 7012, 7014, 7015, 7016, 7116, 7017, 7018, 7019, 7019A, 7020, 7021, 7022, 7122, 7023, 7024, 7025, 7026, 7028, 7029, 7129, 7229, 7030, 7031, 7032, 7033, 7034, 7035, 7035A, 7036, 7136, 7037, 7039, 7040, 7140, 7041, 7046, 7046A, 7049, 7049A, 7149, 7249, 7349, 7449, 7050, 7050A, 7150, 7250, 7055, 7155, 7255, 7056, 7060, 7064, 7068, 7168, 7072, 7075, 7175, 7475, 7076, 7178, 7278, 7278A, 7081, 7085, 7185, 7090, 7093, and 7095. 
     In one embodiment, the 7xxx aluminum alloy includes an amount of alloying elements that leaves the 7xxx aluminum alloy free of, or substantially free of, soluble constituent particles after solutionizing. In one embodiment, the 7xxx aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy with low amounts of (e.g., restricted/minimized) insoluble constituent particles after solutionizing. In other embodiments, the 7xxx aluminum alloy may benefit from controlled amounts of insoluble constituent particles. 
     H. Properties 
     The new 7xxx aluminum alloy bodies produced by the new processes described herein may achieve (realize) an improved combination of properties. 
     i. Strength 
     As mentioned above, the cold working ( 200 ) and the thermally treating ( 300 ) steps may be accomplished to achieve an increase in strength as compared to a reference-version of the aluminum alloy body in the as cold-worked condition and/or the T6 temper (as defined above). Strength properties are generally measured in accordance with ASTM E8 and B557. 
     In one approach, the aluminum alloy body achieves at least a 5% increase in strength (TYS and/or UTS) relative to a reference-version of the aluminum alloy body in the T6 condition. In one embodiment, the aluminum alloy body achieves at least a 6% increase in tensile yield strength relative to a reference-version of the aluminum alloy body in the T6 condition. In other embodiments, the aluminum alloy body achieves at least a 7% increase in tensile yield strength, or at least a 8% increase in tensile yield strength, or at least a 9% increase in tensile yield strength, or at least a 10% increase in tensile yield strength, or at least a 11% increase in tensile yield strength, or at least a 12% increase in tensile yield strength, or at least a 13% increase in tensile yield strength, or at least a 14% increase in tensile yield strength, or at least a 15% increase in tensile yield strength, or at least a 16% increase in tensile yield strength, or at least a 17% increase in tensile yield strength, or at least an 18% increase in tensile yield strength, or at least a 19% increase in tensile yield strength, or at least a 20% increase in tensile yield strength, or at least a 21% increase in tensile yield strength, or at least a 22% increase in tensile yield strength, or at least a 23% increase in tensile yield strength, or at least a 24% increase in tensile yield strength, or at least a 25% increase in tensile yield strength, or at least a 26% increase in tensile yield strength, or more, relative to a reference-version of the aluminum alloy body in the T6 condition. These increases may be realized in the L and/or LT directions. 
     In a related embodiment, the aluminum alloy body may achieve at least a 6% increase in ultimate tensile strength relative to the aluminum alloy body in the T6 condition. In other embodiments, the aluminum alloy body may achieve at least a 7% increase in ultimate tensile strength, or at least an 8% increase in ultimate tensile strength, or at least a 9% increase in ultimate tensile strength, or at least a 10% increase in ultimate tensile strength, or at least an 11% increase in ultimate tensile strength, or at least a 12% increase in ultimate tensile strength, or at least a 13% increase in ultimate tensile strength, or at least a 14% increase in ultimate tensile strength, or at least a 15% increase in ultimate tensile strength, or at least a 16% increase in ultimate tensile strength, or at least a 17% increase in ultimate tensile strength, or at least an 18% increase in ultimate tensile strength, or more, relative to a reference-version of the aluminum alloy body in the T6 condition. These increases may be realized in the L and/or LT directions. 
     In one approach, the aluminum alloy body achieves at least equivalent tensile yield strength as compared to a reference-version of the aluminum alloy body in the as-cold worked condition. In one embodiment, the aluminum alloy body achieves at least a 1% increase in tensile yield strength as compared to a reference-version of the aluminum alloy body in the as-cold worked condition. In other embodiments, the aluminum alloy body achieves at least a 2% increase in tensile yield strength, or at least a 3% increase in tensile yield strength, or at least a 4% increase in tensile yield strength, or at least a 5% increase in tensile yield strength, or at least a 6% increase in tensile yield strength, or at least a 7% increase in tensile yield strength, or at least an 8% increase in tensile yield strength, or more, as compared to a reference-version of the aluminum alloy body in the as-cold worked condition. Similar results may be obtained relative to ultimate tensile strength. These increases may be realized in the L or LT directions. 
     In one embodiment, a new 7xxx aluminum alloy body realizes a typical tensile yield strength in the LT direction of at least 61 ksi. In other embodiments, a new 7xxx aluminum alloy body realizes a typical tensile yield strength in the LT direction of at least 62 ksi, or at least 63 ksi, or at least 64 ksi, or at least 65 ksi, or at least 66 ksi, or at least 67 ksi, or at least 68 ksi, or at least 69 ksi, or at least 70 ksi, or at least 71 ksi, or at least 72 ksi, or at least 73 ksi, or at least 74 ksi, or at least 75 ksi, or at least 76 ksi, or at least 77 ksi, or at least 78 ksi, or at least 79 ksi, or at least 80 ksi, or at least 81 ksi, or at least 82 ksi, or at least 83 ksi, or at least 84 ksi, or at least 85 ksi, or at least 86 ksi, or at least 87 ksi, or at least 88 ksi, or at least 89 ksi, or at least 90 ksi, or at least 91 ksi, or more. Similar results may be achieved in the longitudinal (L) direction. 
     In a related embodiment, a new 7xxx aluminum alloy body realizes a typical ultimate tensile strength in the LT direction of at least 64 ksi. In other embodiments, a new 7xxx aluminum alloy body realizes a typical ultimate tensile strength in the LT direction of at least 65 ksi, or at least 66 ksi, or at least 67 ksi, or at least 68 ksi, or at least 69 ksi, or at least 70 ksi, or at least 71 ksi, or at least 72 ksi, or at least 73 ksi, or at least 74 ksi, or at least 75 ksi, or at least 76 ksi, or at least 77 ksi, or at least 78 ksi, or at least 79 ksi, or at least 80 ksi, or at least 81 ksi, or at least 82 ksi, or at least 83 ksi, or at least 84 ksi, or at least 85 ksi, or at least 86 ksi, or at least 87 ksi, or at least 88 ksi, or at least 89 ksi, or at least 90 ksi, or at least 91 ksi, or at least 92 ksi, or at least 93 ksi, or at least 94 ksi, or at least 95 ksi, or at least 96 ksi, or at least 97 ksi, or at least 98 ksi, or at least 99 ksi, or more. Similar results may be achieved in the longitudinal (L) direction. 
     The new 7xxx aluminum alloy bodies may achieve a high strength and in a short time period relative to a reference-version of the 7xxx aluminum alloy body in the T6 temper. In one embodiment, a new 7xxx aluminum alloy body realizes its peak strength at least 10% faster than a reference-version of the aluminum alloy body in the T6 temper. As an example of 10% faster processing, if the T6-version of the 7xxx aluminum alloy body realizes its peak strength in 35 hours of processing, the new 7xxx aluminum alloy body would realize its peak strength in 31.5 hours or less. In other embodiments, the new 7xxx aluminum alloy body realizes it peak strength at least 20% faster, or at least 25% faster, or at least 30% faster, or at least 35% faster, or at least 40% faster, or at least 45% faster, or at least 50% faster, or at least 55% faster, or at least 60% faster, or at least 65% faster, or at least 70% faster, or at least 75% faster, or at least 80% faster, or at least 85% faster, or at least 90% faster, or more, as compared to a reference-version of the aluminum 7xxx aluminum alloy body in the T6 temper. 
     In one embodiment, a new 7xxx aluminum alloy body realizes its peak strength in less than 10 hours of thermal treatment time. In other embodiments, a new 7xxx aluminum alloy body realizes its peak strength in less than 9 hours, or less than 8 hours, or less than 7 hours, or less than 6 hours, or less than 5 hours, or less than 4 hours, or less than 3 hours, or less than 2 hours, or less than 1 hour, or less than 50 minutes, or less than 40 minutes, or less than 30 minutes, or less than 20 minutes, or less than 15 minutes, or less than 10 minutes of thermal treatment time, or less. Due to the short thermal treatment times, it is possible that paint baking cycles or coating cures could be used to thermally treat the new 7xxx aluminum alloy bodies. 
     ii. Ductility 
     The aluminum alloy body may realize good ductility and in combination with the above-described strengths. In one approach, the aluminum alloy body achieves an elongation (L and/or LT) of more than 4%. In one embodiment, the aluminum alloy body achieves an elongation (L and/or LT) of at least 5%. In other embodiments, the aluminum alloy body may achieve an elongation (L and/or LT) of at least 6%, or at least 7%, or at least 8%, or at least 9%, or at least 10%, or at least 11%, or at least 12%, or more. 
     The aluminum alloy body may realize improved ductility relative to a reference-version of the aluminum alloy body in the as-cold worked condition. In one approach, an aluminum alloy body is at least 5% more ductile (as measured by elongation values) than a reference-version of the aluminum alloy body in the as-cold worked condition. In one embodiment, the aluminum alloy body is at least 10% more ductile than a reference-version of the aluminum alloy body in the as-cold worked condition. In other embodiments, the aluminum alloy body is at least 15% more ductile, or at least 20% more ductile, or at least 25% more ductile, or more, as compared to a reference-version of the aluminum alloy body in the as-cold worked condition. 
     iii. Fracture Toughness 
     The new 7xxx aluminum alloy bodies may realize good fracture toughness properties. Toughness properties are generally measured in accordance with ASTM E399 and ASTM B645 for plane-strain fracture toughness (e.g., K IC  and K Q ) and in accordance with ASTM E561 and B646 for plane-stress fracture toughness (e.g., K app  and K R25 ). 
     In one embodiment, the new 7xxx aluminum alloy body realizes a toughness decrease of not greater than 10% relative to a reference-version of the aluminum alloy body in the T6 temper. In other embodiments, the new 7xxx aluminum alloy body realizes a toughness decrease of not greater than 9%, or not greater than 8%, or not greater than 7%, or not greater than 6%, or not greater than 5%, or not greater than 4%, or not greater than 3%, or not greater than 2%, or not greater than 1% relative to a reference-version of the 7xxx aluminum alloy body in the T6 temper. In one embodiment, the new 7xxx aluminum alloy body realizes a toughness at least equivalent to that of a reference-version of the 7xxx aluminum alloy body in the T6 temper. 
     iv. Electrical Conductivity 
     The corrosion performance of the new 7xxx aluminum alloy bodies may correlate to electrical conductivity. In one embodiment, a new 7xxx aluminum alloy body may realize an electrical conductivity of at least 34% IACS. In other embodiments, a new 7xxx aluminum alloy body may realize an electrical conductivity of at least 34.5% IACS, or at least 35% IACS, or at least 35.5% IACS, or at least 36% IACS, or at least 36.5% IACS, or at least 37% IACS, or at least 37.5% IACS, or at least 38% IACS, or at least 38.5% IACS, or at least 39% IACS, or at least 39.5% IACS, or at least 40% IACS, or at least 40.5% IACS, or at least 41% IACS, or at least 41.5% IACS, or at least 42% IACS, or at least 42.5% IACS, or at least 43% IACS, or at least 43.5% IACS, or at least 44% IACS, or at least 44.5% IACS, or more. These electrical conductivity values may be achieved in combination with improved strength and/or other properties. 
     v. Stress Corrosion Cracking 
     The new 7xxx aluminum alloy bodies may realize good stress corrosion cracking resistance. Stress corrosion cracking (SCC) resistance is generally measured in accordance with ASTM G47. For example, a new 7xxx aluminum alloy body may achieve a good strength and/or toughness, and with good SCC corrosion resistance. In one embodiment, a new 7xxx aluminum alloy body realizes a Level 1 corrosion resistance. In another embodiment, a new 7xxx aluminum alloy body realizes a Level 2 corrosion resistance. In yet another embodiment, a new 7xxx aluminum alloy body realizes a Level 3 corrosion resistance. In yet another embodiment, a new 7xxx aluminum alloy body realizes a Level 4 corrosion resistance. 
     
       
         
               
               
               
             
           
               
                   
                   
               
               
                   
                 Corrosion 
                 Short-transverse stress (ksi) 
               
               
                   
                 Resistance Level 
                 for 20 days (minimum) without failure 
               
               
                   
                   
               
             
             
               
                   
                 1 
                 ≧15 
               
               
                   
                 2 
                 ≧25 
               
               
                   
                 3 
                 ≧35 
               
               
                   
                 4 
                 ≧45 
               
               
                   
                   
               
             
          
         
       
     
     vi. Exfoliation Resistance 
     The new 7xxx aluminum alloy bodies may be exfoliation resistant. Exfoliation resistance is generally measured in accordance with ASTM G34. In one embodiment, an aluminum alloy body realizes an EXCO rating of EB or better. In another embodiment, an aluminum alloy body realizes an EXCO rating of EA or better. In yet another embodiment, an aluminum alloy body realizes an EXCO rating of P, or better. 
     vi. Appearance 
     Aluminum alloy bodies processed in accordance with the new processes disclosed herein may realize improved appearance. The below appearance standards may be measured with a Hunterlab Dorigon II (Hunter Associates Laboratory INC, Reston, Va.), or comparable instrument. 
     Aluminum alloy bodies processed in accordance with the new processes disclosed herein may realize at least 5% higher specular reflectance as compared to the referenced aluminum alloy body in the T6 temper. In one embodiment, the new aluminum alloy bodies realize at least 6% higher specular reflectance as compared to the referenced aluminum alloy body in the T6 temper. In other embodiments, the new aluminum alloy bodies realize at least 7% higher specular reflectance, or at least 8% higher specular reflectance, or at least 9% higher specular reflectance, or at least 10% higher specular reflectance, or at least 11% higher specular reflectance, or at least 12% higher specular reflectance, or at least 13% higher specular reflectance, or more, as compared to the referenced aluminum alloy body in the T6 temper. 
     Aluminum alloy bodies processed in accordance with the new processes disclosed herein may realize at least 10% higher 2 degree diffuseness as compared to the referenced aluminum alloy body in the T6 temper. In one embodiment, the new aluminum alloy bodies realize at least 12% higher 2 degree diffuseness as compared to the referenced aluminum alloy body in the T6 temper. In other embodiments, the new aluminum alloy bodies realize at least 14% higher 2 degree diffuseness, or at least 16% higher 2 degree diffuseness, or at least 18% higher 2 degree diffuseness, or at least 20% higher 2 degree diffuseness, or at least 22% higher 2 degree diffuseness, or more, as compared to the referenced aluminum alloy body in the T6 temper. 
     Aluminum alloy bodies processed in accordance with the new processes disclosed herein may realize at least 15% higher 2 image clarity as compared to the referenced aluminum alloy body in the T6 temper. In one embodiment, the new aluminum alloy bodies realize at least 18% higher 2 image clarity as compared to the referenced aluminum alloy body in the T6 temper. In other embodiments, the new aluminum alloy bodies realize at least 21% higher 2 image clarity, or at least 24% higher 2 image clarity, or at least 27% higher 2 image clarity, or at least 30% higher 2 image clarity, or more, as compared to the referenced aluminum alloy body in the T6 temper. 
     I. Product Applications 
     The new processes described herein may have applicability in a variety of product applications. In one embodiment, a product made by the new processes described herein is used in an aerospace application, such as wing skins (upper and lower) or stringers/stiffeners, fuselage skin or stringers, ribs, frames, spars, seat tracks, bulkheads, circumferential frames, empennage (such as horizontal and vertical stabilizers), floor beams, seat tracks, doors, and control surface components (e.g., rudders, ailerons) among others. Many potential benefits could be realized in such components through use of the products including higher strength, superior corrosion resistance, improved resistance to the initiation and growth of fatigue cracks, and enhanced toughness to name a few. Improved combinations of such properties can result in weight savings or reduced inspection intervals or both. 
     In another embodiment, a product made by the new processes described herein is used in a munitions/ballistics/military application, such as in ammunition cartridges and armor, among others. Ammunition cartridges may include those used in small arms and cannons or for artillery or tank rounds. Other possible ammunition components would include sabots and fins. Artillery, fuse components are another possible application as are fins and control surfaces for precision guided bombs and missiles. Armor components could include armor plates or structural components for military vehicles. In such applications, the products could offer weight savings or improved reliability or accuracy. 
     In another embodiment, a product made by the new processes described herein is used in a fastener application, such as bolts, rivets, screws, studs, inserts, nuts, and lock-bolts, which may be used in the industrial engineering and/or aerospace industries, among others. In these applications, the products could be used in place of other heavier materials, like titanium alloys or steels, for weight reduction. In other cases, the products could provide superior durability. 
     In another embodiment, a product made by the new processes described herein is used in an automotive application, such as closure panels (e.g., hoods, fenders, doors, roofs, and trunk lids, among others), wheels, and critical strength applications, such as in body-in-white (e.g., pillars, reinforcements) applications, among others. In some of these applications the products may allow down-gauging of the components and weight savings. 
     In another embodiment, a product made by the new processes described herein is used in a marine application, such as for ships and boats (e.g., hulls, decks, masts, and superstructures, among others). In some of these applications the products could be used to enable down-gauging and weight reductions. In some other cases, the products could be used to replace products with inferior corrosion resistance resulting in enhanced reliability and lifetimes. 
     In another embodiment, a product made by the new processes described herein is used in a rail application, such as for hopper tank and box cars, among others. In the case of hopper or tank cars, the products could be used for the hoppers and tanks themselves or for the supporting structures. In these cases, the products could provide weight reductions (through down-gauging) or enhanced compatibility with the products being transported. 
     In another embodiment, a product made by the new processes described herein is used in a ground transportation application, such as for truck tractors, box trailers, flatbed trailers, buses, package vans, recreational vehicles (RVs), all-terrain vehicles (ATVs), and the like. For truck tractors, buses, package vans and RV&#39;s, the products could be used for closure panels or frames, bumpers or fuel tanks allowing down-gauging and reduced weight. Correspondingly, the bodies could also be used in wheels to provided enhanced durability or weight savings or improved appearance. 
     In another embodiment, a product made by the new processes described herein is used in an oil and gas application, such as for risers, auxiliary lines, drill pipe, choke-and-kill lines, production piping, and fall pipe, among others. In these applications the product could allow reduced wall thicknesses and lower weight. Other uses could include replacing alternate materials to improve corrosion performance or replacing alternate materials to improve compatibility with drilling or production fluids. The products could also be used for auxiliary equipment employed in exploration like habitation modules and helipads, among others. 
     In another embodiment, a product made by the new processes described herein is used in a packaging application, such as for lids and tabs, food cans, bottles, trays, and caps, among others. In these applications, benefits could include the opportunity for down-gauging and reduced package weight or cost. In other cases, the product would have enhanced compatibility with the package contents or improved corrosion resistance. 
     In another embodiment, a product made by the new processes described herein is used in a reflector, such as for lighting, mirrors, and concentrated solar power, among others. In these applications the products could provide better reflective qualities in the bare, coated or anodized condition at a given strength level. 
     In another embodiment, a product made by the new processes described herein is used in an architecture application, such as for building panels/facades, entrances, framing systems, and curtain wall systems, among others. In such applications, the product could provide superior appearance or durability or reduced weight associated with down-gauging. 
     In another embodiment, a product made by the new processes described herein is used in an electrical application, such as for connectors, terminals, cables, bus bars, and wires, among others. In some cases the product could offer reduced tendency for sag for a given current carrying capability. Connectors made from the product could have enhanced capability to maintain high integrity connections over time. In other wires or cables, the product could provide improved fatigue performance at a given level of current carrying capability. 
     In another embodiment, a product made by the new processes described herein is used in a fiber metal laminate application, such as for producing high-strength sheet products used in the laminate, among others which could result in down-gauging and weight reduction. 
     In another embodiment, a product made by the new processes described herein is used in an industrial engineering application, such as for tread-plate, tool boxes, bolting decks, bridge decks, and ramps, among others where enhanced properties could allow down-gauging and reduced weight or material usage. 
     In another embodiment, a product made by the new processes described herein is used in a fluid container (tank), such as for rings, domes, and barrels, among others. In some cases the tanks could be used for static storage. In others, the tanks could be parts of launch vehicles or aircraft. Benefits in these applications could include down-gauging or enhanced compatibility with the products to be contained. 
     In another embodiment, a product made by the new processes described herein is used in consumer product applications, such as laptops, cell phones, cameras, mobile music players, handheld devices, computers, televisions, microwaves, cookware, washer/dryer, refrigerators, sporting goods, or any other consumer electronic products requiring durability or desirable appearance. In another embodiment, a product made by the new processes described herein is used in a medical device, security systems, and office supplies, among others. 
     In another embodiment, the new process is applied to a cold hole expansion process, such as for treating holes to improve fatigue resistance, among others, which may result in a cold work gradient and tailored properties, as described above. This cold hole expansion process may be applicable to forged wheels and aircraft structures, among others. 
     In another embodiment, the new process is applied to cold indirect extrusion processes, such as for producing cans, bottles, aerosol cans, and gas cylinders, among others. In these cases the product could provide higher strength which could provide reduced material usage. In other cases, improved compatibility with the contents could result in greater shelf life. 
     In another embodiment, a product made by the new processes described herein is used in a heat-exchanger application, such as for tubing and fins, among others where higher strength can be translated into reduced material usage. Improved durability and longer life could also be realized. 
     In another embodiment, the new process is applied to a conforming processes, such as for producing heat-exchanger components, e.g., tubing where higher strength can be translated into reduced material usage. Improved durability and longer life could also be realized. 
     The new 7xxx aluminum alloy products may find use in multi-layer applications. For example it is possible that a multi-layer product may be formed using a 7xxx aluminum alloy body as a first layer and any of the 1xxx-8xxx alloys being used as a second layer.  FIG. 12  illustrates one embodiment of a method for producing multi-layered products. In the illustrated embodiment, a multi-layered product may be produced ( 107 ), after which it is homogenized ( 122 ), hot rolled ( 126 ), solutionized ( 140 ) and then cold rolled ( 220 ), as described above relative to  FIG. 9 . The multi-layered products may be produced via multi-alloy casting, roll bonding, and metallurgical bonding, among others. Multi-alloy casting techniques include those described in U.S. Patent Application Publication No. 20030079856 to Kilmer et al., U.S. Patent Application No. 20050011630 to Anderson et al., U.S. Patent Application No. 20080182122 to Chu et al., and WO2007/098583 to Novelis (the so-called FUSION™ casting process). 
     These and other aspects, advantages, and novel features of this new technology are set forth in part in the description that follows and will become apparent to those skilled in the art upon examination of the description and figures, or may be learned by practicing one or more embodiments of the technology provided for by the patent application. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a flow chart illustrating a conventional process for producing aluminum alloy products. 
         FIG. 2  is a flow chart illustrating a new process for producing aluminum alloy products. 
         FIGS. 3-8  are flow charts illustrating various embodiments of preparing an aluminum alloy body for post-solutionizing cold work. 
         FIG. 9  is a flow chart illustrating one embodiment of a method for producing a rolled aluminum alloy body. 
         FIG. 10  is a graph illustrating R-values as a function of orientation angle for various aluminum alloy bodies. 
         FIGS. 11   a - 11   e  are optical micrographs illustrating aluminum alloy body microstructures; the optical micrographs were obtained by anodizing the samples and viewing them in polarized light. 
         FIG. 12  is a flow chart illustrating one method of producing multi-layered aluminum alloy products. 
         FIG. 13  is a schematic view illustrating the L, LT and ST directions of a rolled product. 
         FIGS. 14-16  are graphs illustrating the thermal treatment response of various 7xxx aluminum alloy bodies for a first 7xxx aluminum alloy composition. 
         FIGS. 17-19  are graphs illustrating the strength-toughness performance of various 7xxx aluminum alloy bodies for the first 7xxx aluminum alloy composition. 
         FIGS. 20-23  are graphs illustrating various properties of various 7xxx aluminum alloy bodies for a second 7xxx aluminum alloy composition. 
         FIGS. 24-27  are graphs illustrating various properties of various 7xxx aluminum alloy bodies for a third 7xxx aluminum alloy composition. 
     
    
    
     DETAILED DESCRIPTION 
     Example 1 
     A first 7xxx aluminum alloy having the composition listed in Table 3, below, is cast, homogenized, and hot rolled into plate/sheet having intermediate gauges of about 0.53 inch, 0.32 inch, 0.16 inch (×2), and 0.106 inch, respectively. One of the 0.16 inch samples (the control) is then cold rolled to a final sheet gauge of about 0.08 in, solution heat treated by soaking at about 885° F. for about 30 minutes, followed by a cold water quench, and then stretching of 1-2% for stress relief. The control is naturally aged for about four days, and then thermally treated to a T6-style temper. 
     The other ones of the samples are first solution heat treated (by the same process) and then cold rolled to a final sheet gauge of 0.08 inch, representing about 85%, 75%, 50%, and 25% cold work, respectively. 
                                                               TABLE 3                   Composition of a 1 st  7xxx alloy (all values in weight percent)            Si   Fe   Cu   Mg   Zn   Zr   Ti   Other Each   Others Total   Bal.               0.02   0.03   2.01   1.59   7.31   0.11   0.02   ≦0.05   ≦0.15   Al                    
These samples are also allowed to naturally age for about four days, and then thermally treated at three temperatures (250° F., 280° F., and 310° F.) for various times. Mechanical and conductivity tests of the samples are then conducted, the results of which are reproduced in Tables 4-6 for each thermal treatment temperature.
 
     
       
         
               
             
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 4 
               
             
             
               
                   
               
               
                 Strength of a 1 st  7xxx aluminum alloy at various thermal treatment times (250° F.) 
               
             
          
           
               
                   
                 Sheet A 
                 Sheet B (new) 
                 Sheet C (new) 
                 Sheet D (new) 
                 Sheet E (new) 
               
               
                   
                 (T6-style) 
                 85% CW 
                 75% CW 
                 50% CW 
                 25% CW 
               
               
                   
                 (ksi) 
                 (ksi) 
                 (ksi) 
                 (ksi) 
                 (ksi) 
               
             
          
           
               
                 Time(hr) 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
               
               
                   
               
             
          
           
               
                 0 
                 49.0 
                 71.8 
                 88.1 
                 99.4 
                 80.5 
                 95.6 
                 73.7 
                 87.6 
                 66.1 
                 81.9 
               
               
                 0.5 
                 57.7 
                 74.8 
                 88.4 
                 96.3 
                 81.1 
                 91.5 
                 70.7 
                 82.3 
                 61.3 
                 75.7 
               
               
                 4 
                 66.3 
                 79.3 
                 91.3 
                 97.8 
                 87.6 
                 92.9 
                 77.9 
                 85.3 
                 71.1 
                 81.7 
               
               
                 12 
                 71.2 
                 80.9 
                 90.5 
                 95.8 
                 87.7 
                 92.4 
                 80.2 
                 86.7 
                 77 
                 84.5 
               
               
                 24 
                 72.9 
                 82.1 
                 90.4 
                 94.8 
                 86.3 
                 91.5 
                 81.0 
                 86.8 
                 78.3 
                 85.3 
               
               
                 36 
                 76.3 
                 83.0 
                 88.9 
                 93.7 
                 85.9 
                 90.9 
                 81.1 
                 86.9 
                 86.9 
                 87.3 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 5 
               
             
             
               
                   
               
               
                 Strength of a 1 st  7xxx aluminum alloy at various thermal treatment times (280° F.) 
               
             
          
           
               
                   
                 Sheet A 
                 Sheet B (new) 
                 Sheet C (new) 
                 Sheet D (new) 
                 Sheet E (new) 
               
               
                   
                 (T6-style) 
                 85% CW 
                 75% CW 
                 50% CW 
                 25% CW 
               
               
                   
                 (ksi) 
                 (ksi) 
                 (ksi) 
                 (ksi) 
                 (ksi) 
               
             
          
           
               
                 Time(hr) 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
               
               
                   
               
             
          
           
               
                 0 
                 49 
                 71.8 
                 88.1 
                 99.4 
                 80.5 
                 95.6 
                 73.7 
                 87.6 
                 66.1 
                 81.9 
               
               
                 0.5 
                 63.5 
                 76.6 
                 91 
                 96.1 
                 83.3 
                 90.7 
                 71.7 
                 81.0 
                 64.5 
                 75.7 
               
               
                 2 
                 68.6 
                 79.7 
                 91.1 
                 95.7 
                 86.1 
                 91.3 
                 76.4 
                 84.1 
                 71.9 
                 80.3 
               
               
                 8 
                 75.1 
                 82.2 
                 88.1 
                 92.4 
                 84.7 
                 89.5 
                 77.8 
                 84.7 
                 75.2 
                 82.9 
               
               
                 16 
                 77.5 
                 83.4 
                 85.5 
                 89.9 
                 83.1 
                 88.1 
                 77.6 
                 84.6 
                 76.8 
                 83.2 
               
               
                 24 
                 79.3 
                 84 
                 82.2 
                 87.8 
                 80.5 
                 86.1 
                 76.9 
                 82.8 
                 75.5 
                 82 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 6 
               
             
             
               
                   
               
               
                 Strength of a 1 st  7xxx aluminum alloy at various thermal treatment times (310° F.) 
               
             
          
           
               
                   
                 Sheet A 
                 Sheet B (new) 
                 Sheet C (new) 
                 Sheet D (new) 
                 Sheet E (new) 
               
               
                   
                 (T6-style) 
                 85% CW 
                 75% CW 
                 50% CW 
                 25% CW 
               
               
                   
                 (ksi) 
                 (ksi) 
                 (ksi) 
                 (ksi) 
                 (ksi) 
               
             
          
           
               
                 Time(hr) 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
                 TYS 
                 UTS 
               
               
                   
               
             
          
           
               
                 0 
                 49 
                 71.8 
                 88.1 
                 99.4 
                 80.5 
                 95.6 
                 73.7 
                 87.6 
                 66.1 
                 81.9 
               
               
                 0.5 
                 68 
                 78.5 
                 88.5 
                 93.8 
                 83.9 
                 89.4 
                 74.3 
                 81.6 
                 68.4 
                 77.7 
               
               
                 2 
                 75 
                 81.5 
                 84.7 
                 90.8 
                 82.3 
                 87.7 
                 75.4 
                 82.6 
                 73.5 
                 80.6 
               
               
                 4 
                 77.5 
                 82.3 
                 82.9 
                 87.8 
                 80.9 
                 86.0 
                 75.7 
                 81.7 
                 72.5 
                 80.1 
               
               
                 8 
                 78.0 
                 82.0 
                 78.9 
                 84.0 
                 76.4 
                 82.5 
                 74.0 
                 79.8 
                 72.9 
                 79.3 
               
               
                 16 
                 76.8 
                 80.4 
                 72.7 
                 79.1 
                 70.9 
                 77.9 
                 69.3 
                 76.7 
                 69.4 
                 77.0 
               
               
                   
               
             
          
         
       
     
     As illustrated in Tables 4-6, above, and  FIGS. 14-16 , Sheets B-E made by the new process realize increases in strength over Sheet A. Indeed, new Sheet B made by the new process realizes a peak tensile yield strength of 91.3 ksi with only about 4 hours of thermal treatment at 250° F. The conventionally produced Sheet A achieves a peak tensile yield strength of about 78-79 ksi, as shown by the data of Tables 5-6. In other words, new Sheet B achieves about a 15.6% increase in tensile yield strength over the conventionally prepared material. It also takes over 36 hours for conventional Sheet A to achieve its peak strength at 250° F. In other words, the new Sheet B material achieves its peak strength about 89% faster than the conventional Sheet A material ((1−4/36)*100%=89%). Stated differently, new Sheet B achieves about a 15.6% increase in peak strength over conventional Sheet A and in less than about 1/10 th  of the time required to peak age the conventional Sheet A material. 
     Given these strength increases, a significant drop in ductility would be expected for Sheets B-E. However, as shown in Table 7, below, good elongation values are measured. All elongation values are in percent. Similar elongation values are measured for the samples thermally treated at 280° F. and 310° F. 
                                                                         TABLE 7                   Elongation of a 1 st  7xxx aluminum alloy at various thermal treatment       times (250° F.)                        Sheet C   Sheet D   Sheet E       Time   Sheet A   Sheet B (new)   (new)   (new)   (new)       (hr)   (T6-style)   85% CW   75% CW   50% CW   25% CW                    0   24   10   11   12   12       0.5   21   10   11   14   13       4   19   10   11   14   13       12   16   10   11   12   13       24   15   10   11   10   13       36   14   10   11   10   10                    
Sheets B-E also realize good electrical conductivity as shown in Tables 8-10, below. All electrical conductivity values are in percent IACS (International Annealed Copper Standard).
 
     
       
         
               
             
               
               
               
               
               
               
             
               
               
               
               
               
               
             
           
               
                 TABLE 8 
               
             
             
               
                   
               
               
                 Electrical conductivity of a 1 st  7xxx aluminum alloy at various 
               
               
                 thermal treatment times (250° F.) 
               
             
          
           
               
                   
                   
                   
                 Sheet C 
                 Sheet D 
                 Sheet E 
               
               
                 Time 
                 Sheet A 
                 Sheet B (new) 
                 (new) 
                 (new) 
                 (new) 
               
               
                 (hr) 
                 (T6-style) 
                 85% CW 
                 75% CW 
                 50% CW 
                 25% CW 
               
               
                   
               
             
          
           
               
                 0 
                 29 
                 29.3 
                 29.1 
                 29.1 
                 29 
               
               
                 0.5 
                 30.7 
                 30.7 
                 30.6 
                 30.3 
                 30.2 
               
               
                 4 
                 32.4 
                 32.8 
                 32.5 
                 32.3 
                 31.8 
               
               
                 12 
                 33.8 
                 34.4 
                 34.3 
                 33.6 
                 33.2 
               
               
                 24 
                 34.7 
                 35.6 
                 35.4 
                 34.8 
                 34.1 
               
               
                 36 
                 35.1 
                 36.4 
                 36.2 
                 35.3 
                 34.8 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
             
               
               
               
               
               
               
             
           
               
                 TABLE 9 
               
             
             
               
                   
               
               
                 Electrical conductivity of a 1 st  7xxx aluminum alloy at various 
               
               
                 thermal treatment times (280° F.) 
               
             
          
           
               
                   
                   
                   
                 Sheet C 
                 Sheet D 
                 Sheet E 
               
               
                 Time 
                 Sheet A 
                 Sheet B (new) 
                 (new) 
                 (new) 
                 (new) 
               
               
                 (hr) 
                 (T6-style) 
                 85% CW 
                 75% CW 
                 50% CW 
                 25% CW 
               
               
                   
               
             
          
           
               
                 0.5 
                 31.9 
                 32 
                 31.9 
                 31.5 
                 31.4 
               
               
                 2 
                 33.4 
                 34 
                 33.9 
                 33.4 
                 33 
               
               
                 8 
                 35.7 
                 37.2 
                 37 
                 36.2 
                 35.7 
               
               
                 16 
                 36.6 
                 39.3 
                 38.8 
                 38.1 
                 37.2 
               
               
                 24 
                 37.7 
                 41.1 
                 40.9 
                 40.2 
                 39.1 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
             
               
               
               
               
               
               
             
           
               
                 TABLE 10 
               
             
             
               
                   
               
               
                 Electrical conductivity of a 1 st  7xxx aluminum alloy at various 
               
               
                 thermal treatment times (310° F.) 
               
             
          
           
               
                   
                   
                   
                 Sheet C 
                 Sheet D 
                 Sheet E 
               
               
                 Time 
                 Sheet A 
                 Sheet B (new) 
                 (new) 
                 (new) 
                 (new) 
               
               
                 (hr) 
                 (T6-style) 
                 85% CW 
                 75% CW 
                 50% CW 
                 25% CW 
               
               
                   
               
             
          
           
               
                 0.5 
                 33.1 
                 33.6 
                 34.2 
                 34.4 
                 33.9 
               
               
                 2 
                 36.3 
                 37.2 
                 38 
                 38.3 
                 36.2 
               
               
                 4 
                 38.8 
                 39.5 
                 40.4 
                 40.8 
                 37.5 
               
               
                 8 
                 41.1 
                 41.9 
                 42.6 
                 42.9 
                 38.3 
               
               
                 16 
                 42.6 
                 43.3 
                 44 
                 44.6 
                 39.7 
               
               
                   
               
             
          
         
       
     
     Example 2 
     Additional mechanical properties of this 1 St  7xxx aluminum alloy are tested. Specifically, the longitudinal (L) and long transverse (LT) strength, elongation, and fracture toughness properties of this 1 st  7xxx aluminum alloy are tested, the results of which are provided in Tables 11-12 below. These results indicate that similar strength and elongation properties may be realized by 7xxx aluminum alloy bodies in the L and LT directions. 
     
       
         
               
             
               
               
               
               
               
               
               
             
               
               
               
               
               
               
               
             
           
               
                 TABLE 11 
               
             
             
               
                   
               
               
                 Strength and Elongation Properties of the 1 st  7xxx aluminum alloy 
               
             
          
           
               
                   
                 CW 
                 Temp 
                 Time 
                 TYS 
                 UTS 
                 Elong. 
               
               
                 Direction 
                 (%) 
                 (F.) 
                 (hr) 
                 (ksi) 
                 (ksi) 
                 (%) 
               
               
                   
               
             
          
           
               
                 L 
                 25 
                 250 
                 36 
                 80 
                 86.2 
                 10 
               
               
                 L 
                 75 
                 250 
                 4 
                 88.55 
                 93.4 
                 8 
               
               
                 L 
                 75 
                 250 
                 24 
                 85.5 
                 90.55 
                 8 
               
               
                 L 
                 85 
                 250 
                 4 
                 91.05 
                 95.95 
                 5.5 
               
               
                 L 
                 85 
                 250 
                 24 
                 87.65 
                 92.45 
                 6 
               
               
                 L 
                 N/A - T6 
                 280 
                 24 
                 77.9 
                 82.3 
                 10 
               
               
                   
                 Control 
                   
                   
                   
                   
                   
               
               
                 L 
                 N/A - T6 
                 310 
                 8 
                 77.8 
                 80.65 
                 10 
               
               
                   
                 Control 
                   
                   
                   
                   
                   
               
               
                 LT 
                 25 
                 250 
                 36 
                 79.15 
                 85.95 
                 10 
               
               
                 LT 
                 75 
                 250 
                 4 
                 86.5 
                 92.9 
                 10 
               
               
                 LT 
                 75 
                 250 
                 24 
                 86.45 
                 91.5 
                 10 
               
               
                 LT 
                 85 
                 250 
                 4 
                 91.7 
                 97.75 
                 9 
               
               
                 LT 
                 85 
                 250 
                 24 
                 89.9 
                 94.75 
                 9.5 
               
               
                 LT 
                 N/A - T6 
                 280 
                 24 
                 77.65 
                 83.25 
                 9 
               
               
                   
                 Control 
                   
                   
                   
                   
                   
               
               
                 LT 
                 N/A - T6 
                 310 
                 8 
                 77.4 
                 81.9 
                 9 
               
               
                   
                 Control 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
               
             
           
               
                 TABLE 12 
               
               
                   
               
               
                 Toughness Properties of the 1 st  7xxx aluminum alloy 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                   
                 CW 
                 Temp 
                 Time 
                 K Q  L-T 
                 K app  L-T 
                 K R25  L-T 
               
               
                 Direction 
                 (%) 
                 (F.) 
                 (hr) 
                 (ksi√in) 
                 (ksi√in) 
                 (ksi√in) 
               
               
                   
               
               
                 L 
                 25 
                 250 
                 36 
                 40.3 
                 N/A 
                 87.1 
               
               
                 L 
                 75 
                 250 
                 4 
                 50.3 
                 61.1 
                 57.7 
               
               
                 L 
                 75 
                 250 
                 24 
                 44.7 
                 71.8 
                 64.8 
               
               
                 L 
                 85 
                 250 
                 4 
                 49.6 
                 54.2 
                 54.3 
               
               
                 L 
                 85 
                 250 
                 24 
                 44.2 
                 58.3 
                 59.6 
               
               
                 L 
                 N/A - T6 
                 280 
                 24 
                 49.6 
                 88.2 
                 91.1 
               
               
                   
                 Control 
                   
                   
                   
                   
                   
               
               
                 L 
                 N/A - T6 
                 310 
                 8 
                 43.5 
                 87.1 
                 86.7 
               
               
                   
                 Control 
               
               
                   
               
               
                   
                 CW 
                 Temp 
                 Time 
                 K Q  T-L 
                 K app  T-L 
                 K R25  T-L 
               
               
                 Direction 
                 (%) 
                 (F.) 
                 (hr) 
                 (ksi√in) 
                 (ksi√in) 
                 (ksi√in) 
               
               
                   
               
               
                 LT 
                 25 
                 250 
                 36 
                 48.3 
                 N/A 
                 78.2 
               
               
                 LT 
                 75 
                 250 
                 4 
                 40.4 
                 N/A 
                 69.0 
               
               
                 LT 
                 75 
                 250 
                 24 
                 40.7 
                 N/A 
                 69.3 
               
               
                 LT 
                 85 
                 250 
                 4 
                 39.2 
                 N/A 
                 77.4 
               
               
                 LT 
                 85 
                 250 
                 24 
                 44.4 
                 N/A 
                 61.4 
               
               
                 LT 
                 N/A - T6 
                 280 
                 24 
                 49.9 
                 N/A 
                 90.1 
               
               
                   
                 Control 
                   
                   
                   
                   
                   
               
               
                 LT 
                 N/A - T6 
                 310 
                 8 
                 48.7 
                 N/A 
                 84.5 
               
               
                   
                 Control 
               
               
                   
               
             
          
         
       
     
     The fracture toughness tests were conducted in accordance with ASTM test standards ASTM E561 and ASTM B646 (for K app  and K R25 ), and E399 and B645 (K IC /K Q ). A middle crack fracture specimen (M(T)) was used for the K app  measurement. The specimen width (W) was 6.3 inches, thickness (B) was 0.08 inch and the initial crack length (2a 0 ) was 1.573 inches, i.e. 2 a o /W=0.25. A compact tension fracture specimen (C(T)) was used for K R25  and K Q  measurements. The specimen width (W) was 2.5 inches and thickness (B) was 0.07 inch, with a nominal initial crack length (a 0 ) of 1.25 and (a 0 )/W=0.50. 
     Those skilled in the art will appreciate that the numerical values of K Q , K app  and K R25  typically increase as the test specimen width increases. K Q , K app  and K R25  are also influenced by specimen thickness, initial crack length and test coupon geometry. Thus, K Q , K app  and K R25  values usually can be reliably compared only from test specimens of equivalent geometry, width, thickness and initial crack length. 
     The 7xxx aluminum alloy body realizes good toughness. Despite the significant increase in strength over the control, the new 7xxx aluminum alloy bodies realize the same strength-toughness trend as the control bodies. This is illustrated in  FIGS. 17-19 . Thus, the new 7xxx aluminum alloy bodies achieve at least equivalent toughness, and generally a better strength-toughness trend as compared to the conventionally processed aluminum alloy bodies. 
     The exfoliation resistance of some of the 1 st  7xxx aluminum alloy sheets is also measured, the results of which are provided in Table 13, below. Test specimens were taken at one-tenth thickness (T/10). The 7xxx aluminum alloy sheets achieve good exfoliation resistance, with most samples achieving ratings of EB or EA. 
     
       
         
               
             
               
               
               
               
             
               
               
               
               
               
             
           
               
                 TABLE 13 
               
             
             
               
                   
               
               
                 EXCO Properties of the 1 st  7xxx aluminum alloy 
               
             
          
           
               
                   
                 Thermal Treatment 
                 EXCO Results 
                   
               
             
          
           
               
                   
                 Sample 
                 Time and Temperature 
                 24 hours 
                 48 hours 
               
               
                   
                   
               
               
                   
                 25% CW 
                 36 HR, 250 F. 
                 EB 
                 EB 
               
               
                   
                 75% CW 
                  4 HR, 250 F. 
                 EA 
                 EB 
               
               
                   
                 75% CW 
                 24 HR, 250 F. 
                 EA 
                 EB 
               
               
                   
                 85% CW 
                  4 HR, 250 F. 
                 EA 
                 EB 
               
               
                   
                 85% CW 
                 24 HR, 250 F. 
                 EB 
                 EC 
               
               
                   
                 Control 
                 24 HR, 280 F. 
                 EA 
                 EB 
               
               
                   
                 Control 
                  8 HR, 310 F. 
                 EA 
                 EA 
               
               
                   
                   
               
             
          
         
       
     
     The 7xxx aluminum alloy bodies are also tested for grain structure as per the OIM procedure, described above. The results are provided in Table 14, below. 
     
       
         
               
             
               
               
               
               
             
           
               
                 TABLE 14 
               
             
             
               
                   
               
               
                 Microstructure (OIM) Properties of the 1 st  7xxx aluminum alloy 
               
             
          
           
               
                   
                 Measurement 
                 First Type Grains 
                 Percent 
               
               
                 Sample 
                 Location 
                 per OIM (vol. fraction) 
                 Unrecrystallized 
               
               
                   
               
               
                 Control 
                 T/4 to surface 
                 0.96 
                  4% 
               
               
                 25% CW 
                 T/4 to surface 
                 0.16 
                 84% 
               
               
                 50% CW 
                 T/4 to surface 
                 0.19 
                 81% 
               
               
                 75% CW 
                 T/4 to surface 
                 0.34 
                 66% 
               
               
                 85% CW 
                 T/4 to surface 
                 0.27 
                 73% 
               
               
                   
               
             
          
         
       
     
     The new 7xxx aluminum alloy bodies have a predominately unrecrystallized microstructure, having a volume fraction of not greater than 0.34 first type grains (i.e., 66% unrecrystallized) in all instances. Conversely, the control body is nearly fully recrystallized having a volume fraction of 0.96 first type grains (i.e., 4% unrecrystallized). 
     The R-values of the 7xxx aluminum alloy bodies are also tested as per the R-value generation procedure, described above. The results are illustrated in  FIG. 10 , described above. The new 7xxx aluminum alloy bodies have high normalized R-values, achieving a peak (maximum) normalized R-value at an orientation angle of 45-50°. These high R-values are indicative of the unique texture, and thus microstructure, of the new 7xxx aluminum alloy bodies described herein. The new 7xxx aluminum alloy bodies realize about 450% to 600% higher maximum R-values as compared to the R-value of the control body (for the purpose of measuring R-values, the control is in the T4 temper, not the T6 temper). 
     Example 3 
     Two additional 7xxx aluminum alloy bodies are prepared as per Example 1. Both are known Russian alloys. One alloy is a copper-free 7xxx aluminum alloy (alloy 1980), and the other alloy is a low copper 7xxx aluminum alloy (alloy 1953). The compositions of these aluminum alloys are provided in Tables 16-17, below. The alloys contain the listed ingredients, the balance being aluminum and not greater than 0.05 wt. % each of other elements, and not greater than 0.15 wt. % in total of these other elements. 
     
       
         
               
             
               
               
               
               
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 16 
               
             
             
               
                   
               
               
                 Composition of a 2 nd  7xxx alloy (all values in weight percent) 
               
             
          
           
               
                 1953 
                 Si 
                 Fe 
                 Cu 
                 Mg 
                 Zn 
                 Ti 
                 Zr 
                 Mn 
                 Cr 
               
               
                   
               
             
          
           
               
                   
                 0.08 
                 0.23 
                 0.56 
                 2.65 
                 5.87 
                 0.04 
                 0.10 
                 0.21 
                 0.20 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
               
               
               
               
             
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 17 
               
             
             
               
                   
               
               
                 Composition of a 3 rd  7xxx alloy (all values in weight percent) 
               
             
          
           
               
                 1980 
                 Si 
                 Fe 
                 Cu 
                 Mg 
                 Zn 
                 Ti 
                 Zr 
                 Mn 
                 Cr 
               
               
                   
               
             
          
           
               
                   
                 0.1 
                 0.15 
                 0.04 
                 2.3 
                 4.4 
                 0.03 
                 0.14 
                 0.4 
                 0.15 
               
               
                   
               
             
          
         
       
     
     The results of Example 3 illustrate that the cold working and thermal treatment steps must be appropriately accomplished to achieve improved properties (e.g., strength). As shown in  FIGS. 20-21  and  24 - 25 , alloys that are thermally treated for an insufficient period of time may not realize the improved properties, as illustrated by the reduction in strength as compared to the as-cold worked condition. As shown in  FIGS. 20-21 , alloys that are thermally treated for an excessive period may also not realize the improved properties, as illustrated by the reduction in strength as compared to the as-cold worked condition. 
     While various embodiments of the present disclosure have been described in detail, it is apparent that modifications and adaptations of those embodiments will occur to those skilled in the art. However, it is to be expressly understood that such modifications and adaptations are within the spirit and scope of the present disclosure.