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MIL-HDBK-5H1 December 1998 — Figures 3.7.4.1.1(a) and (b) permit calculationof residual tensile strengths for complex thermal exposure conditions. They are based upon the rateparameter T(C + log t), in which T is exposure temperature in degrees Rankine, t is exposure time in hoursand C is a constant evaluated for each material. These curves have been verified for use only within theranges of temperatures and exposure times covered in the figures. The following example illustrates theiruse.1 hour.Sample problem: Find F tu at 250F following a complex exposure of 300F, 8 hours plus 350F,1. Reduce given complex exposure by converting 350F exposure to equivalent exposure time at300F.*a. On the 350F single exposure temperature line find 350F, 1 hour.b. From this point move vertically to the 300F exposure temperature line and then readright, 12 hours exposure.c. Total equivalent exposure time at 300F is therefore 8 hours + 12 hours or 20 hours.2. Find F tu at 250F following 300F, 20 hours exposure:a. On the 300F exposure temperature line find 300F, 20 hours.b. From this point move vertically to the 250F test temperature curve and then read left,76 percent F tu .Solution: F tu is 76 percent of the original room temperature F tu . F ty is determined in like manner.F cy can be closely estimated by using the percent reduction factor determined for F ty . For specific data, seeReference 3.7.4.1.Stressed Thermal Exposure — Stress applied during sample and complex thermal exposure of 7075-T6 can have additional effect in reducing material strength. However, the effect becomes significant onlywhen exposure strains exceed 0.2 percent. For specific data, see Reference 3.7.4.1.Figures 3.7.4.1.1(c) through 3.7.4.1.5(b) present elevated temperature curves for variousmechanical properties. Figures 3.7.4.1.6(a) through (m) present tensile and compressive stress-strainand tangent-modulus curves at several temperatures. Figures 3.7.4.1.6(n) through (q) are full-range stressstraincurves for various products. Figures 3.7.4.1.8(a) through (h) provide room-temperature fatigue curvesfor T6 temper products. Fatigue-crack propagation data for sheet are presented in Figure 3.7.4.1.9.Graphical displays of the residual strength behavior of center-cracked tension panels are presented in Figure3.7.4.1.10(a) through (h). — Figures 3.7.4.2.6(a) through (d)present stress-strain and tangent-modulus curves for various products and tempers. Figures 3.7.4.2.6(e) and(f) are full-range stress-strain curves at room temperature for extrusion. Fatigue-crack-propagation data forplate are presented in Figures 3.7.4.2.9(a) through (c). Graphical displays of the residual strength behaviorof center-cracked tension panels are presented in Figures 3.7.4.2.10(a) and (b)._______________________* Choice of reference temperature is optional as long as it permits computation within the bounds of the figures.3-345
3-346 ! ! " Specification ........AMS 4045 and AMS-QQ-A-250/12Form .............. Sheet PlateTemper ............ T6 and T62 a T651Thickness, in. .......0.008-0.0110.012-0.0390.040-0.1250.126-0.2490.250-0.499Basis .............. S A B A B A B A B A B A B A B A B A B A BMechanical Properties:F tu , ksi:L ..............LT .............ST ............F ty , ksi:L ..............LT .............ST .............F cy , ksi:L ..............LT .............ST .............F su , ksi ...........F c bru , ksi:(e/D = 1.5) .......(e/D = 2.0) .......F c bry , ksi:(e/D = 1.5) .......(e/D = 2.0) .......e, percent (S-basis):LT .............E, 10 3 ksi .........E c , 10 3 ksi .........G, 10 3 ksi .........µ ................Physical Properties:, lb/in. 3 ..........C, K, and ...........74......63...........................57676...6967...6871...4611815210011777878...7270...7174...47121156105122...7878...7068...6972...47121156102119810.310.53.90.338080...7270...7174...48124160105122...7878...7169...7073...4712115610312188080...7371...7275...48124160106124...7778...6967...6771...431171459711497980...7169...6973...44120148100118...0.500-1.0007778...7068...6872...4411714510011777980...7270...7074...45120148103120...1.001-2.0007677...6967...6671...4411614310011767879...7169...6873...45119147103120...0.101See Figure 3.7.4.0a <strong>Design</strong> allowables were based upon data obtained from testing T6 temper sheet and from testing samples of sheet, supplied in the O or F temper, which were heat treated todemonstrate response to heat treatment by suppliers. Properties obtained by the user may be lower than those listed if the material has been formed or otherwise cold worked,particularly in the annealed temper, prior to solution heat treatment.b Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, asindicated in Table 3.1.2.3.1(a).c Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.757670 b666459 b62686744114141981132.001-2.5005777871 b686661 b64707045117145101117...10.310.63.90.33717266 b636156 b58656442108134941092.501-3.0005737468 b656358 b6067664311113797112...707165 b605854 b55616142107132891043.001-3.5005727367 b626055 b5764634311013593108...3.501-4.000666761 b565450 b5157573910112484983686963 b585652 b5259594110412887103...MIL-HDBK-5H1 December 1998
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