Bruhn - Analysis And Design Of Flight Vehicles Structures Episode 3 Part 1 pptx

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B2.4 MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES 17-7 PH STAINLESS STEEL Table B2.3 Design Mechanical and Physical Properties of 17-7 PH Stainless Steel AlÚoy 17-1 PH Form Sheet, strip, and plate(+) Bars and Forgings(*) Condition TH 1050 RH 960 ; TH 1050! RH 950 t 1 Thickness or diameter, in | 0.005 to 0.005 to ¡ 0.1875 to 6 and under 9.500 0.1874 | 0.500 : ` 8 | i S( ! | ! h 180 210 | 200 170 | 185 150 190 | 180 140 | 150 158 200 ; 189 147 158 117 136 | 130 111 | 120 297 346 | 330 280 305 360 420 | 400 340 370 225 285 : 270 210 | 225 247 313; 297 231 | 247 See table 2.7.2.1(b) 6 | 6 E, 108 psi 29.0 E., 108 psi 30.0 G, 108 psi 11.0 Physical properties: «, lb/in2 0.276 €, Btu/b)(FE) 0.11 (2 K, Btu/((hr) (ft?) (F)/ft] 9.75 (at 300° F) œ, 10^*in./in./F 6.3 (70° to 600° F) for TH 1050 6.3 (70° to 600° F) for RH 950

* Test direction longitudinal for widths less than 9 in.; transverse for short transverse (thickness) direction

widths 9 in, and over » Test direction longitudinal; these properties not applicable to the 4 Calculated value « Vendors gvaranteed minimums for Fis, Fre, and ¢ Strength at tempercture Expomwre up to 1/2 be Per Cont Fy, ot Room Temperature Tempercture, F Temperature, F

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2.5 17-7 PH STAINLSSS S?EEL (Cont.) 100, 5 i be ie Š a i° ® soi i° 5 «6i về Vẽ ‡” 4 ` 2 9 ° 0 Temoerorue, F Temoeroture, F

Fig B2.15 Effect of temperature on the compressive Fig B2.18 Effect of temperature on the ultimate

yield strength (Fey) of 17-7 PH (TH1050) stainless steel bearing strength (Fpry) of 17-7 PH (TH1050) stainless steel 199, H § } i i 3 i° 8 s@i é v 3 i* ề š Temperature, F Temperature, F

Fig B2.16 Effect of temperature on the ultimate Fig B2.19 Effect of temperature on the bearing yield

shear strength (Fsy) of 17-7 PH (TH1050) stainless steel atrength (Fpry) of 17-7 PH (T'H1050) stainless steel 190) i L1 j « 3 a 3 i 2 o Coy Temoerature, F

Fig B2.20 Effect of temperature on the tensile and

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B2 6 Pet PH STAINLESS ST L Table B2.4 Design Mechanical and Physical Properties of 17-4 PH Stainless Steel Alloy - 174 PH Plate | Bars and forgings (*) €Condition - H 900 H 900 Thickness or diameter, in | 8 and under Basis ị §(œ) § Mechanical properties: Pies ksi 190 190 Fi, ksi 170 170 i 178 178 128 128 318 313 380 380 fects 255 255 (e/D=2.0) - 280 280 e, percent: Ta 2in 10 vee In4ÐD 10 EB, 108 psi 29.0 E,, 104 psi 30.0 G, 10¢ psi 11.0 Physical properties: w, Ibfns C, Btu/(B)(F) K, Btu/((hr) (ft?) Œ/RJ ø, 10-*in./in./F 0.282 0.11 (32° tọ 212° F) 10.3 (at 300° F); 11.2 (at 500° F); 13.1 (at 900° F) 6.0 (70° to 200° F); 6.1 (70° ta 400° F); 6.5 (70° to 900° F) « Vendors guaranteed minimums for Fiy, Fr, and ¢

» Test direction longitudinal; these properties not applicable to the short transverse (thickness) direction Fret Cart Fy, Room Temparotus Teresa, F

Fig 82.21 &ffect of temperature on

the ultimate tensile strength (Ftu) of 17-4 PH (H900) stainless steel Pee Cart Fy, 1 Roam Wrpwctuce

Fig B2.22 Effect of temperature on the tensile yield strength (Fty} ot 17-4 PH (H900} stainless steel MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES Pe Cant Fey of Tenpavaturs 8 2 Temeeeanea.Ƒ

Fig B2.23 Effect of temperature an

the compressive yield strength (Fey) of 17-4 PH (H900) stainless steel 100, = Exaesure se lo Pe Cant 64, 0 Roam Terpmotare Temoerarure, F

Fig B2.24 Effect of temperature on

the ultimate shear strength (F5u) of 17-4 PH (H900) stainless steel Per Cont Figg a fom Tampeglue g 3 SOG XD 800 G6 Temoergrune, F Too 1300 600 Fig 82.25 Effect of temperature on

the ultimate bearing strength (Fpry) of 17-4 PH (H900) stainless steel Senge at mnenainei Expocure up ta = or Fer Gees Fy, gi Xengeroture Tamesrorure F

the bearing yield strength (Fpry? ot 17-4 PH (H900) stainless steel Par Coot & ond Eg of Terosratura 0 Tempera

Fig B2.27 Effect of temperature on the tensile and compressive modulus (E and E,) of 17-4 PH (H900)

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2.7 50 STAINLESS STEEL Table B2.5 Design Mechanical and Physical Properties of AM-350 Stainless Steet 3 Alloy co AM-350 Ỉ T i Form Sheet and strips Sheet and strips i a Candition i DA SCT ẻ Thickness, in, ! 0487 and under ; 0.187 and under 3 Basis 8 S

| Fig 82.30 Effect of temperature on

the compressive yield strength (Foy) of

E, 10° pst ì ao 0 Fig B2.31 Effect of temperature on

E., 108 p: ị 3 the tensile and compressive modulus G, 10 psi 11.0 Physical properties: w, lb/ins : €, Btu/(b)Œ) K, Btus{(hr) it?) (F).ft] a, 10 injin/F 9.282 0.12 (32° to 212° F) 8.4 (at 100° F); 11.7 (at 800° F) 6.3 (70° to 212° F); 7.2 (70° to 932° F) « Test direction longitudinal for widths less than 9 in.; transverse for widths 9 in and over Pe Cant đụ, g9 Temparature Tameeroture,F

the ultimate tensile strength (Ftu) of

AM-350 stainless steel (double-aged)

Tamewrorue,E

the tensile yield strength (Fty} of

AM-350 stainless steel (double-aged)

(E and Eg) of AM-350 stainless steel (doubte-aged) Pet Cant Fi, a Tenperolese ok a mẽ SB Teroermture,f 1900 1600

tig B2.32 Effect of temperature on the ultimate tensile strength (Ftu} of

AM-350 stainless steel (SCT) Par Cont #, at Huan Tonpmralure

the tensile yield strength (Fry) of

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MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES AM-350 STAINLESS STEEL (Cont.) 8 Moadus of | temperature 8 Per Cent € ond E, ot Room Temperature Temperatura, F

Fig B2.34 Effect of temperature on the tensile and compressive modulus (E and Ec) of AM-350 stainless steel (SCT) Per Caat Fy, at Room Terparoture Tamperorure, F

Fig B2.35 Effect of temperature on the bearing yield strength (Fyry) of AM~350 stainless steel (SCT) ặ 3 Pes Cont Fax ot Room Temperature 8 ° ‘af Temoartvg tp to l2 hr Per Cent Fey Of Roo Temperature ‘00-800 Temperature, F

Fig B2.36 Effect of temperature on the compressive

yield strength (Fey) of AM-350 stainless steel (SCT) Per Cant Fin, Ot Room Temperature 1300 Temperature, F

Fig B2.37 Effect of temperature on the ultimate

bearing strength (Fpry) of AM-350 staintess steel

(sCT)

Temperatura, F

Fig B2.38 Effect of temperature on the ultimate shear strength (Fey) of AM-350 stainless steel

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2.9 AISI 301 STAINLESS STEEL

Table B2.6 Design Mechanical and Physicat Properties of AISI 301 Stainless Steel Alloy AI8I 801 « Torm Plate *, sheet, and strip - 7 Condition Annealed | 34 hard 74 hard % hard | Full bard Basis Đ Đ 8 Đ Ss Mechanical properties: đ Pu ki: L 75 125 150 175 185 15 125 150 175 185 30 5 110 136 140 30 15 110 136 140 35 43 58 ĩ 85 35 30 118 160 179 40 67.5 80 95 100 Fore, ksi: (e/D=1.5) (efD=2.0) Foray ksi: (e/D= 1.5) (e/D=2.0) #, percent E, 10° psi: T #„ 10% p ù 28.0 28.0 26.0 26.0 26.0 T 28.0 27.9 27.0 27.0 27.0 G, 10° psi 12.5 12.0 11.5 11.0 11.0 Physical properties: a, Ib/ins 0.286 C, Btu/(b)Œ) 0.108 (at 32° F) K, Btu/[(br) (ft?) (F)/ft} 7.74 (at 32° F) œ, l0~t+Íin/in./E i 9.2 (70° to 200° F) «+ Properties for annealed condition also applicable to annesied AISI 302, 303, 30%, 321, and 347 ™ * Only anneaied condition applicable to plate + See table 2.8.1.1(b)

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B2.10_ MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES a TP SHeAGEA mỉ lamoeretuie Pe Gard Fig si tengealue & Temoeonre,F

the ultimate tensile strength (Fty) of AISI 301 (half-hard) stainless steel Pe Cook Fry at Yenpeolee $

Fig B2.40 Effect of temperature on the tensile yield strength (Fty) of AISI 301 (half-hard) stainlesa steel & Pes Coot Fy a Teeemlose 3

the compressive yield strength (Foy)

of AISI 301 (half-hard) stainless steel Per Cart Fay Baện Tengeulor 3

Fig B2.42 Effect of temperature on the ultimate shear strength (Fsu) of

AISI 301 (half-hard) stainless steei Per Cent Fury at Temper Temoseere,

Fig B2.43 Effect of temperature on the ultimate bearing strength (Fbru) of AISI 301 (halt-hard) stainless steel

AISI SOL STAINLESS STEEL (Cont.} Per Cord Fey 0 Targaatunn

Fig 52.44 Effect of temperature on

the bearing yield strength (Fpry} of

AISI 301 (half-hard)} stainless steel & 8 mm S6 160 090 ó0 Teroewarure, 7 = Pes Can € und Eg oF Terpertture s

the tensile and compressive modulus (E and Eg) of AISI 301 (haif-hard) stainless steel EE Strenqim of tamperatuce 4 Exposure uo tof & 8 Pw Cant Gy of Yengsretea a

Fig B2.46 Effect of temperature on the ultimate tensile strength (Fry) of

AISI 301 (full-hard) stainiess steel Sirenqrn at weed Eeponee up 19} tr Pee Cent Fục gì Bườn Tenpeotire Tameergtee, F

the tensile yield strength (Fry) of AIST 301 (full~hard) stainless steel of momonue Eeonwe we 0 pr fe Cart Fe, at Tempueaturs Temoeranae, F

Fig, B2.48 Effect of temperature on the compressive yield strength (Fey)

of AIST 301 (full-hard) stainless stéel vat Rodan Tenbkdlurr Pee Co 6,

Fig, B2.49 Effect of temperature on

the ultimate shear strength (Fsy) of

AISI 301 (full-hard) stainless steel Pee Gant Fy 8 Room Temperature ‘0 aon" 40d “ĐO ĐO S00 Tamperonae, "20040 —E00 Fig B2.30 Effect of temperature on

the ultimate bearing strength (Fpru)

of AISI 301 (full-hard) stainless steel 109, Sirengin a lemeeravare Exoenure us toy a Pee Cont Fory at Ratan Kengwulone Temoerorure, F

the bearing yieid strength (Fyry) of AISI 301 (full-hard) stainiess steel a Pe Cont tad Ee ot Temperate Tarooratur,

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2.11

2014 ALUMINUM ALLOYS (SHEST 2 PLATS, EXTRUSIONS, FCRGINGS )

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B2,12 MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES

2014 ALUMINUM ALLOYS (SHEET & PLATE, EXTRUSIONS, FORGINGS) (Cont.}

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES

B2, 13

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B2.14 MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES

2014 ALUMINUM ALLOYS (SHEET & PLATE, EXTRUSIONS, FCRGINGS) (Cont.) Table B2.10 Design Mechanical and Physical Properties of 2014 Aluminum Alloy (Forgings}

Alloy 2014

Die Hand forgings Hand forg-ngs

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2.15

EFFECT OF TEMPERATURE ON 2014 ALUMINUM ALLOYS ŸŠTR*EKGTM AT TCMPCSATURC Exposvec ur ro 10 000 wa 8 8 § PER CENT Fụụ AT ROOS TEMPERATURE * ễ 20 100 TEMPERATURE, °F

Fig B2.53 Effect of temperature on the ultimate strength (Fty) of 2014-T6 aluminum alloy (bare and clad sheet 0 020-0, 039 in thick; bare and clad plate 1 501-4 000 in thick; rolled bar, rod and shapes; hand and die forgings; extruded bar, rod and shapes 0 125-0 749 in, thick with cross-sectional area = 25 sq in.) Tho 120 $TR€RGTH AT TEMPCRATUEC TC FEPSsuAC 0P 76 1 000 we AT ROOM TEMPCRATURE 8# „ ho PER CENT F ¬ 1 300) TEMPERATURE, *F

Fig, 82.54 Effect of temperature on the tensile yield strength (Fty) of 2014-T6 aluminum alloy (bare and clad plate

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Bl 16

MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES EFFECT OF TEMPERATURE ON 2014 ALUMINUM ALLOYS (Cont.} Per Cent Fay of Room lengese

Fig, 52.55 Effect of temperature on the compressive yield strength (Fey)

of 2014-T6 aluminum alloy {all

products except thick extrusions) Pe Cont Fy, a Room Tercgarenes 8

the ultimate shear strength (Fgy) of

2014-T6 aluminum alloy (all products

except thick extrusions Pree Cant Fy, ot lemperotore Ro 60 s0 59 60 SEO mm Tempensnee,

the ultimate bearing strength (Fpru) of 2014-T6 aluminum alioy (ail products except thick extrusions)

the bearing yield strength (Fpry) of 2014-T6 aluminum alloy (all products except thick extrusions) Pee Cart £ and Ey of Room tanpessse 2 “wa A00 cám 9 288 7 508 600 190 000 Tenoworee

the tensile and compressive modulus {EB and Eg) of 2014 and 2017 aluminum alloys,

2024 ALUMINUM ALLOY (BARE SHEET & PLATE, EXTRUSIONS, BAR, ROD & WIRE)

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2 17

2024 ALUMINUM ALLOY (BARE SHEET & PLATE, EXTRUSIONS, BAR, ROD & WIRE) (Cont

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MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES 2024 ALUMINUM ALLOY (BARE SHEET & PLATS, SXTRUSIONS, BAR, ROD & WIRE) (Cont.)

Table B2.13 Design Mechanical and Physical Properties of 2024 Aluminum Alloy (Bar, Rod, and Wire);

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Table B2 14 Design Mechanical and Physical Properties of Clad 2024 Aluminum Alloy (Sheet, Plate, and Coiled Sheet) Alloy Chau 2024 Form Sheet and plate Coiled sheet Sheet and plato Tent › Tfeat treated und rolled Heat treated ` Vivat treated by user * tevated Neat (seated | Meat treated, cold worked, and aged and aged 7 > Condition -T3 -T46 -T4 -T2 rT?4 -T76 |-Tal -T86 5

0.010- | 0.063-| 0.020-Í ä.08a- 0.280- Í0-ã00- |L@01- |>001- fo.dus— | 0.063 [o 280-[o, sua-|1 o01-|2 60%-fo.010- Ju.063- Jo or0-[0.003-].<0.08340.020- |0.063- |o.250- * Thickness, in 0.062 | 0.249 | 0.082 | 0.499 | 0.500 1.000 |2.006+ | 4.000- | 0.062 | 0.249 0 400 [1 000-12, 000-13 000-fo0.062 J0.128 [0.062 [0.249 ]20.065] 0.062 | 0 240] 0.400 0.500" gg “

Width, In < —-_| | | — = a ¬

Dasls Alnlalnlaln HỊA|HỊA|D|A|B|A|pl a | a | ay a J|A|n|Aln A A fa[ula wo [2

Mechnnt 8 Z

Fas, kal ° lỗ

+ fal] G2) 5] 485) Ga] GHP G7] Ge 6a) 6| 61] 6ãJ 59 63| Ai] 54) SUT BL 62] il Sa 54) 54] 68] 61] 63) ul 62| 61] 674 67| 69{ 7t 74| 70[ 71| 634 70 oad 1 Avg ity ti) 6 | ñ2| fis] 0| 83| 62) 61 Gul Git Ss) Gi] Saf 57] 56) Sup SUF Or 62] cu Sa 34) SM] GIF Gt) 6a BỊ 62| 63Ï 64] 6đ{ 6| THỊ 7IÌ 63Ệ 70 E 0 Bag, hat 3 m

+ as] az] s6p af sof os] ssf Gul s 46| a0} 44 31] 35) 36] ax} as} aa sa) anf auf 42/40} 57] oy] ul 6s] 7] 69| 63| 66] 6| 6 ES] ? sol ad anf al as] sal sal 52] 42} anf 42] sey 42] aa] asf sol gx] | as] - ä6| as} 4a} az] aut Saf Saf 2] an} 66] ssf 65] 66] aa] 65 s a

uy, thi ` Z

+ STP Su] sp da) abl THỊ dnt aay 40| 40Ƒ 10| Saf 33] 36) as} aa 36] đối UAE 40| 4i 40) 55] 57] Ga] 45) 47] i] Gif 65 È

+ vq ce} taf tl suf sa} aul sail 43} to] 44] aa] 35) 36] 3a] mỊ a] 36] at anf az] 40) 5s) 57] 63] 67] 6 6ï} we EB fo

kel kai ssp oop ney any au) ga) aa] aa đu aa] 3s} 35} 33: a] đói $5) 32) Se] Äx| äa| - 37‡ 33 35j 3uJ 4mÌ 4: aif an 8 pat 4 (/0)=1.5 od se M vay suf v3) ba] Be] BY) 92 wy wat ai] BI] Hz} 92) 92t 95) 9] 43] 96) 100] 100] Lou} 16] 104] 105/106] 1a] LOS a =

(/D)=2 + AVP Ds I 12Ì124H116J124{H2Ìt1ni I6|110Ƒ13Ÿi tạ| 118 3H 110) TOSEL TOFU NG] LMG] FU H4 VK] 022) 131) 135) £38) bd] 935] LSP SS BH Oo +\ ” đaệt ‘ iS

(e115 all na 64 Gul 5u] ea] 36) 62! 44) 40) $07 Sal Sal Sa} BOP Sa} $2) Su] Su} 56] Ga] GU) 78] Bs] as] wa] 9] 7] Us] s3ƒ sói sĩ 4 kị (e'D}~ 20 3) 9 74] 6) 70) 54 Saf Ss] atl Gay 54) 38J Sus} šöj 6IỈ BIỈ 6ƒ - 7áƑ — 7H tI| 9i|totltbilitrldoltoi|iee|tezl04 > « nm ag le te] diel |g 9 © af feaf [ag HỆ we ied | 19) a) H 5] | gỊ q ‹ 4 E lan E, 108 pst 5 H tú 105 AST a ` s a |e Ree vs wm] us 10.0 vs wb 0á | 1k0 ef} os 00 9 i] „„ HE ái ta Va H7 B 4 a œ |8 we ˆ mm mã [el a2 [or [we]orpwapqa] ov] we o |e = a (7, 108 mã HH" ~~ a hysteat properties: ia N 9.100 0.100 ta

Buf CE} 0.24 (at 212° F) 0.23 (at 212° F) a

Ấ, Bu/(hr)fEEME)T 70 (at 77° F) 86 (at 7° F)

10 Anse 12.6 (68° to 212° F) 12.6 (68° to 212° F)

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B2.20 | MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES EFFECT OF TEMPERATURE ON 2024 ALUMINUM ALLOYS 5 i i 3 5 2 a i i ‡ 2 Fig 52.60 Effect of temperature on

the ultimate tensile strength (Ftu) of 2024-T3 and 2024-T4 aluminum alloy

(all products except extrusions)

Te nue,P

the ultimate tensile strength (Fry) of

2024-T3 and 2024-T4 aluminum alloy

(extrusions)

‘20 100 oO

Temporaten, F

Fig, B2.62 Effect of temperature on the tensile yield strength (Fty) of 2024-T3 and 2024-T4 aluminum alloy (all products except extrusions), 5 Pos Cont Fy, af Temperance 3

the tensile yield strength (Fty) of

2024-T3 and 2024-T4 aluminum alloy

(extrusions)

or m0 OO a S6 t0 a, Tommercture, F

Fig B2.64 Effect of exposure at elevated temperatures on the room-

temperature ultimate tensile strength

(Feu) of 2024-T3 and 2024-T4 aluminum

alloy (all products except thick extrusions) Per Cent Fy, at Temperotere Teoweee, F

the compressive yield strength (Fey)

of clad 2024-T3 and clad 2024-T4

aluminum alloy (sheet),

Fig B2.66 Effect of exposure at elevated temperatures on the room- temperature tensile yield strength {Fty) of 2024-T3 and 2024-T4

aluminum alloy {all products except

thick extrusions}

the ultimate shear strength (Fs) of

clad 2024-T3 and clad 2024-T4

aluminum alloy (sheet)

Fig B2.68 Effect of temperature on the ultimate bearing strength (Fbru)

of clad 2024-T3 and clad 2024-T4

aluminum alloy (sheet) Pe Coot, ot Tempers Temearene,

Pig B2.69 Effect of temperature on

the bearing yield strength (Fpry) of clad 2024-T3 and clas 2024-T4

aluminum alloy (sheet) 8 Pes CRU E A04 E, ot meesle a MÔ SÓO Tenoerenre,r

Fig B2,70 Effect of temperature on

the tensile and compressive modulus

(E and Eg) of 2024 aiuminum alloy

Pee

Cart

Etongonan

Pig B2.71 Effect of temperature on

the elongation of 2024-T3 and 2024-T4

aluminum alloy (all products except thick extrusions)

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Table B2,15 Design Mechanical and Physical Properties of 7075 Aluminum Alloy (Sheet and Plate) Thicknese (in) 9.260-8.000 Direction of test L Foy {A velues} „ bee Tabls 8.1.1.1.1 Alloy 7075 * Form: Sheet and plate Condition - -T6^ “Thieknogs,in -| 0015-0.039 | 0.040-0.249 | 0.250-0.500 | 0.501-1.000 | 1.001-2.000 | 2.001-2.500 | 2.501-3.000 | 3.001-3.500 | 3.501-4.000 Đasis " A B A B A B A B A B A B A B A A Mechanical properties: Pia, ksi 7] 7 { 77] 7] 77 | mw) 7] 82] 7] 80] 73] 75] 70] 72 68 66 ?6 | THÍ 77| 79] 77} mw | 77] 8sof 77] 7] 73| 7] wy] 7 68 66 6| 69| 6414| 66 64 62 eo} 69[ 67] 70, 67] 69] 69] 72] 63] 71] 62| 65{ 60| 62 58 56 65| 68| 66] 69| 66; 68| 66] 69} 6] 69| 62} 65] 60| 62 58 56 61] 63] 59] 60 56 54 67) 7] 68) mf 69| 71| 69| 72| 68| 71| os] 67] 63| 65 62 60 70| 73] 71| 74| oo] 71| 69] 72] 68} mm] 65] 67| 63] 65 62 60 sẻ ` i ` a wif -: ` et] 66| 62] 63 62 60 46] 47] 46) 47| 46] 47} 47] 49] 46| 47} 43] 45) |] 44 40 39 (/Đ=15) 14 | 1177| 116 [ 119 |- 108 | 110 | 110 | t5 | 109 | 112] 102] 105} 98] tor 95 “ (e/D=20) M44} 48] 146] 150] 139 | 142] 142] 147 | 140] 144] 131) 135] 126] 130 122 H8 Pry, kai (/Đ=1.5) 92] 97| 94| 98| 87] 90| 9590| 0| 83] 92| sit 84| 78| 81 16 r3 (e/D =2 106 | 110] 107] 112} 100} 104] 104} 108] 102] 106) 93] 97] 90] 93 87 84 ¢, percent TỪ T 7 8 8 6 5 5 5 8 ` 7 8 8 6 4 3 3 3 2 ST vị 1 1 1 E, 10" psi 10.3 E., \0* pai 10.5 G, 10* psi 3.0 Physica! properties: a, tb/in 0.101 C, Btu/(ib)(F) 0.23 (at 212°F) K, Buu/{(br)(ft4)(F) sft} 76 (at 77°F) a, 10-*in./in 'F : 12.9 (68° to 212°F)

@ For the stress relieved temper -T651, all values for the ~T6 temper apply with 2.001-2.500 L s

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Table B2.16 Design Mechanical and Physical Properties of Clad 7075 Aluminum Alloy (Sheet and Ptate) Alloy Glad 7075 Form Sheet and plate Condition ~T6 0.015— 0.010- 0.063— 0.188- 0.250- 0.500- 1001- 2.001~ 2.501- | 3.001- | 3.501- Thickness, in Hasis 4 | 0.039 [A 0.062 |B |A 0.187 |B|A 15 0.249 0.499 1.000® 2.000% 2.ã00* 3.0005 | 3.500 | 4.000% |A [B|AIB|AIB|AIB|AlIs A A Mechanical propertie Fay ksi—L T St 7) 73) 72) 74) 73) 75] 75) 77] 78{ 77] 77] 79] 7] 78) 71] ?3| 68| 70] 70) 73) AI 72) 74] 73) 75] 7] 77) 751 771 m1 771 T6 | 77| m1 73] 68] 70] " h 66 66 64 64 ] | | | 67] 60] 64] 66| 64 62 Le Ss? ¬ 60| 63| 62| 64J 6ä | 65 | 64 | 66 | 64| 66 | 64] 66 | 6+Œ| 67] 60 | 62 | 55 | 60] 61) edo 64] 63] 65] 64] 66] 65] 67} 65] 67] 66] 68| 66 | oo] Go} 62| 58| 60] popped -| | | .J 56 56 54 54 | | | er] 63] 59} 6o] 56 54 Fey, ksi Le ST T 62] 64) 67] 65) 64] 66/ 65] 67] 66] 68/ 66 | 60 | 66| 69| 66| 69] @2| 64] 61| 62! food 66| 68 | 67] 69| 68 | 70} G6] Go} 66) 69} 66 | 69 | 62 | 64 | 61 | 62} | | E | | | | | | | | 6| 66| 6| s3] so 60 62 58 58 60 Bay RSE, 42) 44) 43] 44] 44} 45] 45] 46] 45] 46] 46] 47] 45) 46] 42] 43] 40] 41] 39 38 Fung ksi (e/D =1.5) (e/D =2.0) 108 | H10 | 108 | 111 [110 | 112 | 412 | 116 | 405 | 10g | 108 | 111 | 106 | 109 | 99 | 102 | 95] 98! 143 | 139 | 137 | 141 | 139 | 142 | 142 | 146 | 135 | 139 | 139 | 142 | 137 | 140 | 128 | 131 | 122 | 196] 119 | 118 92 90 Por ksi°—(e/D=1.5) | (e/D =2.0) 85} go | s8 | 91] s0| 92] 91] 94} si} a7] 86 | ss| 56 | 90| 78] 81} 75} 73 | 73 98 | 102 | 101 | 102 | 102 | 106 | 104 | 107 | 98 {100 | 99} 102] 99] 101] go] 93] 87!) 90] 94 70 81 e, percent~-L , 7 8 8 8 8] | 6 5 5 5 5 T 7 8 8 8 8 6 4 3 3 3 2 4m ` t 1 1 EB, 108 pst: -Pri, See., 10.3 10.3 10.3 Ee, 10* psi—Pri, See 0.5 98 10.0 10.5 10.5 10.5 G, 108 psi 97 10.0 10.2 Physical properties: w, Ib/in 0.101 C, Btu/(b)(F) K, eof tee a, 10-¢in./in/P

a For the atresa relieved temper —T663, all valucs for the -T6 temper apply with the

exception of Fey Applicable Fey values are se follows: Phicknese (in) 0.260- 0.499 0.600-2.000 2.001-2.500 2.501-8.000 Direction of teat L L 1 L Fey (A values) 82 64 s0 68 0.23 (at 2129) 70 (at 77%F) 12.0 (68° ta 212°R)

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` Table B2.17 Design Mechanical and Physical Properties of 7075 Aluminum Alloy (Extrusions) wy Whfind Œ 180/05)0) ‹ 0.23 (at 212k) K, Bru/{(hr) 2) (F 76 (nt 779 E) Alloy ee

1 1¿xtrusions (rod, b; and shapes)

Condition eee _ _ —T6e Cross: =20 420 — | >30, <32 | <32 = Up to 0.249 | 0.250-0.499 | 0.500-0.749 1500-2.999 3.000-4,499 4.500-5.0 a |p A B A B A B A B A B A B A B a | wef AT BOY AC |B AL a | S a of mw] sata faa] 8I| as} ar] gs] gi | 85} gt] sa} 78] 81| 78 81 a |p bones wl] 78| 77| zm 73| 75| 72| 74} 66) 68| 62] 64| oz] 61] 60 62 š 3 Đo | | 714Ả TH| THỊ 2} ml 72] wi 72| 76} 7Ì 7| 70| 73] 68 71 Ễ ø TC co | oa 7] 6| 68| 63| 66| 6232| 64] ã6| 68] ð54| 56] 4| 5ú6| 53 55 8 a Frey, ksi a Tứ a| | ml vil zi | 72) 7} 72] 7) 72) 7] os] 72 8 đc 2c cuc khen 7Ì 18] va] THỊ | a 7) 7) eo} 72] 05, 68| | | -| 3 lo quy KD co cuc aa} 45| 45{ 47] 465, a7| 45] 47] 45] |} 45] ao] 43] 4a] 43 44 EL |m nh mn " t0 | 107] 07] 102] 97| 102) 97| 102| 97| 1092| 97] 101] 94] 97| 94 97 © |e 1 125 | lãi | 1360| 186 | 130] 136] 130] 136} 130 | 136 | 322] 126] 7| 1252| HỆ 28) BIS Por, ksi or} 96| BI 85, 79) sa] vol sa] 79| 84| vel ail 77| gol 75 78 a¡ 3 i? 98 | 101} 102] 108] 101] 106] 101] 206] 101] 106} 92} 96} 91} 05] 88 92 Š |e e, percent q |M Lovee eee ee ees 7 8 7 8 7 8 1 8 7 8 7 8 6 6 a im 1 5] 5] 4| 3 1Ì 1Ị 1 a " a B, 10° psi & |S E,W! psi * la G, 108 psi _ a 13 Physical properti 0.101 Soe - a - oa) a 4 Pe ~~ tr a a, 10-4 infin fh mm 12.9 (68° to 212°F)

* For the stress relleved compers -‘16510 and -'T6511, all vahies for the ~T6 temper apply, with Thickness tin.) Area (4g in.) Direction of Teat Fy, (A values)

diy exception of Fag Applicable Fe, values are sted below: 1,600-2.U00 <?z0 1 70

Thickness (in) Area (ag bt.) Direction of teat Fey (A values) 9.000-4.490 ‘<32 L s5

#0240 <2 1+ 70 4500-5100 <32 L a

0.250) 1.740 <z 1, a + For extrusions with outstanding legs, the load carrying ability of such iegs shall be determined

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B2 24

7075 ALUMINUM ALLOY (EXTRUSIONS, FORGINGS, BAR, ROD, WIRE) (Cont.}

Table B2.18 Design Mechanical and Physical Properties of 7078 Aluminum Alloy

(Hand Forgings and Die Forgings)

MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES Alloy T075

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ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Ba, 25 7075 ALUMINUM ALLOY (EXTRUSIONS, FORGINGS, BAR, ROD, WIRE) (Cont.)

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B2.26 MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR FLIGHT VEHICLE STRUCTURES EFFECT OF TEMPERATURE ON 7075 ALUMINUM ALLOYS Per Cent Fay oF Tampeeohe 9 SN lạm MO s2 46A 6o Tòn 4o Temeeere,

Fig B2.75 Effect of exposure at elevated temperatures on the room-

temperature tensile yield strength (Fty) of 7075-T6 aluminum alloy {all products) Per Cant Fy, ot Temperate me HO S0 00 666 7115 849 Tamaerohure, E

the ultimate tensile strength (Fty) of 7075-T6 aluminum alloy (ail products)

$

}

i or Fig 52.76 Effect of temperature on

sa the compressive yield strength (Fey)

š of 7075-T6 aluminum alloy (ail products)

3

é Đi nh LG

§

fig B2.73 Effect of temperature on the tensile yield strength (Fty) of

7075-T6 aluminum alloy (all products) Pur Cant Fy, 91 Temperature 8 ome OOOO 0009 Su Temperate, F

the ultimate shear strength (Fgy) of

T0T5-T6 aluminum alloy (all products) Per Cant Fry ot Temparatics rr a Torrone, F

Fig B2.74 Effect of exposure at elevated temperatures on the room- temperature ultimate tensile strength {Ftu) of 7075-T6 aluminum alloy (all products) Pee Coat F ggg Rooms Temperate Tompercnare, F

Fig B2.T8 Effect of temperature on the ultimate bearing strength (Fbru)

of 7075-T6 aluminum alloy (all preducts)

Fig, B2.79 Effect of temperature on the bearing yield strength (Fpry) of 7075-T6 aluminum alloy (all products) & 8 han E on, sọ Bướm Famperstora

Fig B2.80 Effect of temperature on the tensile and compressive modulus

(E and Ec) of 7075-T6 aluminum alloy

Temomature,F

Fig B@.81 Effect of exposure at elevated temperatures on the elongation

of 7075-T6 aluminum alloy (all products

except thick extrusions)

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B2.28 | MECHANICAL AND PHYSICAL PROPERTIES OF METALLIC MATERIALS FOR PLIGHT VEHICLE STRUCTURES

AZ313 MAGNESIUM ALLOY (SHEET

# ' ` ` ` “

Swan, GOH Wn Tongan Mogulus, 10° pai

Fig B2.82 Typical stress-strain and tangent-modulus

curves for AZ31B-O magnesium alloy at room temperature (longitudinal) 8 Streng?n at temperature Exposure up To 00 Ar = Per Cant Fry ot Room Teepeohre 8 wo ao 42G S0 00 XS ®o Temperature, F

Fig B2.83 Effect of temperature on the ultimate tensile strength (Fig) of AZ31B-H24 magnesium alloy 100, i ze Exposure Strength at temoerarure up to 000 he ề A i “ $1 1000 nr 3 a0 về Za 3 B 9 “wae 300 400 500 S00 700 «800 Temperature, F

Fig BZ 84 Effect of temperature on the tensile yield

strength (Fty) of AZ31B-H24 magnesium alloy 100 & of Room Temperature § a & Pee Cent Fe 3 wo MO OOOO Temperotura, F

Fig B2.85 Effect of temperature on the compressive

yieid strength (Foy) of AZ31B-H24 magnesium alloy,

& PLATE) (Cont,) trọng ot temperature Zxpowra up m 1000 w ⁄ § a Room Temperate 3 & Per Cent Fy, L 9 00 Z0 X0 4Ọ) AOO 600 7O 9U Tempegtue,F

Fig B2.86 Effect of temperature on the ultimate shear strength (Fgy) of AZ31B-H24 magnesium ailoy 109 ‘at Tomes Exooaure up 18 1000 trị 80: Per Gent Fy, ot Room Temperataes 8 Z0 0 400 100 a T0 á00 Temperature, F

Fig B2.87 Effect of temperature on the ultimate bear-

ing strength (Fpyy) of AZ31B-H24 magnesium alloy Strengin ar

v9 10 1000 hr 9 10 20 *#Ố 400 40G 600 700 ®O

Tempercture, F

Fig B2 88 Effect of temperature on the bearing yield strength (Fory) of AZ31B-H24 magnesium alloy

30

As Renin erreea-atren C= Taree Menges mamas ‘Be Comoremn strese-sman Ds Comerenane ange mechan a ‘Stress, 1000 pal ° + * ` + lộ ‘Strain, QOOL in fn, Tongert Modaue, pm

Fig B2.89 Typical stress-strain and tangent-modulus

curves for AZ31B-H24 magnesium alloy at room

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