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재료 이름
프로세스 호환성
알루미늄 7075-t 7351(EN aw-7075/도 3.4365/UNS a 97075/AlZn 5.5 mgcu)
표준 시스템 | 지명 | 메모 |
|---|---|---|
EN / ISO (주요) | EN AW-7075 (AlZn5.5MgCu) | 주요 국제 지명 [10†L5-L6] |
DIN (독일) | 3.4365 (AlZnMgCu1.5) | 재료 번호;유럽 조달에서 널리 참조되는 레거시 지명 [10†L6-L6] |
UNS (미국) | A97075 | 통합 번호 시스템 지정 [5†L9-L9] |
ANSI / AA (미국) | AA7075은 | 알루미늄 협회 등록 지명 |
JIS (일본) | A7075 | 일본 산업 표준 지정 [5†L17-L17] |
BS (영국, 레거시) | 2L95 / L95 | 레거시 영국 표준 지명 [5†L17-L17] |
AFNOR (프랑스) | A-Z5GU는 | French standard equivalent [5†L17-L17] |
Common Internal / Supplier Code | 76528 | Frequently encountered as an internal or distributor material reference for 7075-T7351 plate; confirm with the specific supplier's certificate |
7075 belongs to the 7xxx series (Al-Zn-Mg-Cu) heat-treatable wrought aluminum alloy family. It is the benchmark high-strength aluminum alloy, originally developed for airframe structures and often referred to as “aerospace aluminum” [7†L5-L6]. The T7351 temper denotes a specific processing route: solution heat-treated, stress-relieved by controlled stretching, and then artificially overaged to maximize stress corrosion cracking (SCC) resistance [6†L2-L7]. This overaging intentionally trades a portion of peak strength (compared with T6 or T651) for a substantial improvement in SCC resistance and fracture toughness, making T7351 the preferred temper for thick plate, heavily machined parts, and long-service structural components exposed to sustained tensile stress [3†L18-L25] [0†L17-L20].
7075-T7351 occupies the “SCC-resistant, fatigue-critical, thick-section” niche in the high-strength aluminum market. It is not a substitute for 6061 on corrosion resistance or weldability, and it is not the absolute peak-strength temper—T6 or T651 will deliver higher tensile and yield values [7†L12-L13]. Instead, 7075-T7351 is specified when the design driver is high strength combined with resistance to stress corrosion cracking under sustained load, particularly in thick plate sections, marine or humid environments, and long-life aerospace or defense structures [3†L18-L25] [12†L32-L35]. For B2B procurement, 7075-T7351 is the default specification for aircraft wing ribs, fuselage frames, heavily machined structural fittings, mold bases for thick-section tooling, and high-performance automotive or motorsport components that cannot tolerate SCC-related field failures [4†L5-L9] [7†L15-L18].
부동산 | Typical Value (T7351) | Unit | Notes / Design Implication |
|---|---|---|---|
Density | 2.81–3.0 | g/cm³ | Approximately one-third the density of steel; weight savings remain a primary driver [6†L23-L23] [0†L8-L9] |
Ultimate Tensile Strength (UTS) | 505–510 | MPa | Lower than T6/T651 (~572 MPa); the trade-off for improved SCC resistance and toughness [6†L15-L16] [0†L7-L8] [7†L12-L12] |
Yield Strength (Rp0.2) | 410–434 | MPa | Lower than T651 (~503 MPa); design allowable must use T7351-specific values [6†L15-L16] [7†L13-L13] |
휴식에 연장 | 7.5–8 | % | Slightly lower ductility than T651; still adequate for most machined structural parts [6†L12-L13] [7†L13-L13] |
경도 | 135–140 | HB | Lower than T651 (~150 HB); reflects the overaged temper [6†L11-L11] [0†L16-L16] [7†L13-L14] |
Modulus of Elasticity | 70–71.7 | GPa | Stiffness similar to other aluminum alloys; no stiffness penalty for the SCC-resistant temper [6†L12-L12] [8†L12-L12] |
Fatigue Strength (5×10⁸ cycles) | ~160 | MPa | Good fatigue resistance; surface condition and finishing process materially affect fatigue life [6†L13-L13] [8†L13-L13] |
열 전도성 | 130 | W/m·K | Lower than 6061 (~167 W/m·K); heat concentrates at the cutting edge during machining [6†L19-L19] [0†L8-L8] |
Coefficient of Thermal Expansion (CTE) | 23 | µm/m·°C | Comparable to other aluminum alloys [6†L19-L19] |
Maximum Mechanical Service Temperature | ~200 (121 for sustained load) | °C | Strength degrades above 200°C; for sustained-load SCC-critical applications, design limits are lower [6†L16-L17] [0†L20-L20] |
Melting Range (Solidus–Liquidus) | ~480–640 | °C | Solidus 480°C; liquidus 640°C [6†L17-L18] |
SCC resistance advantage: The defining property of T7351. The overaged microstructure raises the stress corrosion cracking threshold substantially compared with T6/T651, making T7351 suitable for sustained tensile loads in the short-transverse direction—a loading condition that can cause delayed failure in T651 [3†L18-L25] [7†L9-L10] [8†L28-L29].
Fracture toughness: Improved compared with T651. The T73-type overaging increases resistance to crack propagation, which is why T7351 is preferred for damage-tolerance-critical and thick-section parts [0†L18-L20] [3†L20-L25].
Fatigue resistance: 좋은 (fatigue strength ~160 MPa at 5×10⁸ cycles). However, surface treatments can reduce fatigue life; finishing processes must be qualified against the specific loading spectrum [6†L13-L13] [11†L7-L8] [11†L40-L42].
Strength trade-off: T7351 delivers roughly 10–15% lower tensile and yield strength than T651. This is a deliberate engineering trade: strength is sacrificed for field reliability under sustained load and corrosive exposure [7†L12-L13] [12†L32-L35].
All values are typical industry data based on makeitfrom, ASTM/EN standards, and mill product literature. Actual properties vary with product form (plate, bar, forging), thickness, and specific heat treatment lot. Always confirm the mill certificate for the specific delivery, especially when designing to T7351-specific allowables rather than T651 allowables.
Element | Min (%) | Max (%) | Functional Role in 7075 |
|---|---|---|---|
Zn (Zinc) | 5.1 | 6.1 | Primary strengthening element; forms MgZn₂ precipitates [6†L29-L30] [9†L42-L42] |
Mg (Magnesium) | 2.1 | 2.9 | Partners with Zn in precipitate formation [6†L30-L30] [9†L43-L43] |
Cu (Copper) | 1.2 | 2.0 | Improves strength and SCC resistance; reduces corrosion resistance and weldability [6†L30-L30] [9†L43-L43] |
Cr (Chromium) | 0.18 | 0.28 | Grain refinement; helps resist stress corrosion cracking [9†L41-L41] |
Fe (Iron) | — | 0.50 | Impurity; higher Fe forms coarse intermetallics that reduce toughness |
Si (Silicon) | — | 0.40 | Impurity; kept low |
Mn (Manganese) | — | 0.30 | Minor grain-refining effect |
Ti (Titanium) | — | 0.20 | Grain refiner |
Others (each / total) | — | 0.05 / 0.15 | — |
Al (Aluminum) | Remainder (typically 86.9–91.4%) | Balance [6†L29-L29] | |
General / atmospheric corrosion: Average to moderate. The copper content (1.2–2.0%) reduces the alloy's inherent corrosion resistance compared with 6xxx or 5xxx alloys. Protective finishing is recommended for exposed service [0†L23-L24] [12†L19-L20].
Stress-corrosion cracking (SCC): Good–excellent (superior to T651). This is the primary reason T7351 is specified over T6/T651. The overaged temper and controlled stretching dramatically raise the SCC threshold, making T7351 resistant to the delayed, brittle failures that can occur in T651 under sustained tensile stress [3†L18-L25] [12†L32-L35].
Exfoliation corrosion: 좋은. Overaged tempers like T7351 are generally resistant to exfoliation attack [3†L23-L25].
Anodizing compatibility: Not recommended for cosmetic anodizing. The high zinc and copper content can cause dark spots, staining, or color inconsistency in conventional anodizing. Hard anodizing is technically feasible and provides excellent wear resistance (coating hardness can exceed HV 400), but the cosmetic result is not uniform [12†L20-L22] [8†L35-L38].
Welding: Poor / Not recommended. 7075 is generally considered not weldable by conventional fusion processes due to hot-cracking sensitivity and loss of properties in the heat-affected zone. Welding also destroys the T7351 temper and the SCC resistance that was the reason for selecting this material [12†L14-L15] [12†L29-L29].
Mechanical fastening: Excellent / Preferred. Riveting, bolting, and interference-fit fastening are the standard joining methods for 7075-T7351 aerospace and structural assemblies [12†L10-L10].
Adhesive bonding: 좋은, provided the surface is properly prepared (degreased, etched, and primed). Bonded doublers and repairs are used in aerospace applications.
Rating: MODERATE (good machinability for a high-strength alloy, but abrasive to tooling and sensitive to distortion)
7075-T7351 is generally considered to have good machinability—its high hardness produces clean, powdery chips and excellent surface finish potential [0†L24-L25] [2†L6-L7]. However, two alloy-specific characteristics separate it from 6061 and demand process discipline: (1) accelerated tool wear—the hard intermetallic particles in 7075 cause tool wear 30–50% faster than 6061—and (2) residual stress redistribution, which remains a distortion risk in thin-walled or asymmetric parts even with the stress-relieved T7351 temper [2†L6-L8] [8†L21-L28]. T7351 mitigates the SCC risk and improves toughness, but it does not eliminate the need for distortion-control strategies when machining large pockets or thin ribs from thick plate [2†L40-L42].
응용 프로그램 | Tool Recommendation | Key Geometry / Coating |
|---|---|---|
밀링 | Diamond-coated carbide or PCD (polycrystalline diamond) for production; sharp carbide for prototypes | Diamond coating reduces the accelerated wear caused by 7075's abrasive particles; positive rake for chip evacuation [8†L23-L23] |
커브 | Carbide inserts; PCD for high-volume finishing | Sharp, positive rake; chip breaker optimized for aluminum; wiper geometry for finish |
Drilling | Solid carbide with polished flutes | 135–140° point angle; internal coolant preferred for deep holes |
Thin-wall milling | Sharp, high-helix carbide end mills | Toolpath strategy is more critical than tool geometry; see distortion control below |
Operation | Cutting Speed / Feed Strategy | Notes / Source Basis |
|---|---|---|
Milling (general 7075) | Linear speed 150–220 m/min; feed per tooth 0.03–0.10 mm | Recommended range for 7075; slightly lower than 6061 to manage tool wear and heat [8†L22-L23] |
Milling (distortion-sensitive) | Use quasi-symmetric staggered toolpaths; avoid contour-parallel for thin-wall and deep-pocket parts | Published thin-wall studies on Al 7075-T7351 show that toolpath strategy significantly affects thickness deviation; staggered strategies reduce warping [2†L10-L14] [2†L28-L32] |
Stress-relief (if required) | 230°C for 2–4 hours between roughing and finishing for extreme distortion cases | Recommended for high-residual-stress 7075 plate when machining deep pockets or frames [8†L28-L29] |
냉각 | High-pressure flood coolant mandatory; MQL only with careful evaluation | 7075 is more sensitive to machining heat than 6061; above 250°C strength drops sharply and built-up edge accelerates [8†L30-L33] |
Parameters are starting-point references from machining guides and published studies on 7075 and 7075-T7351. Evefab validates and adjusts every program against the specific part geometry, fixturing, machine tool, and mill certificate. For thick plate and thin-wall parts, a rough → stress-relief (if required) → finish sequence is planned at the quotation stage.
Issue | Root Cause in 7075-T7351 | Evefab Solution |
|---|---|---|
Accelerated tool wear | Hard intermetallic particles (Al-Cu-Mg-Zn phases) abrade the cutting edge; wear rate is 30–50% faster than 6061 [2†L6-L8] [8†L21-L22] | Diamond-coated or PCD tooling; proactive tool-life monitoring; do not extend tool replacement intervals for cost savings [8†L23-L23] |
Distortion / warping after machining | Residual stress redistribution during material removal; T7351 is stress-relieved by stretching but not stress-free [2†L40-L42] [8†L26-L28] | Quasi-symmetric staggered toolpaths; balanced material removal; stress-relief (230°C / 2–4 h) between roughing and finishing for extreme cases [8†L28-L29] |
Built-up edge (BUE) | Aluminum's affinity for tool materials, aggravated by inadequate cooling or dull edges | Sharp, polished edges; high-pressure flood coolant; positive rake; diamond coatings |
Surface finish inconsistency | Tool wear and BUE transfer marks on the high-hardness matrix | PCD or diamond-coated finishing tools; optimized finishing passes; in-process roughness checks |
Chatter in thin webs and ribs | Modulus is only ~70 GPa; high strength does not compensate for low stiffness in thin sections | Custom vacuum fixtures or low-melt fixturing; support structures; trochoidal or high-feed paths with light radial engagement |
Anodizing cosmetic defects | High Zn and Cu content cause dark spots or staining in conventional anodizing [12†L20-L22] | Hard anodizing if wear resistance is required (functional, not cosmetic); otherwise specify chemical conversion coating or primer/paint for corrosion protection [8†L37-L38] |
Standard CNC tolerance (milling): ±0.02 mm achievable on stable features; ±0.005 mm achievable on critical features with in-process verification
As-machined surface roughness: Ra 0.8–1.6 µm typical with carbide; Ra 0.4–0.8 µm achievable with PCD/diamond-coated finishing and optimized parameters
Flatness after machining: dependent on part geometry and toolpath strategy; quasi-symmetric staggered strategies are used to control distortion on thin-wall and deep-pocket parts [2†L10-L14]
3/4/5-axis CNC milling — primary process for aerospace structural parts, thick plate components, mold bases, and heavily machined fittings
CNC 선반가공 — shafts, pins, and highly stressed rotational components
CNC drilling / reaming / tapping — hole preparation for riveted and bolted assemblies
CNC boring — precision bores for bushings, bearings, and actuator interfaces
Surface grinding — for tight flatness or finish requirements beyond milling capability
High-speed machining (HSM): Good–excellent. 7075-T7351 responds well to appropriate cutting speeds (150–220 m/min), and diamond-coated tooling is compatible with HSM spindles [8†L22-L23]. The limiting factor is thermal management and tool wear, not the alloy's basic machinability.
Thin-walled / distortion-critical machining: Moderate, but manageable with the correct strategy. This is the defining process challenge for 7075-T7351. Published studies on thin sections confirm that toolpath strategy materially affects dimensional accuracy, and that a stress-relief step between roughing and finishing can be necessary for extreme geometries [2†L10-L14] [8†L28-L29]. Evefab treats toolpath and stress-management planning as a first-class engineering deliverable for these parts.
Complex geometry / monolithic structural parts: 걸출했어 when the design intent is high strength with significant material removal from thick plate or billet. 7075-T7351 is routinely machined into wing ribs, fuselage frames, and heavily pocketed structural fittings where the buy-to-fly ratio is aggressive and SCC resistance under sustained load is a safety-critical requirement [4†L32-L32] [7†L15-L17].
산업 | Typical 7075-T7351 Parts | Why 7075-T7351 Fits |
|---|---|---|
Aerospace & Defense | Wing ribs, fuselage frames, wing spars, landing gear support fittings, missile structures, satellite brackets | SCC resistance under sustained load; improved fracture toughness; qualified under AMS 4124 and ASTM B209; ideal for thick plate and long-life structures [1†L18-L21] [5†L23-L27] [7†L15-L16] |
High-Performance Automotive & Motorsport | Chassis components, suspension arms, gearbox housings, wing supports, high-load brackets | Strength close to steel at one-third the weight; T7351 provides SCC margin for parts exposed to weather or marine air [4†L5-L9] [2†L19-L20] |
Precision Mold Bases & Tooling | Thick-section mold bases, mold frames, high-precision injection mold components, fixtures for heavy machining | High hardness (135–140 HB) and dimensional stability after T7351 processing; good machinability for deep pockets; SCC resistance for long-service tooling [7†L17-L17] [0†L23-L25] |
Marine & Offshore (protected / sustained load) | Structural fittings, mast components, deck hardware (with protective coating), subsea brackets | T7351 is specified over T651 where sustained tensile load and marine exposure coexist; protective finishing is still required for general corrosion [12†L32-L35] [3†L18-L25] |
Industrial & Robotics | Robot arms, end-effector structures, high-load frames, precision machine components | Lightweighting reduces inertia and improves dynamic response; SCC resistance supports long-term reliability in humid factory environments [7†L16-L17] |
Thick-section wing ribs and fuselage frames with deep pockets: 7075-T7351 plate is machined into integral rib and frame structures with deep lightening pockets and thin flanges. The T7351 temper provides the SCC resistance needed for sustained load in service, while Evefab’s quasi-symmetric staggered toolpath strategy and optional intermediate stress-relief manage the residual stress redistribution that would otherwise cause distortion in T651 [7†L15-L16] [8†L26-L29].
Highly stressed aircraft fittings and landing-gear support components: 7075-T7351 is machined into load-transfer fittings, lugs, and attachment points where static strength, fatigue life, and SCC resistance are all critical. The T7351 temper’s improved fracture toughness compared with T651 is a direct safety benefit in these applications [3†L20-L25] [4†L5-L7].
Thick mold bases and heavy-duty tooling for injection molding: 7075-T7351 offers higher hardness and wear resistance than 6061, combined with the SCC resistance needed for long-service mold bases that may see sustained clamping loads. It machines to fine finishes and holds dimensional stability when toolpaths are managed correctly [7†L17-L17].
High-performance automotive suspension and chassis components: The combination of high strength, good fatigue resistance, and SCC margin for weathered exposure makes 7075-T7351 a standard choice for motorsport and high-end automotive structural parts where T651’s SCC sensitivity would be a durability concern [4†L5-L9] [2†L19-L20].
Evefab maintains qualified stock of EN AW-7075 (3.4365 / AlZn5.5MgCu) plate and bar in T7351 temper, with traceability to AMS 4124, ASTM B209, and EN 573-3 where required [1†L18-L21] [5†L23-L27]. For every production lot, we review the mill certificate’s actual Zn, Mg, Cu, and Cr values and confirm the T7351 processing route—solution treatment, controlled stretching, and overaging to maximize SCC resistance—because these variables directly affect machinability, distortion behavior, and final properties [6†L2-L7]. If the application involves moderate sustained load with less severe SCC exposure, our engineering team transparently discusses whether T651 or T6 would deliver higher strength at lower cost; if maximum SCC resistance and toughness are the drivers, we recommend T7351 without compromise [12†L32-L35]. We help you select the correct temper for the actual service loading, not just the highest strength number on the datasheet.
Our process library includes validated parameter sets for 7075-T7351 across roughing, finishing, drilling, and boring operations, derived from published machining guides and our own production history [8†L22-L23]. For thick-plate and distortion-critical programs, we do not rely on CAM defaults: we plan quasi-symmetric staggered toolpath strategies and, where the geometry and residual stress risk demand it, a rough → stress-relief (230°C / 2–4 h) → finish sequence [8†L28-L29]. Yield rates for 7075-T7351 production parts exceed 96% at first-pass inspection on repeat-order programs, with dedicated diamond-coated and PCD tooling and high-pressure coolant where tool wear and surface finish are critical [8†L23-L23].
Evefab delivers ±0.02 mm standard machining tolerance및±0.005 mm on critical features for 7075-T7351 components using 4-axis and 5-axis CNC platforms. As-machined surface finish reaches Ra 0.8–1.6 µm with carbide tooling and Ra 0.4–0.8 µm with PCD/diamond-coated finishing. For corrosion protection—which is recommended for exposed 7075-T7351 parts—we coordinate chemical conversion coating, primer and paint systems, and hard anodizing where wear resistance is required through qualified aerospace-approved finishing partners [8†L34-L38]. We do not recommend conventional cosmetic anodizing on 7075-T7351, because the high Zn and Cu content causes staining and color inconsistency; for functional surfaces, hard anodizing is the appropriate specification [12†L20-L22].
From 1–5 piece prototype runs (typically 3–7 working days depending on geometry and finishing) to 10,000+ piece annual volumes, Evefab scales 7075-T7351 production across dedicated machining cells configured for high-strength aluminum. For large thick-plate aerospace and tooling parts, we plan the entire workflow—material sourcing, temper verification, roughing, dimensional stabilization (including intermediate stress-relief if specified), finishing, and final CMM inspection—so the delivered part meets the design intent for both strength and geometry. For programs transitioning from prototype to production, we carry the validated toolpath and parameter set forward, avoiding the “prototype-to-production distortion surprise” that occurs when a proven process is replaced by an unvalidated CAM default.
Every 7075-T7351 shipment includes a mill certificate (EN 10204 3.1 or AMS-compliant certification) traceable to the heat/lot number, with actual chemical composition and mechanical properties, including confirmation of the T7351 temper and overaging treatment. In-process inspection uses CMM, surface roughness testers, and, for distortion-critical parts, flatness verification on a granite surface plate. Final inspection reports include dimensional data, surface finish values, and visual criteria per your drawing. FAI (First Article Inspection), PPAP, and AS9102 documentation are available for aerospace and production programs. For defense and aerospace applications, we can additionally coordinate NADCAP-approved special process suppliers and third-party source inspection as required.
Contact Evefab for a CNC machining quote and DFM consultation for your Aluminum 7075-T7351 (3.4365 / AlZn5.5MgCu) project. Upload your CAD files and specify temper (T7351/T651), plate thickness, sustained-load direction (to verify SCC exposure), distortion sensitivity (thin-wall vs. solid), fatigue-critical features, and finishing requirements—our engineering team will return a manufacturability review and firm quote within 24 hours.
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