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2024 T351 Aluminum Plate

With the continuous advancement of aviation technology and the expansion of the aviation market, the demand for high-performance aluminum alloy materials is also increasing. The demand for 2024 aluminum alloy plates, as an excellent aviation material, will continue to grow.

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1. Material Composition & Manufacturing Process

2024 aluminum alloy (AMS 4035, ASTM B209, EN 485) is a high-strength Al-Cu-Mg alloy engineered for critical structural applications. The T351 temper provides optimal fracture toughness through solution heat treatment, controlled stretching, and natural aging:

Alloy Chemistry:

Copper (Cu): 3.8-4.9% (precipitation hardening)

Magnesium (Mg): 1.2-1.8% (S-phase formation)

Manganese (Mn): 0.30-0.9% (grain refinement)

Iron (Fe): ≤0.50% max

Base Material:

Aluminum (Al): ≥93.5% (balance)

Controlled Impurities:

Zinc (Zn): ≤0.25% max

Chromium (Cr): ≤0.10% max

Silicon (Si): ≤0.50% max

Precision Thermomechanical Processing:

Direct Chill Casting: 700-750°C molten temperature

Homogenization: 480-495°C for 12-24 hours

Hot Rolling: Reduction at 400-440°C

Solution Heat Treatment: 493-502°C (±3°C) for 1.5-2 hours

Water Quenching: Cooling rate >170°C/sec

Stretching: Permanent set 1.5-3% (T351 specific)

Natural Aging: 30-120 days at ambient temperature

Certified to AMS 4035 and NAS 402 specifications with full aerospace traceability from melt to plate.

2. Mechanical Properties of T351 Temper State

Property	Minimum	Typical	Test Standard	Aerospace Significance
Ultimate Tensile Strength	415 MPa	440-480 MPa	ASTM B557	Superior to T3 temper
Yield Strength (Rp0.2)	275 MPa	300-320 MPa	ASTM B557	85% retention at 150°C
Elongation (50mm gauge)	8%	10-15%	ASTM B557	Higher in rolling direction
Shear Strength	255 MPa	285 MPa	ASTM B831	65% of tensile strength
Bearing Strength	580 MPa	620 MPa	ASTM E238	e/D=2.0 condition
Fatigue Strength (10⁷)	140 MPa	160 MPa	ASTM E466	R=0.1 condition
Hardness (Brinell)	120 HB	125-135 HB	ASTM E10	Consistent through section
Fracture Toughness (K₁c)	35 MPa√m	40 MPa√m	ASTM E399	L-T orientation preferred
Compression Yield	275 MPa	300 MPa	ASTM E9	Rib/spar applications

3. Microstructure & Thermomechanical Processing

T351 Temper Specifics:

Solution Heat Treatment:

Temperature: 495±5°C

Soak Time: 30 min/inch thickness

Quench Delay: <10 seconds

Stretching Process:

Permanent Set: 2.0-2.5%

Uniformity Tolerance: ±0.15%

Natural Aging Kinetics:

80% properties in 4 days

Full stabilization in 30 days

Microstructural Characteristics:

Grain Structure: Unrecrystallized with pancake grains

Aspect Ratio: 8-10:1 in rolling direction

Precipitate Phases:

θ' (Al₂Cu) platelets (10-100nm)

S (Al₂CuMg) phases

Dispersoids:

Al₂₀Cu₂Mn₃ compounds

Dislocation Density: 5-8×10¹⁰/cm²

Subgrain Size: 1-3μm

4. Dimensional Specifications & Tolerances

Parameter	Aerospace Tolerance	Commercial Tolerance	Notes
Thickness (3-150mm)	±0.3%	±0.7%	AMS 4035 Class A
Width (1200-3000mm)	±3 mm	±12 mm	Edge exclusion zone 25mm
Length (2400-12000mm)	+5/-0 mm	+20/-0 mm	Precision cuts available
Flatness	0.2% of length	0.5% of length	Per NAS 402 requirements
Squareness	1 mm/1000 mm	3 mm/1000 mm	Critical for spars
Surface Roughness	0.4-0.8 μm Ra	1.0-3.0 μm Ra	Mirror finish optional

Special Capabilities:

Oversize Plates: Up to 4000mm wide × 15000mm long

Ultrasonic Inspection: ASTM B594 Level AA

Edge Conditions: Machined, sheared, or abrasive cut

Weight Formula: Thickness(mm) × Width(m) × Length(m) × 2.78 = Weight(kg)

5. Corrosion Resistance & Protection Systems

Environment	Performance	Protection Method	Aerospace Application
Humidity Exposure	Fair	Alclad version recommended	Skin panels
Salt Spray (500hr)	Poor	Anodizing + primer required	External structures
Stress Corrosion	Moderate	Overaging (T851) optional	Critical load components
Exfoliation	Poor	Cladding essential	Wing surfaces
Fuel Tank Environment	Good	Integral fuel tank coatings	Wing box structures
Galvanic Corrosion	Fair	Isolation washers	Fastened joints

Surface Treatment Systems:

Alclad Coating: 5-10% total thickness per side

Anodizing:

Chromic acid: 2.5-5.0μm

Sulfuric acid: 10-25μm

Primers:

Epoxy primers (8-15μm)

Chromate primers (5-8μm)

Topcoats:

Polyurethane topcoats (25-50μm)

Specialty fuel tank sealants

Chemical Conversion: Titanium-zirconium systems

6. Machining & Fabrication Properties

Operation	Tool Material	Recommended Parameters	Aerospace Practice
Milling	Carbide inserts	Vc=600-1000 m/min, fz=0.15 mm	High RPM machining
Drilling	Carbide drills	Vc=80-150 m/min, fn=0.1 mm/rev	Peck drilling cycle required
Turning	PCD/CBN tools	Vc=600-900 m/min	Dry machining feasible
Reaming	Coated reamers	Vc=20-30 m/min	H8 tolerance achievable
Grinding	CBN wheels	Vc=30-35 m/sec	Surface finish Ra 0.2μm
EDM	Graphite electrodes	Current: 15-30A	Precision cavity machining

Forming Considerations:

Bend Radius: 3T minimum (T=thickness)

Springback Compensation: 2-4° overbend required

Hot Forming: 150-190°C recommended

Creep Age Forming: 120-130°C for 8-24 hours

Post-forming Heat Treatment: Prohibited in T351

7. Welding & Joining Technologies

Process Limitations:

Fusion Welding: Generally not recommended

Alternative Joining Methods:

Riveting: CherryMAX aerospace rivets

Adhesive Bonding: FM-300 film adhesive

Friction Stir Welding: Limited applications

Laser Beam Welding: Experimental only

Brazing: Vacuum furnace brazing

Repair Welding Protocol:

Material Condition: Only T351 plate

Filler Metal: 4043 or 2319 alloys

Preheat: 120-150°C mandatory

Post-Weld Aging: 120°C/24hr recommended

NDT Requirements: Dye penetrant mandatory

8. Physical Properties for Aerospace Design

Property	Value	Flight Application Significance
Density	2.78 g/cm³	Weight-critical structures
Melting Range	500-635°C	Firewall protection limits
Thermal Conductivity	121 W/m·K	Heat sink components
Electrical Conductivity	34% IACS	Avionics housing applications
CTE (20-100°C)	22.9 ×10⁻⁶/K	Thermal stress calculations
Young's Modulus	73.1 GPa	Wing flexure modeling
Poisson's Ratio	0.33	Finite element analysis
Fatigue Crack Growth Rate	4×10⁻⁴ mm/cycle	Damage tolerance design
Damping Capacity	0.001	Vibration-sensitive components

9. Quality Control & Certification

Testing Protocol:

Chemical Analysis: Spark OES per ASTM E1251

Mechanical Testing:

Longitudinal/transverse specimens

Tensile tests per 1000kg lot

Fracture Toughness Testing:

K₁c values for all plate shipments

Corrosion Testing:

ASSET per ASTM G66

EXCO per ASTM G34

NDT Requirements:

Ultrasonic per AMS 2631

Fluorescent penetrant inspection

Eddy current for surface flaws

Microstructure Control:

Grain size per ASTM E112

Precipitate distribution analysis

Aerospace Certifications:

AS9100 Rev D Quality System

NADCAP Accredited:

Heat Treating

Chemical Processing

NDT

MIL-Specs:

MIL-A-83377

MIL-PRF-6855

OEMS Approval: Boeing D6, Airbus AIMS

EU Aviation Safety: EASA Form 1

10. Industrial Applications & Handling

Aerospace Applications:

Aircraft fuselage skins

Wing stringers and ribs

Landing gear components

Engine mounting structures

Rotorcraft transmission platforms

Spacecraft fuel tanks

Missile airframes

Flight control surfaces

Material Handling Protocol:

Storage Conditions:

Temperature: 15-30°C

Humidity: <45% RH

Isolation from corrosive materials

Stacking Requirements:

Wooden dunnage at 300mm intervals

Maximum stack height: 800mm

Protective interleaving paper

Lifting Systems:

Vacuum pad lifters

Spread beam systems

Non-magnetic handling fixtures

Transport Precautions:

VCI (Vapor Corrosion Inhibitor) protection

Desiccant packages

Weatherproof enclosures

Post-processing:

Immediate surface cleaning

Temporary corrosion protection

Controlled aging period

Time-limited storage before use

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