Aerospace Structural Components
View system integration details
This page explains how Primary Load Frame is classified within Other Transport Equipment Manufacturing. Technical values and manufacturer relationships are research references; confirm the current specification and supplier evidence for each order.
The primary structural element in aerospace assemblies that bears and distributes the main operational loads.
Technical details and manufacturing context for Primary Load Frame
| Parameter | Typical range | Notes & selection driver |
|---|---|---|
| Ultimate Tensile Strength | ≥480 MPa | Minimum for aerospace grade aluminumASTM B557 |
| Yield Strength | ≥400 MPa | Ensures no permanent deformation under loadASTM B557 |
| Fatigue Life | ≥100000 cycles | At max operating stressASTM E466 |
| Density | 2.7–2.8 g/cm³ | Aluminum alloy typicalASTM B557 |
| Modulus of Elasticity | 68–72 GPa | Stiffness for deflection controlASTM E111 |
| Thermal Expansion Coefficient | 22–24 10⁻⁶/K | Matching with composite materialsASTM E831 |
| Operating Temperature Range | -55–70 °C | Aerospace environment limitsMIL-STD-810 |
| Corrosion Resistance | ≥500 h | Salt spray test durationASTM B117 |
| Dimensional Tolerance | ±0.1 mm | Critical for assembly fitISO 2768-m |
| Surface Roughness | Ra 1.6–3.2 µm | Fatigue crack initiationISO 4287 |
| Weight | 15–60 kg | Depends on size and configuration |
| Max Load Capacity | 50–200 kN | Static and dynamic loads |
Ranges are indicative industry figures for RFQ preparation, not a supplier commitment. Confirm every value and standard with the legal manufacturer before ordering.
| pressure: | Up to 10,000 psi |
| other spec: | Maximum dynamic load: 500 kN, Fatigue life: 10^7 cycles at 80% max load |
| temperature: | -65°C to +150°C |
Indicative industry ranges for design and RFQ preparation. Confirm the exact figures and applicable standard with the manufacturer before specifying.
Quoted from the published standard.
A practical evidence checklist for RFQ preparation and supplier evaluation.
Compare the published product scope and source details, then include your specifications and quantity in an enquiry.
Manufacturer profiles associated with Primary Load Frame.
Explore company information and manufacturing capabilities, then discuss the scope of your project with a relevant supplier.
Ask for use case, specification boundaries, supplier type, and RFQ preparation information for this product.
The Primary Load Frame can be made from aerospace-grade aluminum alloy, titanium alloy, or carbon fiber composite, as listed in the directory. The choice depends on the application's structural and weight requirements.
Key parameters include ultimate tensile strength (≥480 MPa for aluminum), yield strength (≥400 MPa), fatigue life (≥100,000 cycles), modulus of elasticity (68–72 GPa), and maximum load capacity (50–200 kN). These are reference ranges; confirm with the manufacturer for the specific model.
Relevant standards include ASTM B557 for tensile properties, ASTM E466 for fatigue, ASTM E111 for modulus, ASTM E831 for thermal expansion, MIL-STD-810 for temperature, ASTM B117 for corrosion, ISO 2768-m for tolerances, and ISO 4287 for surface roughness. These are verification references, not certifications.
Inspect for cracks, corrosion, and deformation, especially at load-bearing points. Verify dimensional tolerances and surface roughness. Follow the manufacturer's maintenance guidelines and use non-destructive testing as required.
This component is essential for the following industrial systems and equipment:
Commonly used trade names and technical identifiers for Primary Load Frame.
Editorial classification, named public sources where available, and source-reviewed manufacturer records.
Compare manufacturer profiles with relevant product and process capability.