Detailed Description
Survey VTOL operators flying 2m+ wingspan airframes report wingtip deflection exceeding 120mm at 8kg MTOW when using 6061-T6 aluminum spars-directly reducing effective lift-to-drag ratio by 14% and cutting survey coverage per flight by nearly 1.8km². Thermal drift from midday sun softens aluminum further, compounding the problem.
Our T800 prepreg carbon plates (IM modulus 294GPa) replace aluminum spars with a 48% lighter solution that increases specific stiffness by 3.2×. Layup schedule: [0°/90°/±45°]ns symmetric, autoclave cured to void content ≤1.0%. Full-scale three-point bend testing confirms deflection under 18mm at equivalent load-a 6.7× improvement. Fatigue testing to 10⁶ cycles at 60% UTS shows zero delamination.
CNC machining employs high-speed spindle (24,000rpm) with compression-cut toolpath, preventing edge fraying on thin 1.5mm sections. Batch fiber volume fraction is logged at 63±1.5%, with each lot linked to raw material mill certs. Export documentation includes dual-use screening confirmation and commercial invoice with proper HS classification.
Specification
|
Parameter |
Value |
|---|---|
|
Fiber grade |
T800 IM carbon |
|
Layup |
[0/90/±45]ns symmetric |
|
Process |
Autoclave prepreg |
|
Plate size |
Up to 2000×1000mm |
|
Thickness |
1.0mm – 15mm |
|
Flexural modulus |
165GPa |
|
Void content |
≤1.0% |
|
Fatigue life |
>10⁶ cycles @ 60% UTS |
|
Export docs |
Full legal export pack |
Custom FAQ
Q: Can this plate be used as a direct bolt-in replacement for aluminum wing spars?
A: Yes, with redesigned fastener pattern accounting for carbon's lower bearing strength. We provide FEA comparison and transition fitting drawings.
Q: What is the lead time for 20mm thick T800 plates?
A: Prototype: 7–10 days; production batch: 15–20 days including autoclave cycle and NDT.
Q: Is high-modulus carbon safe for close-proximity RF antenna mounting?
A: T800 is conductive; we recommend isolating RF antennas >50mm from carbon structure or using RF-transparent fairing inserts.
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