High-Temperature Prepreg Epoxy System for Military/Industrial UAV
Key Features
- Tg 150–180°C (dry) meets thermal demands of high-power UAV engines and desert operating environments
- 30-day out-time at 23°C enables complex multi-zone lay-up of large UAV structures
- CAI >250 MPa and OHC ≥280 MPa satisfy aerospace-grade damage tolerance requirements
- OOA/VBO capable — <1% void content without autoclave, reducing capital tooling cost
- Stable hot-wet performance — Tg retention ≥85% after 14-day water soak at 70°C
- Available in UD and fabric formats up to 600 mm wide for automated lay-up compatibility
A high-performance prepreg epoxy matrix system designed for autoclave and out-of-autoclave (OOA) manufacture of military, industrial surveillance, and long-endurance UAV airframe structures. The system exhibits a controlled out-time of 30 days at room temperature, enabling complex lay-up schedules without compromising resin flow behavior or final mechanical properties.
Autoclave cure at 120–135°C/6 bar produces a dense, void-free laminate with Tg of 150–180°C, suitable for high-performance UAV structures operating near engine exhaust zones or in desert/high-altitude thermal environments. OOA processing with vacuum-bag-only (VBO) cure achieves Tg ≥ 150°C with void content below 1%, meeting aerospace structural certification standards.
Compressive strength after impact (CAI) exceeds 250 MPa, and open-hole compression (OHC) strength is ≥ 280 MPa, making this system suitable for UAV wing skins, fuselage bulkheads, and rotor blade structures where both hot-wet performance and impact damage tolerance are mandatory. Supplied as unidirectional (UD) and fabric-format prepregs in widths up to 600 mm.
Specifications
| Parameter | Value |
|---|---|
| Out-time at 23°C | 30 days |
| Storage life at -18°C | 12 months |
| Prepreg areal weight (UD) | 150–300 g/m² |
| Cure temperature (OOA/VBO) | 120°C / vacuum bag only |
| Open-hole compression (OHC) | ≥280 MPa |
| Void content (OOA/VBO cure) | <1.0% |
| Cure temperature (autoclave) | 120–135°C / 6 bar |
| Void content (autoclave cure) | <0.5% |
| Glass transition temperature (Tg) | 150–180°C (dry) / 130–150°C (wet) |
| Compressive strength after impact (CAI) | >250 MPa |
Applications
FAQ
For OOA/VBO cure of wing skins, the recommended cycle is: (1) Debulk at room temperature for 1 hour under full vacuum (≥0.95 bar); (2) Heat at 1–3°C/min to 120°C; (3) Hold at 120°C for 4 hours under continuous vacuum; (4) Free-standing post-cure at 150°C for 2 hours to achieve maximum Tg. Ensure the vacuum bag stack includes a single-ply breather and Gore-Tex membrane between laminate and bleeder to control resin bleed precisely. Panel thickness uniformity tolerance is ±0.1 mm for certified structural parts.
Direct Contact
💬WhatsApp +86 156 3910 0440Telegram +86 156 3910 0440✉️[email protected]Reply within 24 hours
Related Products
Low-Viscosity Infusion Epoxy for Carbon Fiber Drone Frames
Ultra-low mixed viscosity (200–500 mPa·s) enables complete CF wet-out in VARI and RTM without vacuum assistance above 0.8 bar
Impact-Toughened Epoxy for Carbon Fiber Drone Propellers
GIC 400–600 J/m² — 3–4× higher than unmodified epoxy, reduces catastrophic delamination on impact
Radar-Transparent Cyanate Ester Resin for UAV Radome
Dk 3.0–3.2 and Df 0.005–0.008 at 10 GHz — among the lowest of any structural composite matrix
Epoxy Structural Adhesive for Carbon Fiber to Aluminum Drone Bonding
Lap shear 25–35 MPa on CF and aluminum — 3–5× safety factor over typical drone joint loads