Product overview
The Mugin GF500 Airframe Kit provides the structural starting point for a fixed-wing UAV build within the Mugin 5 series. Its twin-boom pusher architecture uses a carbon fiber composite primary structure and is designed for gasoline pusher propulsion. Overall dimensions are approximately 5000 × 3500 × 960 mm, with a wing area of 2.62 m² and an approximate airframe weight of 33 kg. Propulsion, flight-control and mission equipment are selected to suit the completed aircraft.
Equipment integration is supported by front and center-wing access hatches. The fiberglass front hatch leaves space beneath its cover for GPS or radio equipment, while the center-wing opening can accommodate a parachute installation or be adapted for a fuel filler. Fuselage internal dimensions are approximately 1800 × 368 × 393 mm, although equipment layout determines the usable volume. Rear landing gear with a custom disc brake system is included for runway operations; the optional 30 L fuel tank is selected separately.
Recommended take-off weight is 72–88 kg, while 120 kg is the airframe structural limit. Maximum payload depends on the final configuration, and operating weight and performance depend on the propulsion, flight-control systems and completed integration. Recommended maximum speed is 40 m/s, recommended cruise speed is 30–35 m/s, and stall speed is 25 m/s at 80 kg MTOW. The recommended pusher propeller is 30–34 inches. Fixed-wing wind resistance is Level 6; VTOL wind resistance and propeller specifications are N/A.
Specifications
| Specification | Value & conditions |
|---|---|
| Product configuration | Mugin GF500 Airframe Kit; base version of the Mugin 5 series; fixed-wing airframe kit with a twin-boom pusher layout. |
| Dimensions | Approx. 5000 × 3500 × 960 mm |
| Fuselage internal dimensions | Approx. 1800 × 368 × 393 mmReference dimensions; usable space depends on the equipment layout. |
| Wing area | 2.62 m² |
| Primary structure | Carbon fiber composite |
| Propulsion design | Designed for gasoline pusher propulsion |
| Fuel tank capacity | 30 L (Optional)Optional fuel tank, selected separately for the order. |
| Maximum structural weight limit | 120 kgAirframe structural limit; aircraft operating weight and performance depend on selected propulsion, flight-control systems and final integration. |
| Maximum payload | Depends on final configurationDepends on final configuration. |
| Recommended maximum speed | 40 m/s |
| Recommended cruise speed | 30–35 m/s |
| Stall speed | 25 m/sAt 80 kg MTOW. |
| Wind resistance | VTOL N/A / Fixed-wing Level 6VTOL: N/A; fixed-wing configuration: Level 6. |
| Airframe weight | Approx. 33 kg |
| Recommended take-off weight | 72–88 kg |
| Recommended pusher propeller | 30–34 inches |
| Recommended VTOL propeller | N/A |
| Front equipment access | Fiberglass front hatch with space beneath it for GPS or radio equipment. |
| Center-wing integration access | Center-wing hatch supports a parachute installation or adaptation for a fuel filler. |
| Rear landing gear | Rear landing gear with a custom disc brake system.Included equipment for runway operations. |
| Equipment integration | Airframe supports integration of selected propulsion, flight-control and mission equipment.Propulsion, flight-control and mission equipment selected for the aircraft build. |
| Internal space limitation | Internal dimensions are reference values.Equipment layout determines usable internal space. |
| Fuel tank supply configuration | Selected separately for the order.Optional 30 L fuel tank. |
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